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Journal articles on the topic 'Subsonic wind tunnels'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

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1

Tabatabaei, Narges, Ramis Örlü, Ricardo Vinuesa, and Philipp Schlatter. "Aerodynamic Free-Flight Conditions in Wind Tunnel Modelling through Reduced-Order Wall Inserts." Fluids 6, no. 8 (July 27, 2021): 265. http://dx.doi.org/10.3390/fluids6080265.

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Parallel sidewalls are the standard bounding walls in wind tunnels when making a wind tunnel model for free-flight condition. The consequence of confinement in wind tunnel tests, known as wall-interference, is one of the main sources of uncertainty in experimental aerodynamics, limiting the realizability of free-flight conditions. Although this has been an issue when designing transonic wind tunnels and/or in cases with large blockage ratios, even subsonic wind tunnels at low-blockage-ratios might require wall corrections if a good representation of free-flight conditions is intended. In order to avoid the cumbersome streamlining methods especially for subsonic wind tunnels, a sensitivity analysis is conducted in order to investigate the effect of inclined sidewalls as a reduced-order wall insert in the airfoil plane. This problem is investigated via Reynolds-averaged Navier–Stokes (RANS) simulations, and a NACA4412 wing at the angles of attack between 0 and 11 degrees at a moderate Reynolds number (400 k) is considered. The simulations are validated with well-resolved large-eddy simulation (LES) results and experimental wind tunnel data. Firstly, the wall-interference contribution in aerodynamic forces, as well as the local pressure coefficients, are assessed. Furthermore, the isolated effect of confinement is analyzed independent of the boundary-layer growth. Secondly, wall-alignment is modified as a calibration parameter in order to reduce wall-interference based on the aforementioned assessment. In the outlined method, we propose the use of linear inserts to account for the effect of wind tunnel walls, which are experimentally simple to realize. The use of these inserts in subsonic wind tunnels with moderate blockage ratio leads to very good agreement between free-flight and wind tunnel data, while this approach benefits from simple manufacturing and experimental realization.

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2

Wiriadidjaja, Surjatin, Fadilah Hasim, Shuhaimi Mansor, Waqar Asrar, Azmin Shakrine Mohd Rafie, and Ermira Junita Abdullah. "Subsonic Wind Tunnels in Malaysia: A Review." Applied Mechanics and Materials 225 (November 2012): 566–71. http://dx.doi.org/10.4028/www.scientific.net/amm.225.566.

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In Malaysia, there exist wind tunnels operated by several universities and organizations. Most of them are actively used for a variety of experimental works that are needed by uncounted educational curricula and aerodynamics related researches. Lately, wind tunnels have even become increasingly accepted as one of common engineering tools in solving of unexpected and abundant wind engineering problems that are continually facing automotive industries, oil and gas companies, as well as governmental agencies and ministries. This paper is meant to present an overview of the existing wind tunnels, accompanied with information on some important technical data, and added, to a lesser extent, with complementary information about backgrounds and design philosophies. The emphasis is, however, given only to those with test section size of 1.0 square meter or larger. From the general point of view, some information about testing capabilities and trends in wind tunnel technology is also presented.

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3

Hrúz, Michal, Pavol Pecho, and Martin Bugaj. "Design procedure and honeycomb screen implementation to the air transtport department’s subsonic wind tunnel." AEROjournal 16, no. 2 (2020): 3–8. http://dx.doi.org/10.26552/aer.c.2020.2.1.

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Wind tunnels are the most widely used tools when comes to validation of Reynold number. Most of wind tunnels use various air straighteners or flow conditioners to achieve as most unified air flow as it’s possible. This article deals with design and creation procedure of air flow straightener – honeycomb screen. Based on mathematical relations and empirical experience defines dimensions and characteristics for subsonic wind tunnel of the Air Transport Department of University of Žilina. Wind tunnel equipped with a suitable screen provides more relevant and accurate data, which are crucial for final validation of results of test objects.

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4

Wolf, T. "Improvement and modernization of subsonic wind tunnels." Journal of Aircraft 30, no. 1 (January 1993): 57–63. http://dx.doi.org/10.2514/3.46305.

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5

Krajček Nikolić, Karolina, Anita Domitrović, and Slobodan Janković. "Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel." PROMET - Traffic&Transportation 30, no. 4 (September 10, 2018): 457–63. http://dx.doi.org/10.7307/ptt.v30i4.2685.

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To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.

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6

Wiriadidjaja, Surjatin, Azmin Shakrine Mohd Rafie, Fairuz Izzuddin Romli, and Omar Kassim Ariff. "Aerodynamic Interference Correction Methods Case: Subsonic Closed Wind Tunnels." Applied Mechanics and Materials 225 (November 2012): 60–66. http://dx.doi.org/10.4028/www.scientific.net/amm.225.60.

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The approach to problems of wall interference in wind tunnel testing is generally based on the so-called classical method, which covers the wall interference experienced by a simple small model or the neo-classical method that contains some improvements as such that it can be applied to larger models. Both methods are analytical techniques offering solutions of the subsonic potential equation of the wall interference flow field. Since an accurate description of wind tunnel test data is only possible if the wall interference phenomena are fully understood, uncounted subsequent efforts have been spent by many researchers to improve the limitation of the classical methods by applying new techniques and advanced methods. However, the problem of wall interference has remained a lasting concern to aerodynamicists and it continues to be a field of active research until the present. The main objective of this paper is to present an improved classical method of the wall interference assessment in rectangular subsonic wind tunnel with solid-walls.

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7

Ghorbanian, Kaveh, Mohammad Reza Soltani, and Mojtaba Dehghan Manshadi. "Experimental investigation on turbulence intensity reduction in subsonic wind tunnels." Aerospace Science and Technology 15, no. 2 (March 2011): 137–47. http://dx.doi.org/10.1016/j.ast.2010.06.009.

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8

Gorbushin, Anton Roaldovich. "AIR HUMIDITY EFFECT ON FLOW PARAMETERS IN SUBSONIC AND TRANSONIC WIND TUNNELS." TsAGI Science Journal 49, no. 1 (2018): 1–12. http://dx.doi.org/10.1615/tsagiscij.2018026783.

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9

Starikov, O. Yu. "The study of the induction of subsonic wind tunnels with an axisymmetric working part." Fluid Dynamics 20, no. 1 (1985): 130–33. http://dx.doi.org/10.1007/bf01097375.

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10

Meyer, O., W. Nitsche, and I. Futterer. "Numerical and experimental investigations on the reduction of wind tunnel wall interference by means of adaptive slots." Aeronautical Journal 105, no. 1052 (October 2001): 571–80. http://dx.doi.org/10.1017/s0001924000012513.

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Abstract The flow in many wind tunnel experiments is affected by the presence of test section walls. The resulting interference can be minimised by correcting the measured model pressures, or by influencing the model flow directly with the use of ventilated or adaptive test section walls. The objective behind the latter technique is to guide the flow in the test section to achieve low interference (i.e. free flow) condition at the model. The most successful technique of flexible, adaptive walls is still restricted to small research wind tunnels due to its mechanical complexity. However, a very promising alternative is the use of adaptive slots in the test section walls. This concept combines the method of passive slotted walls, as they are already implemented in many large wind tunnels, and flexible walls. Additionally, this technique presents the opportunity of full 3D adaptations because the slots can be situated in all four test section walls. This paper presents preliminary experimental results and the latest numerical calculations on the effectiveness of adaptive slots. The experiments were conducted under high subsonic flow conditions in the new slotted test section of the transonic wind tunnel at TU Berlin’s Aeronautical Institute (ILR). The numerical results presented are focussed on the 2D slot adaptation of a 2D-model (CAST7 aerofoil) and the 3D slot adaptation of a body of revolution (3D-ETB). In addition, basic studies were made of the flows associated with a single slot on one wall and a bump on the other. The numerical and the first experimental investigations have shown the potential of adaptive slots to reduce wall interferences effectively. The adaptation accuracy of the investigated slot configurations deviated not more than 3% from the reference case (2D-wall adaptation).

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11

Chikitkin, Aleksandr, Mikhail Petrov, Roman Dushkov, and Ernest Shifrin. "Aerodynamic Design of a Laval Nozzle for Real Gas Using Hodograph Method." Aerospace 5, no. 3 (September 10, 2018): 96. http://dx.doi.org/10.3390/aerospace5030096.

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We propose an approach for the design of the subsonic part of plane and axisymmetric Laval nozzles for real gases. The proposed approach is based on the hodograph method and allows one to solve the inverse design problem directly. Real gas effects are taken into consideration using the chemical equilibrium model. We present nozzle contours computed with the proposed method for a stoichiometric methane-air mixture. Results confirm that real gas effects have a strong influence on the nozzle shape. The described method can be used in the design of nozzles for rocket engines and for high-enthalpy wind tunnels.

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12

Ristic, Slavica. "A - a view in the invisible." Theoretical and Applied Mechanics 40, no. 1 (2013): 87–119. http://dx.doi.org/10.2298/tam1301087r.

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Flow visualization is an important topic in, experimental and computational fluid dynamics and has been the subject of research for many years. This paper presents an overview of flow visualization techniques. The physical basis and applications of different visualization methods for subsonic, transonic and supersonic flow in wind and water tunnels are described: direct injection methods, (smoke, dye, fog and different small particles), gas and hydrogen bubbles, , flow visualization by tufts, oil, liquid crystals, pressure and temperature sensitive paints, shadow, schlieren, interferometry, Laser Doppler Anemometry, Particle Image Velocimetry and other special techniques. Almost all presented photos have been recorded during tests in laboratories of MTI Belgrade.

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13

Mena, Jesús Garicano, Raffaele Pepe, Andrea Lani, and Herman Deconinck. "Assessment of Heat Flux Prediction Capabilities of Residual Distribution Method: Application to Atmospheric Entry Problems." Communications in Computational Physics 17, no. 3 (March 2015): 682–702. http://dx.doi.org/10.4208/cicp.070414.211114a.

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AbstractIn the present contribution we evaluate the heat flux prediction capabilities of second-order accurate Residual Distribution (RD) methods in the context of atmospheric (re-)entry problems around blunt bodies. Our departing point is the computation of subsonic air flows (with air modeled either as an inert ideal gas or as chemically reacting and possibly out of thermal equilibrium gas mixture) around probe-like geometries, as those typically employed into high enthalpy wind tunnels. We confirm the agreement between the solutions obtained with the RD method and the solutions computed with other Finite Volume (FV) based codes.However, a straightforward application of the same numerical technique to hypersonic cases involving strong shocks exhibits severe deficiencies even on a geometry as simple as a 2D cylinder. In an attempt to mitigate this problem, we derive new variants of RD schemes. A comparison of these alternative strategies against established ones allows us to derive a diagnose for the shortcomings observed in the traditional RD schemes.

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14

Sahu, Rishabh Kumar, Saurabh Sharma, and Vivek Swaroop Vishal Kumar. "Experimental Investigations and Computational Analysis on Subsonic Wind Tunnel." International Journal of Trend in Scientific Research and Development Volume-3, Issue-3 (April 30, 2019): 1708–11. http://dx.doi.org/10.31142/ijtsrd23511.

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15

Florin, MUNTEANU, OPREAN Corneliu, and STOICA Corneliu. "INCAS SUBSONIC WIND TUNNEL." INCAS BULLETIN 1, no. 1 (September 24, 2009): 12–14. http://dx.doi.org/10.13111/2066-8201.2009.1.1.3.

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16

Wu, Lian Sheng, Guang Li Li, and Qi Fu. "The Study of Design and Installation Process for Supersonic Nozzle." Advanced Materials Research 569 (September 2012): 500–503. http://dx.doi.org/10.4028/www.scientific.net/amr.569.500.

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A practical optimal design method of supersonic nozzle is proposed for a supersonic wind tunnel’s design. Design a set of nozzle wall lines with the same nozzle length and different Mach numbers 1.5, 2.0, 2.5. Use numerical simulation method for the verify and analysis of the designed nozzle. Mainly study the impact of the installation gradient between nozzle and test section on flow field quality. This wind tunnel is the subsonic, transonic and supersonic wind tunnel and its test section cross is 0.2 m × 0.2 m .The impact on flow field quality of the test section was studied quantitatively by using the numerical simulation method. The installation gradient index was given. It has some practical value to the construction of supersonic wind tunnel. At present, this study has been applied in construction of the wind tunnel. The gradient of the test section import shall not be greater than 0.5 mm.

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17

Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel, and V. Gollnick. "Wind tunnel testing of additive manufactured aircraft components." Rapid Prototyping Journal 24, no. 5 (July 9, 2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

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Purpose This paper aims to report on the physical distortions associated with the use of additive manufactured components for wind tunnel testing and procedures adopted to correct for them. Design/methodology/approach Wings of a joined-wing test aircraft configuration were fabricated with additive manufacturing and tested in a subsonic closed-loop wind tunnel. Wing deflections were observed during testing and quantified using image-processing procedures. These quantified deflections were then incorporated into numerical simulations and results had agreed with wind tunnel measurement results. Findings Additive manufacturing provides cost-effective wing components for wind tunnel test components with fast turn-around time. They can be used with confidence if the wing deflections could be accounted for systematically and accurately, especially at the region of aerodynamic stall. Research limitations/implications Significant wing flutter and unsteady deflections were encountered at higher test velocities and pitch angles. This reduced the accuracy in which the wing deflections could be corrected. Additionally, wing twists could not be quantified as effectively because of camera perspectives. Originality/value This paper shows that additive manufacturing can be used to fabricate aircraft test components with satisfactory strength and quantifiable deflections for wind tunnel testing, especially when the designs are significantly complex and thin.

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18

Yu, Li, Bin Bin Lv, Hong Tao Guo, Yu Yan, Xing Hua Yang, and Jian Guo Luo. "Research on Transonic Wind Tunnel Flutter Test for a Wing Model." Advanced Materials Research 1006-1007 (August 2014): 26–29. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.26.

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This paper adopts self-designed wing model to conduct flutter test on subsonic and transonic, and obtains flutter characteristic of the model, and the test results are used for calibration and verification of flutter procedures. The sub-critical extrapolation is used to obtain the flutter sub-critical parameters and the direct observation method is used to obtain comparison of results. Error of results obtained by the two approaches does not exceed 5%, and validates reliability of the sub-critical prediction approach in continuous adjusted dynamic pressure flutter test.

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19

Koreanschi, A., O. Sugar-Gabor, and R. M. Botez. "Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing." Aeronautical Journal 120, no. 1227 (May 2016): 757–95. http://dx.doi.org/10.1017/aer.2016.30.

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ABSTRACTAn experimental validation of an optimised wing geometry in the Price-Païdoussis subsonic wind tunnel is presented. Two wing models were manufactured using optimised glass fibre composite and tested at three speeds and various angle-of-attack. These wing models were constructed based on the original aerofoil shape of the ATR 42 aircraft and an optimised version of the same aerofoil for a flight condition of Mach number equal to 0.1 and angle-of-attack of 0°. The aerofoil's optimisation was realised using an ‘in-house’ genetic algorithm coupled with a cubic spline reconstruction routine, and was analysed using XFoil aerodynamic solver. The optimisation was concentrated on improving the laminar flow on the upper surface of the wing, between 10% and 70% of the chord. XFoil-predicted pressure distributions were compared with experimental data obtained in the wind tunnel. The transition position was estimated from the experimental pressure data using a second derivative methodology and was compared with the transition predicted by XFoil code. The results have shown the agreement between numerical and experimental data. The wind-tunnel tests have shown that the improvement of the laminar flow of the optimised wing is higher than the value predicted numerically.

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20

Carlin, G. J., and D. Bevan. "Prediction of subsonic wind tunnel mounting system interference." Journal of Aircraft 24, no. 5 (May 1987): 317–21. http://dx.doi.org/10.2514/3.45447.

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21

Collins, S. W., B. W. Westra, J. C. Lin, G. S. Jones, and C. H. Zeune. "Wind tunnel testing of powered lift, all-wing STOL model." Aeronautical Journal 113, no. 1140 (February 2009): 129–37. http://dx.doi.org/10.1017/s0001924000002840.

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Abstract Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximising efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14ft by 22ft Subsonic Wind Tunnel. The test’s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.

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Reis, M. L. C. C., O. A. F. Mello, and M. Chisaki. "UNCERTAINTY IN STATIC PRESSURE CORRECTION IN A SUBSONIC WIND TUNNEL." Revista de Engenharia Térmica 3, no. 2 (December 31, 2004): 122. http://dx.doi.org/10.5380/reterm.v3i2.3533.

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The static pressure p on the subsonic Wind Tunnel of the Aerodynamic Testing Laboratory of the Institute of Aeronautics and Space IAE, Aerospace Technical Center CTA, is measured using an absolute pressure sensor, located on the upper test section wall. This measurement is not taken at the same location as the one where the model is mounted during the actual wind tunnel test. This fact raises the need for a correction during data reduction. The identification and evaluation of the associated error source is important because the static pressure is an input quantity for the calculation of the total pressure pt, Mach number M and density ρ during the test. The present paper is concerned with the determination of the relationship between the static pressure measured on the tunnels upper wall and that at the model location, and with the analysis of the uncertainty propagation for the measured flow parameters.

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23

M. Saad, Magedi Moh, and Norzelawati Asmuin. "Determine Aerodynamic Characteristics for FX63-137 Aerofoil by Using Subsonic Wind Tunnel." Applied Mechanics and Materials 695 (November 2014): 651–54. http://dx.doi.org/10.4028/www.scientific.net/amm.695.651.

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This paper is primarily concentrated with determining aerodynamic characteristics and choosing the best angle of attack at a maximum lift and low drag for the FX 63-137 aerofoil at a low Reynolds number and a speed of 20m/s and 30m/s, by using subsonic wind tunnel through manufacturing the aerofoil by aluminum alloy using a CNC machine. The proposed methodology is divided into several stages. Firstly, manufacturing the aerofoil using an aluminum alloy. Secondly, the testing process is carried out using subsonic wind tunnel. Thirdly, the results are displayed and compared with results produced from related works, in order to find out the best angle of attack at a maximum lift.

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Idris, Imam Maulana. "RANCANG BANGUN TEROWONGAN ANGIN (WIND TUNNEL) TIPE SUBSONIC DENGAN TEST SECTION 0,2 X 0,2 M UNTUK ALAT PERAGA MEKANIKA FLUIDA." Mechonversio: Mechanical Engineering Journal 2, no. 2 (December 18, 2019): 19. http://dx.doi.org/10.51804/mmej.v2i2.614.

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Wind tunnel merupakan suatu alat yang berfungsi untuk mengetahui suatu kondisi udara yang mengenai benda padat. wind tunnel sering digunakan dalam berbagai bidang seperti aerodinamika, teknik, dan fisika, melalui bidang bidang tersebut terowongan angin memegang peranan penting. Karena di labolatorium teknik mesin belum mempunyai wind tunnel, padahal peranannya sangat dibutuhkan untuk penelitian mahasiswa. Tujuan yang ingin di capai dalam rancang bangun ini adalah sebagai alat penunjang praktikum di labolatorium Universitas Ma’arif Hasyim Latief dalam bidang ilmu aerodinamika ataupun dalam perkembangan dunia otomotif dengan menyesuaikan dengan wind tunnel yang sudah pernah dibuat dan memenuhi standart. Rancang bangun ini menghasilkan wind tunnel tipe subsonic dengan test section 0,2 X 0,2m yang mempunyai ukuran keseluruan 2,42m X 0,61m X 1,11m, dengan panjang Test Section 0,452m, Diffuser 0,909m, Contraction 0,508m, Hanycome 0,096m, dan wind tunnel yang telah dibuat dapat bekerja dengan baik.

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Daneshmand, Saeed, A. Ahmadi Nadooshan, and C. Aghanajafi. "Evaluation of FDM Rapid Prototyping with ABSi Material for Airfoil Design." Materials Science Forum 594 (August 2008): 249–54. http://dx.doi.org/10.4028/www.scientific.net/msf.594.249.

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For faster new product introduction aerospace companies are interested in reducing the time it takes to make wind tunnel models. The increased capability of rapid prototyping technologies has made them attractive for this purpose. An experimental study was done of rapid prototyping technology and their ability to make components for wind tunnel models in a timely and cost effective manner. This paper discusses the application of wing-body-tail configuration constructed using fused deposition method (FDM) for Subsonic and transonic wind tunnel testing. An experimental study was undertaken comparing a rapid prototyping model constructed of FDM Technologies using ABSi (Acrylonitrile butadiene styrene) to that of a standard machined steel model. Testing covered the Mach range of Mach 0.3 to Mach 1.3 at an angle-of-attack range of + 4° to +26° at zero sideslip and at angle of-sideslip ranges from –10 to +10 degrees at 16 degrees angle-of-attack.. Results from this study show relatively good agreement between the two models. It can be concluded that FDM model show promise in preliminary aerodynamic development studies and reduction in time and cost.

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Batill, Stephen M., and Joseph J. Hoffman. "Aerodynamic design of three-dimensional subsonic wind tunnel inlets." AIAA Journal 24, no. 2 (February 1986): 268–69. http://dx.doi.org/10.2514/3.9255.

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Rtishcheva, A. S. "Development of air exchanging system for subsonic wind tunnel." Journal of Physics: Conference Series 1128 (November 2018): 012135. http://dx.doi.org/10.1088/1742-6596/1128/1/012135.

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Rtishcheva, A. S. "Calculations of air cooler for new subsonic wind tunnel." Journal of Physics: Conference Series 891 (November 10, 2017): 012042. http://dx.doi.org/10.1088/1742-6596/891/1/012042.

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Pavlenko, Kaprilevskaya, Kozlov, and Katasonov. "Investigation of the Flow behind the Roughness Element on the UAV Surface at a Favorable Pressure Gradient." Siberian Journal of Physics 15, no. 2 (2020): 61–72. http://dx.doi.org/10.25205/2541-9447-2020-15-2-61-72.

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In a wind tunnel of low subsonic speeds, an experimental study was conducted of the windward flow of a trapezoidal model of a flying wing (UAV) with a locally installed perturbation generator in the region of maximum susceptibility on its surface. The generator was a three-dimensional roughness element whose height was comparable to the thickness of the boundary layer. The uniqueness of the work was that the experiments were carried out in a wind tunnel at real flight Reynolds numbers on a UAV model at a scale of 1:1. The results of visualization of the flow near a smooth surface and behind roughness were obtained using the method of liquid crystal thermography. The internal structure and processes of development of the longitudinal perturbation behind the roughness downstream were studied in detail using the thermoanemometry method.

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Jelínek, Tomáš, Erik Flídr, Martin Němec, and Jan Šimák. "Test Facility for High-Speed Probe Calibration." EPJ Web of Conferences 213 (2019): 02033. http://dx.doi.org/10.1051/epjconf/201921302033.

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A new test facility was built up as a part of a closed-loop transonic wind tunnel in VZLU´s High-speed Aerodynamics Department. The wind tunnel is driven by a twelve stage radial compressor and Mach and Reynolds numbers can be changed by the compressor speed and by the total pressure in the wind tunnel loop by a set of vacuum pumps, respectively. The facility consists of an axisymmetric subsonic nozzle with an exit diameter de = 100 mm. The subsonic nozzle is designed for regimes up to M = 1 at the nozzle outlet. At the nozzle inlet there is a set of a honeycomb and screens to ensure the flow stream laminar at the outlet of the nozzle. The subsonic nozzle can be supplemented with a transonic slotted nozzle or a supersonic rigid nozzle for transonic and supersonic outlet Mach numbers. The probe is fixed in a probe manipulator situated downstream of the nozzle and it ensures a set of two perpendicular angles in a wide range (±90°). The outlet flow field was measured through in several axial distances downstream the subsonic nozzle outlet. The total pressure and static pressure was measured in the centreline and the total pressure distribution in the vertical and horizontal plane was measured as well. Total pressure fluctuations in the nozzle centreline were detected by a FRAP probe. From the initial flow measurement in a wide range of Mach numbers the best location for probe calibration was chosen. The flow field was found to be suitable for probe calibration.

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Tang, Xin Zi, Xu Zhang, Rui Tao Peng, and Xiong Wei Liu. "Wind Tunnel Experimental Study of Wind Turbine Airfoil Aerodynamic Characteristics." Applied Mechanics and Materials 260-261 (December 2012): 125–29. http://dx.doi.org/10.4028/www.scientific.net/amm.260-261.125.

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High lift and low drag are desirable for wind turbine blade airfoils. The performance of a high lift airfoil at high Reynolds number (Re) for large wind turbine blades is different from that at low Re number for small wind turbine blades. This paper investigates the performance of a high lift airfoil DU93-W-210 at high Re number in low Re number flows through wind tunnel testing. A series of low speed wind tunnel tests were conducted in a subsonic low turbulence closed return wind tunnel at the Re number from 2×105to 5×105. The results show that the maximum lift, minimum drag and stall angle differ at different Re numbers. Prior to the onset of stall, the lift coefficient increases linearly and the slope of the lift coefficient curve is larger at a higher Re number, the drag coefficient goes up gradually as angle of attack increases for these low Re numbers, meanwhile the stall angle moves from 14° to 12° while the Re number changes from 2×105to 5×105.

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32

Sanz, J. M., E. R. McFarland, N. L. Sanger, T. F. Gelder, and R. H. Cavicchi. "Design and Performance of a Fixed, Nonaccelerating Guide Vane Cascade That Operates Over an Inlet Flow Angle Range of 60 Deg." Journal of Engineering for Gas Turbines and Power 107, no. 2 (April 1, 1985): 477–84. http://dx.doi.org/10.1115/1.3239753.

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A unique set of wind tunnel guide vanes are designed with an inverse design code and analyzed with a panel method and an integral boundary layer code developed at the NASA Lewis Research Center. The fixed guide vanes, 80 ft long with 6-ft chord length, were designed for the NASA Ames 40 × 80/80 × 120 ft Wind Tunnel. Low subsonic flow is accepted over a 60 deg range of inlet angle from either the 40 × 80 leg or the 80 × 120 leg of the wind tunnel, and directed axially into the main leg of the tunnel where drive fans are located. Experimental tests of 1/10-scale models were conducted to verify design calculations.

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33

Kovalev, M. A., and A. N. Nikitin. "Choosing the aerodynamic configuration of a subsonic cruise missile." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 3 (October 31, 2019): 59–66. http://dx.doi.org/10.18287/2541-7533-2019-18-3-59-66.

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The paper presents a comparison of two aerodynamic configurations of subsonic cruise missiles, characterized by the use of swept-back and forward-swept wings. The results of wind tunnel tests with the use of an automated measurement system characterizing the dependence of the lift and drag coefficients in a sufficiently wide range of angles of attack are presented. This allows us to compare the aerodynamic quality of the cruise missile models under investigation. The analysis of the results of experiments with the models and calculations in conditions of steady-state low-altitude horizontal flight revealed that the configurations of cruise missiles with a moderately swept wing, selected for comparison, have similar aerodynamic characteristics. Both configurations ensure the mode of flight at a given altitude and velocity in the range of the best angles of attack (maximum aerodynamic quality). Missiles with swept-back wings have better aerodynamic performance in terms of maximum aerodynamic quality, while the lift increment due to reduced trim losses for the forward-swept wing configuration only partially compensates the difference of the aerodynamic characteristics of the alternatives under consideration. Therefore, it is concluded that the choice of aerodynamic configuration of a subsonic cruise missile with a swept-back wing is preferable.

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34

Hanifudin, Muhamad. "ANALISA DISTRIBUSI KECEPATAN ALIRAN OPEN CIRCUIT TYPE SUBSONIC WIND TUNNEL MENGGUNAKAN PIPA PITOT DENGAN PEMBACAAN SENSOR TEKANAN MPXV7002DP." Mechonversio: Mechanical Engineering Journal 2, no. 2 (December 18, 2019): 57. http://dx.doi.org/10.51804/mmej.v2i2.619.

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Tuntutan memiliki wind tunnel semakin tinggi di mana wind tunnel bermanfaat untuk mahasiswa teknik yang akan mengadakan penelitian lanjutan yang berkenaan dengan gaya-gaya aerodinamis (drag, lift, side), fenomena aliran udara ataupun tentang pengembangan terowongan angin itu sendiri. Atas dasar tersebut kami bermaksud merancang dan membangun wind tunnel.Sebelum wind tunnel dapat dipakai untuk pengujian gaya-gaya terhadap benda, diperlukan pengujian distribusi kecepatan aliran udara pada wind tunnel. Pengujian distribusi kecepatan aliran wind tunnel biasanya dilakukan dengan menggunakan pipa pitot pembacaan manometer pipa U. Untuk mendapatkan hasil pengukuran yang lebih akurat dan cepat maka pembacaan tekanan diganti dengan sensor tekanan dikombinasikan dengan arduino. Sehingga data yang diperoleh nantinya akan bisa dikonversi otomatis menjadi kecepatan aliran dengan menggunakan program arduino. Setelah dilakukan penelitian pengukuran kecepatan aliran udara dengan menggunakan pipa pitot dan sensor tekanan MPXV7002DP dikombinasikan Arduino hasilnya lebih cepat dan lebih akurat karena dapat mengukur kecepatan yang lebih rendah dibanding manometer pipa U yaitu 2.55 m/s dibanding 4.031 m/s . Akan tetapi jangkauan maksimalya tidak setinggi manometer pipa U karena hanya ternyata hanya mampu membaca kecepatan lebih dari 2.55 m/s sampai 57.64 m/s. Sedangkan manometer pipa U dapat membaca kecepatan lebih dari 57.64 m/s. Hasil pengujian kecepatan aliran udara pada wind tunnel didapatkan bahwa kececepatan minimal aliran udara yang melewati test section adalah 11.81 m/s sedangkan kececepatan maksimal aliran udara yang melewati test section adalah 12.72 m/s. Distribusi kecepatan aliran udara Open Circuit Type Subsonic Wind Tunnel dapat dikatakan seragam tapi belum baik karena setelah diuji dengan Peta I-MR kecepatan aliran masih melewati batas kontrol.

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35

Yaman, Kemal. "Subsonic Flutter of Cantilever Rectangular PC Plate Structure." International Journal of Aerospace Engineering 2016 (2016): 1–10. http://dx.doi.org/10.1155/2016/9212364.

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Flutter characteristics of cantilever rectangular flexible plate structure under incompressible flow regime are investigated by comparing the results of commercial flutter analysis program ZAERO©with wind tunnel tests conducted in Ankara Wind Tunnel (ART). A rectangular polycarbonate (PC) plate, 5 × 125 × 1000 mm in dimension, is used for both numerical and experimental investigations. Analysis and test results are very compatible with each other. A comparison between two different solution methods (g-methodandk-method) of ZAERO©is also done. It is seen that thek-methodgives a closer result than the other one. However,g-method results are on a conservative side and it is better to use conservative results, namely,g-method results. Even if the modal analysis results are used for the flutter analysis for this simple structure, a modal test should be conducted in order to validate the modal analysis results to have accurate flutter analysis results for more complicated structures.

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KHAN, Md Akhtar, and Chinmaya PADHY. "Aerodynamic and Experimental Analysis of Bio-mimic corrugated dragonfly aerofoil." INCAS BULLETIN 12, no. 2 (June 5, 2020): 73–85. http://dx.doi.org/10.13111/2066-8201.2020.12.2.7.

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In this work, experimental and computational approach is used to understand the corrugation attitude of a bio-inspired dragonfly mimicked corrugated airfoil at low Reynolds number varying from 15000 to 75000 to understand the advantages of pleated corrugated airfoil. The CFD analysis is carried out on the 2-dimensional bio-mimetic corrugated ‘Pantala flavescens’ dragonfly forewing to predict the aerodynamic characteristics of the corrugated dragonfly aerofoil with varying angle of attack from 0° to 8°. The computational analysis of the wing profile is done using the ANSYS-19 ICEM CFD and FLUENT software. For the experimental test, the model is printed in 3-D printer machine and tested in subsonic Wind Tunnel at different speeds and different angle of attacks using a wind tunnel 6-component balance. The computational simulation reveals the exemplary results of the pleated airfoil (corrugated aerofoil) with new design constraints. Finally, the computational result is validated with experimental results.

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Salvador, Mikael William. "Definition of a Subsonic Wind Tunnel Exhauster for Automotive Tests." International Journal for Research in Applied Science and Engineering Technology 7, no. 7 (July 31, 2019): 1102–10. http://dx.doi.org/10.22214/ijraset.2019.7178.

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Kai, Daiki, Hiroki Sugiura, and Asei Tezuka. "Magnetic Suspension and Balance System for High-Subsonic Wind Tunnel." AIAA Journal 57, no. 6 (June 2019): 2489–95. http://dx.doi.org/10.2514/1.j057679.

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Manoj Veetil et al.,, Manoj Veetil et al ,. "Test Section Blockage Corrections for Subsonic Open-Circuit Wind Tunnel." International Journal of Mechanical and Production Engineering Research and Development 9, no. 2 (2019): 645–48. http://dx.doi.org/10.24247/ijmperdapr201964.

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40

Dragoş, L. "Subsonic flow past a thin airfoil in a wind tunnel." Mechanics Research Communications 18, no. 2-3 (March 1991): 129–34. http://dx.doi.org/10.1016/0093-6413(91)90041-t.

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41

Jadeja, Ajaysinh. "Conceptual Design, Analysis, and Fabrication of Subsonic Vertical Wind Tunnel." International Journal for Research in Applied Science and Engineering Technology 9, no. 3 (March 31, 2021): 1352–61. http://dx.doi.org/10.22214/ijraset.2021.33441.

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42

Hung, Nguyen Manh, and Hoang Thi Bich Ngoc. "Experimental study of laminar separation phenomenon combining with numerical calculations." Vietnam Journal of Mechanics 33, no. 2 (June 10, 2011): 95–104. http://dx.doi.org/10.15625/0866-7136/33/2/41.

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The separation is much more sensitive for laminar flow than for turbulent flow. These remarks have been attested for both subsonic and supersonic flows. However, they are not applicable to transonic flows when there are interactions between boundary layer and shock wave. Along with the Reynolds number, the Mach number is a necessary dimensionless parameter for the condition and the mechanism of separations. The report presents one part of studies on laminar separation with Mach number of incompressible flow. The laminar regimes correspond to flows through wind turbine blades. Our experimental work for laminar separation phenomenon was carried out in a subsonic open circuit wind tunnel by taking photographs. The accuracy of experimental results basically depends on the accuracy of wind tunnel and the quality of smoke on density and constitutive materials. Experimental results permit to determine the position of separation and the form of turbulent region followed from the separation point. Numerical studies were simultaneously realized. Based on obtained experimental and numerical results, the report presents also the comparison between the laminar separation and the turbulent separation.

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43

Srivastava, Ankur, and Andrew J. Meade. "Use of Active Learning to Design Wind Tunnel Runs for Unsteady Cavity Pressure Measurements." International Journal of Aerospace Engineering 2014 (2014): 1–11. http://dx.doi.org/10.1155/2014/218710.

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Wind tunnel tests to measure unsteady cavity flow pressure measurements can be expensive, lengthy, and tedious. In this work, the feasibility of an active machine learning technique to design wind tunnel runs using proxy data is tested. The proposed active learning scheme used scattered data approximation in conjunction with uncertainty sampling (US). We applied the proposed intelligent sampling strategy in characterizing cavity flow classes at subsonic and transonic speeds and demonstrated that the scheme has better classification accuracies, using fewer training points, than a passive Latin Hypercube Sampling (LHS) strategy.

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44

Nordin, Normayati, Zainal Ambri Abdul Karim, Safiah Othman, and Vijay R. Raghavan. "Design and Development of Low Subsonic Wind Tunnel for Turning Diffuser Application." Advanced Materials Research 614-615 (December 2012): 586–91. http://dx.doi.org/10.4028/www.scientific.net/amr.614-615.586.

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In practice, it is basically difficult even with controlled measurement environment to acquire a steady, uniform and fully developed flow. The flow entering diffuser was severely distorted despite a sufficient hydrodynamic entrance length already introduced. This was mainly due to the imperfect joining of duct and the abrupt change of the inlet cross-section applied. In this study, several basic features of a low subsonic wind tunnel, i.e. a centrifugal blower with 3-phase inverter, a settling chamber, screens and a contraction cone, are designed and developed for a turning diffuser application in order to improve the flow quality. The flow profiles are examined using Pitot static probe at five measurement points within the range of inflow Reynolds number, Rein= 5.786E+04-1.775E+05. The steady, uniform and fully developed turbulent flow profiles with an average deviation with theory of about 3.5% are obtained. This proves that a good flow quality could be produced by means of incorporating some basic features of a low subsonic wind tunnel to the system.

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45

Falcão Filho, João B. P., and Marcos A. Ortega. "Numerical Study of the Injection Process in a Transonic Wind Tunnel—Part I: The Design Point." Journal of Fluids Engineering 129, no. 6 (December 5, 2006): 682–94. http://dx.doi.org/10.1115/1.2734236.

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Injectors are to be installed in a transonic wind tunnel with the ultimate objective of expanding the Reynolds number envelope. The aim of this research effort is to numerically simulate the steady mixing process involving the supersonic jets and the tunnel subsonic main stream. A three-dimensional, Reynolds-averaged Navier–Stokes numerical code was developed following the main lines of the finite-difference diagonal algorithm, and turbulence effects are accounted for through the use of the Spalart and Allmaras one-equation scheme. This paper focuses on the “design point” of the tunnel, which establishes (among other specifications) that the static pressures of both streams at the entrance of the injection chamber are equal. Three points are worth noting. The first is related to the numerical strategy that was introduced in order to mimic the real physical process in the entire circuit of the tunnel. The second corresponds to the solution per se of the three-dimensional mixing between several supersonic streams and the subsonic main flow. The third is the calculation of the “engineering” parameters, that is, the injection loss factor, gain, and efficiency. Many interesting physical aspects are discussed, and among them, the formation of three-dimensional shocks’ and expansions’ “domes”

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46

Malmuth, N. D. "An asymptotic theory of wind-tunnel-wall interference on subsonic slender bodies." Journal of Fluid Mechanics 177 (April 1987): 19–35. http://dx.doi.org/10.1017/s0022112087000831.

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An asymptotic theory of solid cylindrical wind-tunnel-wall interference about subsonic slender bodies has been developed. The basic approximation used is one of large wall-radius to body-length ratio. Matched asymptotic expansions show that in contrast to the analogous two-dimensional problem of a confined airfoil, three regions exist. Besides the incompressible crossflow and nearly axisymmetric zones, a wall layer exists where reflection in the wall of the line source representing the body becomes of dominant importance. From the theory, the interference pressures are shown to be approximately constant for closed bodies. Also demonstrated is that D'Alembert's paradox holds for interference drag of such shapes. Numerical studies comparing the exact theory to the asymptotic model which provides drastic simplifications, show that the latter can be used with reasonable accuracy to describe flows, even where the characteristic tunnel-radius to body-length ratio is as low as 1.5.

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47

Giardino, Frank, and Joana Rocha. "Design and Characterization of a High-Speed Subsonic Aeroacoustic Wind Tunnel." Journal of Aircraft 56, no. 1 (January 2019): 108–20. http://dx.doi.org/10.2514/1.c035113.

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48

Bragg, Michael B., and Abdollah Khodadoust. "Study of the droplet spray characteristics of a subsonic wind tunnel." Journal of Aircraft 32, no. 1 (January 1995): 199–204. http://dx.doi.org/10.2514/3.46701.

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49

Calautit, John Kaiser, Hassam Nasarullah Chaudhry, Ben Richard Hughes, and Lik Fang Sim. "A validated design methodology for a closed-loop subsonic wind tunnel." Journal of Wind Engineering and Industrial Aerodynamics 125 (February 2014): 180–94. http://dx.doi.org/10.1016/j.jweia.2013.12.010.

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50

Dinca, Liviu, and Jenica Ileana Corcau. "A prototype for airflow speed control in a subsonic wind tunnel." IEEE Aerospace and Electronic Systems Magazine 29, no. 2 (February 2014): 14–21. http://dx.doi.org/10.1109/maes.2014.120131.

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