Relevant bibliographies by topics / Grid Fin Aerodynamics

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Grid Fin Aerodynamics'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Grid Fin Aerodynamics"

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Chen, Jian Zhong, and Pei Qing Liu. "Test Technique Research for the Hinge Moment of a Grid Fin in High Speed Wind Tunnel." Applied Mechanics and Materials 574 (July 2014): 480–84. http://dx.doi.org/10.4028/www.scientific.net/amm.574.480.

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In order to study the test technique for the hinge moment of a grid fin in wind tunnel, a platform based on half model support technique was established in FL-23 and FL-31 wind tunnel in China Aerodynamics Research & Development Center (CARDC). The platform developed a wind tunnel test balance, rudder control system and the aerodynamics measurement system. This test technique was important to optimize aerodynamic configurations of a grid fin, design or evaluate the capability of the rudder control system. Nomenclature
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Liu, Yuanchun, Zhi-xun Xia, and Jun Liu. "Numerical simulation of aerodynamic characteristics and heating for grid fin missiles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 7 (May 24, 2018): 2368–77. http://dx.doi.org/10.1177/0954410018778790.

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A grid fin is an unconventional missile control surface comprising an outer frame supporting an inner grid of lifting surfaces. Although the topic of grid fin aerodynamics has been studied by many researchers, only a few have considered aerodynamic heating, generating a high-quality structured grid that remains to be a difficult task. An effective method of grid partition and an aerodynamic prediction method to simulate the viscous flow fields of grid-fin configurations at supersonic Mach numbers have been developed. Multi-block and H-O-type grid treatments are developed for complex grid fin configurations. The viscous flow over a tail-controlled missile with grid fins at a Mach number of 2.5 and several angles of attack is calculated using computational fluid dynamics. Additionally, the heat flux distribution of grid fins is investigated, and the effects of shock wave interaction on heat flux are analyzed. The numerical results show good agreement with the measured data, and confirm that this method is an effective way to numerically simulate viscous grid fin flow fields. Furthermore, the aerodynamic heating results show that, because the peak heat flux on the shock wave interaction region is lower than that on the leading edge of the grid fin, it does not affect the thermal protection of the grid fin.
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Tripathi, Manish, Mahesh M. Sucheendran, and Ajay Misra. "Experimental analysis of cell pattern on grid fin aerodynamics in subsonic flow." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 3 (September 5, 2019): 537–62. http://dx.doi.org/10.1177/0954410019872349.

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Grid fins consisting of a lattice of high aspect ratio planar members encompassed by an outer frame are unconventional control surfaces used on numerous missiles and bombs due to their enhanced lifting characteristics at high angles of attack and across wider Mach number regimes. The current paper accomplishes and compares the effect of different grid fin patterns on subsonic flow aerodynamics of grid fins by virtue of the determination of their respective aerodynamic forces. Furthermore, this study deliberates the impact of gap variation on aerodynamics of different patterns. Results enunciate enhanced aerodynamic efficiency, and lift slope for web-fin cells and single diamond patterns compared to the baseline model. Moreover, the study indicates improved aerodynamic performance for diamond patterns with higher gaps by providing elevated maximum lift coefficient, delayed stall angle, and comparable drag at lower angles. The study established the presence of an additional effect termed as the inclination effect alongside the cascade effect leading to deviations with respect to lift, stall, and aerodynamic efficiency amongst different gap variants of the individual patterns. Thus, optimization based on the aerodynamic efficiency, stall angle requirements, and construction cost by optimum pattern and gap selection can be carried out through this analysis, which can lead to elevated aerodynamic performance for grid fins.
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Burkhalter, John E., and Harris M. Frank. "Grid Fin Aerodynamics for Missile Applications in Subsonic Flow." Journal of Spacecraft and Rockets 33, no. 1 (January 1996): 38–44. http://dx.doi.org/10.2514/3.55704.

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Dol, Sharul Sham. "Aerodynamics Analysis of Grid Fins Inner Lattice Structure in Cruise Missile." WSEAS TRANSACTIONS ON FLUID MECHANICS 16 (May 19, 2021): 92–101. http://dx.doi.org/10.37394/232013.2021.16.9.

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Grid fins are normally placed at the rear end of cruise missiles, rockets and other ballistic devices to control their trajectory especially at the final stage of flight. These fins provided fine control of the pitch, yaw and other lateral movements, allowing for higher stability and accuracy of the cruise missiles. This project investigates computationally the relation between grid fins inner lattice structures dimensionless parameters and the fins aerodynamics drag coefficient. The project gathered data from 12 different fins by varying the parameters of its internal lattice structure such as thickness, width and chord at various angles of attack (0°, 20° and 40°). The freestream was set at a constant speed of 150 m/s that gives Reynolds number > 1.7 x 106 . The results were experimentally compared by using a re-scaled model of a single fin in a sub-sonic wind tunnel, achieving a difference in results of not exceeding 6%. The results obtained that as the width-chord ratio increases, the aerodynamics drag coefficient increases for fixed thickness-width ratio. The results also demonstrated that as the angle of attack increases, the aerodynamics drag increases. The thickness-width ratio has the larger impact on the aerodynamics drag. The results can be used to improve the design of guided cruise missiles.
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Tripathi, M., M. M. Sucheendran, and A. Misra. "Effect of aspect ratio variation on subsonic aerodynamics of cascade type grid fin at different gap-to-chord ratios." Aeronautical Journal 124, no. 1274 (December 3, 2019): 472–98. http://dx.doi.org/10.1017/aer.2019.146.

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ABSTRACTThis paper dwells upon investigating the effect of aspect ratio (AR) variation on the aerodynamic performance of unconventional control surfaces called grid fins by virtue of a series of subsonic experiments on a simplified grid fin variant called the cascade fin. Wind tunnel tests were performed for different AR (variable span) grid fins. The same had been investigated for different gap-to-chord ratio (g/c) variants. Results demonstrated a tangible increase in the aerodynamic efficiency as well as stall angle reduction for higher AR. Moreover, higher AR leads to increased pitching moment, which emphasizes elevated hinge moment requirements. The study ensued the presence of higher deviation between the low AR fins, that is $AR<2$ compared to the pertinent deviations between the high AR fins, that is $AR\geq2$ . The effect associated with these variations was termed as span effect in this paper. It was established that, the deviations arising due to this phenomena were lesser for higher g/c and higher AR. The analysis of AR variation for different g/c presented a limiting value of AR reduction for stall performance enhancement. Thus, optimised selection of the g/c and AR values can lead to enhanced aerodynamic efficiency alongside an improved stalling characteristic.
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Burkhalter, John E., Roy J. Hartfield, and Todd M. Leleux. "Nonlinear aerodynamic analysis of grid fin configurations." Journal of Aircraft 32, no. 3 (May 1995): 547–54. http://dx.doi.org/10.2514/3.46754.

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Chen, S., M. Khalid, H. Xu, and F. Lesage. "An investigation of the grid fins as control surface devices for missiles." Aeronautical Journal 104, no. 1034 (April 2000): 183–90. http://dx.doi.org/10.1017/s0001924000028086.

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Abstract Recently, grid fins have been receiving increasing attention as a practical and efficient means of controlling missile trajectory. Preliminary studies at IAR have demonstrated that modern CFD methods can be used for computing flows past complex grid fin type configurations, and that these methods are more soundly physically based than the earlier vortex lattice and/or shock expansion methods. The current paper addresses the issue of the grid fin size, in terms of both the panel thickness and the frontal shape. The study covers three thicknesses for the grid fin panel, with front shapes having a simple blunt square face, as well as a sharp knife-edge shape. In addition, an important aspect of the present investigation is to quantify the aerodynamic effect of the ramp fairing installed immediately upstream of the blunt base upon which the grid fin assembly resides. A comparison of flow field characteristics and aerodynamic coefficients of the grid fin assembly, with and without the fairing ramp, would provide a direct means of evaluating the effect of the ramp. At this stage, the investigations are based on Euler calculations. The present study focuses on a standard grid fin configuration mounted on a generic cylindrical body.
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Theerthamalai, P., and M. Nagarathinam. "Aerodynamic Analysis of Grid-Fin Configurations at Supersonic Speeds." Journal of Spacecraft and Rockets 43, no. 4 (July 2006): 750–56. http://dx.doi.org/10.2514/1.16741.

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Salehi Paniagua, Keyvan, Pablo García-Fogeda, and Félix Arévalo. "Aeroelastic Stability of an Aerial Refueling Hose–Drogue System with Aerodynamic Grid Fins." Aerospace 10, no. 5 (May 18, 2023): 481. http://dx.doi.org/10.3390/aerospace10050481.

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In this work, the aeroelastic stability of an aerial refueling system is investigated. The system is formed by a classical hose and drogue, and the novelty of our work is the inclusion of a grid fin configuration to improve its stability. The unsteady aerodynamic forces on the grid fins are determined using the concept of a unit grid fin (UGF). For each UGF, the unsteady aerodynamic forces are computed using the Doublet-Lattice Method, and the forces on the complete grid fins are calculated using interfering factors obtained from wind tunnel measurements for the steady case. The static equilibrium position of the system influences the linearized perturbed unsteady motion of the ensemble. This effect, together with the phase lag angle introduced to account for the unsteady aerodynamic forces in the hose, makes the flutter computation of the complete system a non-typical one. The results show that, by adding the grid fins, the stability of the refueling system is improved, delaying or annulling flutter occurrence.
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Dissertations / Theses on the topic "Grid Fin Aerodynamics"

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Балалаєв, Антон Валерійович, and Anton Balalaiev. "Характеристики решітчастого дворядного робочого колеса вентилятора двоконтурного турбореактивного двигуна." Thesis, Національний авіаційний університет, 2021. https://er.nau.edu.ua/handle/NAU/48802.

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Дисертаційну роботу присвячено вирішенню науково-прикладної задачі підвищення ефективності дворядних лопаткових вінців вентиляторів двоконтурних турбореактивних двигунів шляхом застосування решітчастих дворядних робочих коліс. Вперше отримано характеристики решітчастого дворядного робочого колеса вентилятора ТРДД методом чисельного експерименту. Показано, що застосування решітчастих дворядних РК забезпечує підвищення ефективності вентилятора, збільшує його напірність. Ступінь підвищення тиску в діапазоні режимів обертання ротору від 2202…3010 об/хв збільшується до 10 % в порівнянні з дворядним РК. Представлено дослідження частотних характеристик власних коливань однорядної, еквівалентної дворядної та решітчастих дворядних лопаток робочих коліс вентилятора ТРДД. Показано, що застосування дворядних лопаток у дослідженому вентиляторі без перегородок недопустимо у зв’язку з наявністю власних форм коливань, де відбувається перетинання лопаток першого і другого ряду. Показано, що застосування решітчастих дворядних робочих лопаток дозволяє покращити жорсткість та забезпечити надійну роботу вентилятора. Удосконалено методику вибору параметрів решітчастого дворядного робочого колеса вентилятора ТРДД з урахуванням спектру частот власних коливань. Отримала подальший розвиток теорія дворядних лопаткових вінців в частині дослідження решітчастих дворядних лопаткових вінців з великим подовженням.
The thesis is devoted to solving the scientific and applied problem of increasing the efficiency of tandem blade rows of fans of turbofan engines by using grid tandem impellers. For the first time, the characteristics of a grid tandem impeller are obtained by the method of numerical experiment. It is shown that the use of grid tandem impellers provides an increase in the efficiency of the fan, increases its loading. The pressure ratio increases in the range of rotor rotation speed from 2202 ... 3010 rpm increases up to 10 % compared to a tandem impellers. Investigations of the frequency characteristics of natural vibrations of a singlerow, equivalent to tandem row and grid tandem blades of the turbofan engine fan impellers are presented. It is shown that the use of tandem blades in the investigated fan without partitions is unacceptable due to the presence of natural vibration modes, in which the blades of the first and second rows intersect. It is shown that the use of grid tandem rotor blades improves rigidity and ensures reliable operation of the fan. The technique for selecting the parameters of a grid tandem turbofan engine fan impeller has been improved, taking into account the spectrum of natural vibration frequencies. The theory of tandem blade rows was further developed in terms of the study of grid tandem blade rows with a large elongation.
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Theerthamalai, P. "Aerodynamic Analysis Of Grid Fins Using Analytical And Computational Methods." Thesis, 2007. http://hdl.handle.net/2005/563.

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Grid fins (lattice fins) are used as a lifting and control surface for highly manoeuvrable missiles. Grid fins also find their applications for air-launched submunitions. The main advantages are its low hinge moment requirement and good high angle of attack performance characteristics. Two dimensional analysis has been carried out using linear and shock-expansion theo- ries. The results indicate that above certain depth-to-height ratio, (called critical depth-to-height ratio,) the local normal force becomes negative due to shock reflection from the opposite side. Hence, depth (chord) for grid fin cell should not exceed a critical value. A prediction method has been developed for the estimation of aerodynamic character- istics of grid fin-body combinations at supersonic Mach numbers based on shock-expansion theory. Body upwash theory has been used for the effect of body; method of images has been used for carry-over forces onto the body. Empirical relation has been used for the modelling of separated body vortices and their effect on the leeward side fins. The method has been validated with experimental results for three configurations. The comparison is good for individual fin characteristics as well as overall characteristics for all the cases at higher supersonic Mach numbers. For lower supersonic Mach numbers at higher angles of attack, the prediction deviates from experiment. The reason for the deviation is due to shock detachment and shock reflection from opposite side, which is not modelled in the present method. Vortex lattice method has been used for prediction of linear aerodynamic character- istics of grid-fins at subsonic Mach numbers. Empirical relation based on trends from available experimental data has been used for the non-linear effect. The method has been validated with experimental results for several configurations without and with control surface deflections. The predicted aerodynamic characteristics compare well with experimental results for all the cases and the difference is within 15%. Based on the subsonic and supersonic analytical methods, a prediction code for the aerodynamic analysis of configuration with grid fins has been developed. Flow field computations inside isolated cells have been carried out using CFD code, PARAS-3D. Effects of depth-to-height ratio, web thickness, web leading edge angle and cell width-to-height ratio have been studied. Increase in thickness reduces the critical depth and increases the normal force. This increment in normal force is due to shock wave formation at the expansion side and its interaction with the opposite side. Effect of cell cross sectional shape has been studied using inviscid computation over isolated cells. Square, right triangular, equilateral triangular and hexagonal cross sections have been considered for this study. The normal force for square cell at zero roll is higher compared to 45 deg roll (diamond shape). Triangular cells show large variation in normal force with roll orientation due to large variation in projected area with roll angle. To compare the characteristics of different cross sectional cells, the normal force is normalised with respect to total internal web area. The comparison shows that the hexagonal cell gives maximum normal force and right triangular cell gives the minimum. Packaging efficiency of different cross sections is analysed by normalising the normal force with frontal area. The results show that triangular cells are preferred for packaging efficiency. Viscous flow computations over complete configuration have been carried out using FLUENT. GAMBIT has been used for geometry definition and grid generation. Hexahedral finite volumes are used to generate the grids including the nose region. Flow computations have been carried out at supersonic Mach numbers. To reduce the compu- tational time, Flow computations upto 0.5 calibre ahead of grid fin have been carried out with body-alone configuration. Flow over the fin-body section has been computed sep- arately taking the inlet pressure condition from the body-alone computed results. This procedure has reduced the grid size to around 1/5th and the computations converged faster due to imposition of converged solution at the pressure inlet. The computed results on the body show that the Flow separation occurs on the lee- ward side of the body and formation of separated vortices. The comparison of pressure distribution on the body with experiment is good. Flow computations over the fin-body section have been carried out at different Mach numbers and angles of attack. The computed normal force coefficient on the horizontal fin compares well with experimental data. Computations with fin deflection of -15 deg have also been carried out and the computed results are within 10% of the experimental data. Flow computations over another grid fin configuration have been carried out at dif- ferent roll angles. The comparison of individual fin force and overall normal force and pitching moment coefficients with experiment is good. The comparison demonstrates the capability of prediction methods as well as CFD in analysing aerodynamic performance of grid fin configurations.
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Book chapters on the topic "Grid Fin Aerodynamics"

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Tripathi, Manish, Mahesh M. Sucheendran, and Ajay Misra. "Effect of Chord Variation on Subsonic Aerodynamics of Grid Fins." In Lecture Notes in Mechanical Engineering, 105–28. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9601-8_8.

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Conference papers on the topic "Grid Fin Aerodynamics"

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Krishnamurthy, Ravindra, Nikhil Shende, and Balakrishnan Narayanarao. "CFD Simulation of grid fin flows." In 31st AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-3023.

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Burkhalter, John, and Harris Frank. "Non-linear aerodynamic analysis of grid fin configurations." In 13th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1894.

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Ma, MingSheng, Youqi Deng, Ming Zheng, and Naichun Zhou. "Navier-Stokes Computations for a Grid Fin Missile." In 23rd AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4973.

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Miller, Mark, and Wm Washington. "An experimental investigation of grid fin drag reduction techniques." In 12th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1914.

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Hughson, Montgomery, Eric Blades, and Gregg Abate. "Transonic Aerodynamic Analysis of Lattice Grid Tail Fin Missiles." In 24th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3651.

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Pruzan, Daniel, Michael Mendenhall, William Rose, and David Schuster. "Grid Fin Stabilization of the Orion Launch Abort Vehicle." In 29th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-3018.

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WASHINGTON, WM, PAMELA BOOTH, and MARK MILLER. "Curvature and leading edge sweep back effects on grid fin aerodynamic characteristics." In 11th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3480.

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Despeyroux, Antoine, Robert Desaulnier, Ryan Luciano, Michael Piotrowski, Jean-Pierre Hickey, Xiaohua Wu, Nicolas Hamel, and François Lesage. "Numerical analysis of static and dynamic performances of grid fin controlled missiles." In 32nd AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3285.

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Theerthamalai, P., S. Manisekaran, and M. Nagarathinam. "A Prediction Method for Aerodynamic Characterization of Grid-Fin Configurations at Supersonic Speeds." In 23rd AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4967.

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DeSpirito, James, and Jubaraj Sahu. "Viscous CFD calculations of grid fin missile aerodynamics in the supersonic flow regime." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-257.

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