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Journal articles on the topic 'Trailing edge flaps'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

Dalli, Uğbreve;ur, and Şcedilefaatdin Yüksel. "Identification of Flap Motion Parameters for Vibration Reduction in Helicopter Rotors with Multiple Active Trailing Edge Flaps." Shock and Vibration 18, no. 5 (2011): 727–45. http://dx.doi.org/10.1155/2011/675791.

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An active control method utilizing the multiple trailing edge flap configuration for rotorcraft vibration suppression and blade loads control is presented. A comprehensive model for rotor blade with active trailing edge flaps is used to calculate the vibration characteristics, natural frequencies and mode shapes of any complex composite helicopter rotor blade. A computer program is developed to calculate the system response, rotor blade root forces and moments under aerodynamic forcing conditions. Rotor blade system response is calculated using the proposed solution method and the developed pr

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2

Jia, Ya Lei, Zhong He Han, Fu You Li, Ya Kai Bai, and Ji Xuan Wang. "Influence of Flap Deflection Angle on Wind Turbine Airfoil with Trailing Edge Flaps." Advanced Materials Research 977 (June 2014): 222–27. http://dx.doi.org/10.4028/www.scientific.net/amr.977.222.

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To improve the ability of capturing the wind energy of wind turbine and shorten the design period is of great importance to designing wind turbine blade. The article established S809 airfoil model with trailing edge flaps, The gap of the frontal subject and trailing edge flap adopt uniform gap structure, this structure will reduce the influence of the gap on aerodynamic characteristics.Using the k-ω Two equation turbulence model , the article calculated aerodynamic performance of S809 with 10% chord length trailing edge flaps under different deflecting angles. Results show that gap between the

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3

Moriarty, J. A., and E. O. Tuck. "Thin aerofoils with high-incidence flaps or blunt trailing edges." Aeronautical Journal 93, no. 923 (1989): 93–99. http://dx.doi.org/10.1017/s0001924000016857.

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SummaryThe method of matched asymptotic expansions is used to calculate the lift for a class of thin aerofoils with highincidence flaps or blunt trailing edges. The analysis is based on smallness of the ratio between the flap length (or trailingedge thickness) and the chord of the main foil. Results are compared with exact solutions for bent plates and for triangular and quadrilateral bodies. A procedure for extension to general trailing-edge configurations, including detached flaps, is outlined.

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4

Pan, Lin, Ze Zhu, Zhaoyang Shi, and Leichong Wang. "Modeling and Investigation of Blade Trailing Edge of Vertical Axis Offshore Wind Turbine." Sustainability 13, no. 19 (2021): 10905. http://dx.doi.org/10.3390/su131910905.

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In this study, the structure of the trailing edge of the vertical axis offshore wind turbine blade is modified. First, according to the method of parameterization, the offshore wind turbine model is established, and a series of characteristics of the offshore wind turbine are obtained. Second, we add flaps with different lengths to the trailing edge of NACA0021 airfoil to obtain different dynamic characteristics. The angle of the additional trailing edge flaps is modified. Finally, a simulation model for the modified airfoil of the vertical axis offshore wind turbine is reestablished, and the

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5

Richter, K., and H. Rosemann. "Experimental investigation of trailing-edge devices at transonic speeds." Aeronautical Journal 106, no. 1058 (2002): 185–93. http://dx.doi.org/10.1017/s0001924000012987.

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AbstractThe influence of trailing-edge devices such as Gurney flaps and divergent trailing edges of different height on the aerodynamic performance of an aerofoil at transonic speeds has been investigated experimentally. The investigation has been carried out in the Transonic Wind Tunnel Göttingen (TWG) using the two-dimensional aerofoil model VC-Opt at freestream Mach numbers of M ε [0.755, 0.775, 0.790] and a Reynolds number of Re = 5.0 x 106.The results have shown that the trailing-edge devices increase the circulation of the aerofoil leading to a lift enhancement and pitching-moment decrea

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6

Saxena, Anand, and Inderjit Chopra. "Wind Tunnel Testing of a Swashplateless Rotor with Compact Brushless Motor Actuated Flaps for Primary Control." Journal of the American Helicopter Society 65, no. 1 (2020): 1–6. http://dx.doi.org/10.4050/jahs.65.012010.

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A swashplateless rotor trim using brushless DC motor actuated trailing edge flaps was achieved in the Glenn L. Martin wind tunnel. A 6-ft-diameter, four-bladed articulated rotor with motor–flap system integrated into the NACA 0012 airfoil section was fabricated. A Maxon EC-10 brushless DC motor as an on-blade actuator and a lightweight mechanism were incorporated to actuate the trailing edge flap. The rotor torsion frequency was lowered to 2/rev using soft pitch links, allowing the blade pitch response to a trailing edge flap input. A closed-loop controller was employed to ensure trailing edge

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7

Brown, L., and A. Filippone. "Aerofoil at low speeds with Gurney flaps." Aeronautical Journal 107, no. 1075 (2003): 539–46. http://dx.doi.org/10.1017/s0001924000013427.

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This paper reviews the research on Gurney flaps and related high lift trailing edge devices. It investigates aerofoil performances at Reynolds numbers Re ≅ 105 and below, both with the clean configuration and various Gurney flap sizes. The device height is optimised, and a semi-empirical formula linking flap height to free stream speed and aerofoil chord is proposed. The analysis shows that the optimal size of the device is always below the boundary-layer thickness at the trailing edge. Discussion of results includes analysis of hysteresis loops occurring in the L/D performances. These are mos

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8

Lendraitis, Martynas. "Investigation of performance gains on a sailplane with morphing wing trailing edge." Mechanics 25, no. 4 (2019): 299–303. http://dx.doi.org/10.5755/j01.mech.25.4.22325.

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Increasing the performance of a modern sailplane is challenging. Most of the known valid approaches have already been applied in practice. Morphing technology, which could allow to adapt to various flight stages is yet to be applied. An investigation of possible flight performance benefits of such technology is carried out here. Using a genetic algorithm, a morphing trailing edge flap for airfoil HQ-17 is formed for -4° and +12° flap deflections. The performance is evaluated and compared with a regular flap, which shows that for the HQ-17 airfoil, drag could be reduced by up to 36% in comparis

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9

Shen, Jinwei, and Inderjit Chopra. "Swashplateless Helicopter Rotor with Trailing-Edge Flaps." Journal of Aircraft 41, no. 2 (2004): 208–14. http://dx.doi.org/10.2514/1.9279.

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10

LIM, IN-GYU, and IN LEE. "AEROELASTIC ANALYSIS OF BEARINGLESS ROTOR SYSTEMS WITH TRAILING EDGE FLAPS." Modern Physics Letters B 23, no. 03 (2009): 461–64. http://dx.doi.org/10.1142/s0217984909018655.

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An aeroelastic analysis of bearingless rotor systems with trailing edge flaps was conducted using large deflection-type beam theory for forward flight conditions with a focus on reducing vibration while minimizing control effort. The aerodynamic forces of the rotor blade were calculated using two-dimensional quasi-steady strip theory. For the analysis of forward flight, the nonlinear periodic blade steady response was obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim. The objective function, which includes vibratory hub loads

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11

Bloy, A. W., N. Tsioumanis, and N. T. Mellor. "Enhanced Aerofoil Performance Using Small Trailing-Edge Flaps." Journal of Aircraft 34, no. 4 (1997): 569–71. http://dx.doi.org/10.2514/2.2210.

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12

Frederick, M., E. C. Kerrigan, and J. M. R. Graham. "Gust alleviation using rapidly deployed trailing-edge flaps." Journal of Wind Engineering and Industrial Aerodynamics 98, no. 12 (2010): 712–23. http://dx.doi.org/10.1016/j.jweia.2010.06.005.

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13

Buhl, Thomas, Mac Gaunaa, and Christian Bak. "Potential Load Reduction Using Airfoils with Variable Trailing Edge Geometry." Journal of Solar Energy Engineering 127, no. 4 (2005): 503–16. http://dx.doi.org/10.1115/1.2037094.

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This paper presents an investigation of the potential for reduction of fluctuating loads on wind turbine blades with the use of flaplike deflectable trailing edges. More specifically, the aeroelastic response of an elastically mounted airfoil section with a deflectable trailing edge is investigated. This is done by coupling a model for the aerodynamic forces on a deforming airfoil with a linear spring/damper model for the elastic deformation of a rigid airfoil to which the forces associated with the deflection of the trailing edge are added. The analysis showed that when the airfoil experience

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14

Guo, Peng, Xing Jun Hu, and Jun Yuan Zhang. "Drag Reduction on the 35° Slant Angle Ahmed Reference Body Using Flaps." Applied Mechanics and Materials 668-669 (October 2014): 156–59. http://dx.doi.org/10.4028/www.scientific.net/amm.668-669.156.

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Based on computational fluid dynamics numerical simulation methods, this article studied the changes of resistance characteristics and tail pressure distribution on the 35° slant angle Ahmed model after installing the rear flaps. The results show that the appropriate size and reasonable arrangement of flaps can make the model tail separated airflow attach on the flap and the flap trailing edge separate again, narrow the tail separation zones, improve the model tail pressure, reduce the pressure difference on the forepart and rear model,lower the model resistance, then causing the drag reductio

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15

Jain, Shubham, Nekkanti Sitaram, and Sriram Krishnaswamy. "Computational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics." International Scholarly Research Notices 2015 (January 14, 2015): 1–11. http://dx.doi.org/10.1155/2015/402358.

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The present study comprises steady state, two-dimensional computational investigations performed on NACA 0012 airfoil to analyze the effect of Gurney flap (GF) on airfoil aerodynamics using k-ε RNG turbulence model of FLUENT. Airfoil with GF is analyzed for six different heights from 0.5% to 4% of the chord length, seven positions from 0% to 20% of the chord length from the trailing edge, and seven mounting angles from 30° to 120° with the chord. Computed values of lift and drag coefficients with angle of attack are compared with experimental values and good agreement is found at low angles of

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16

Bernhammer, Lars O., Roeland De Breuker, and Moti Karpel. "Energy harvesting for actuators and sensors using free-floating flaps." Journal of Intelligent Material Systems and Structures 28, no. 2 (2016): 163–77. http://dx.doi.org/10.1177/1045389x16645954.

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A novel configuration of an energy harvester for local actuation and sensing devices using limit cycle oscillations has been modeled, designed and tested. A wing section has been designed with two trailing-edge free-floating flaps. A free-floating flap is a flap that can freely rotate around a hinge axis and is driven by trailing edge tabs. In the rotational axis of each flap a generator is mounted that converts the vibrational energy into electricity. It has been demonstrated numerically how a simple electronic system can be used to keep such a system at stable limit cycle oscillations by var

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17

Zhang, Zhu, Wei Dong Yang, and Da Lin Yang. "Piezoelectric Actuators Used for Helicopter Vibration Reduction." Advanced Materials Research 718-720 (July 2013): 1729–33. http://dx.doi.org/10.4028/www.scientific.net/amr.718-720.1729.

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This paper covers the development of two piezoelectric actuators for trailing edge flap control on mach scaled model helicopter rotors. The design, analysis and bench tests of these two actuators are described. Under different voltages and frequencies, their drive performances are tested and compared. Results showed that these two actuators all can effectively drive and control the flaps with each advantages and disadvantages.

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18

Kizhakke Kodakkattu, Saijal, Prabhakaran Nair, and Joy M.L. "Design optimization of helicopter rotor using kriging." Aircraft Engineering and Aerospace Technology 90, no. 6 (2018): 937–45. http://dx.doi.org/10.1108/aeat-12-2016-0250.

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Purpose The purpose of this study is to obtain optimum locations, peak deflection and chord of the twin trailing-edge flaps and optimum torsional stiffness of the helicopter rotor blade to minimize the vibration in the rotor hub with minimum requirement of flap control power. Design/methodology/approach Kriging metamodel with three-level five variable orthogonal array-based data points is used to decouple the optimization problem and actual aeroelastic analysis. Findings Some very good design solutions are obtained using this model. The best design point in minimizing vibration gives about 81

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19

Hernandez, Gloria, Richard M. Wood, and Robert E. Collins. "Leading- and trailing-edge flaps on supersonic delta wings." Journal of Aircraft 27, no. 2 (1990): 158–62. http://dx.doi.org/10.2514/3.45912.

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20

Lee, T., and P. Gerontakos. "Unsteady Airfoil with Dynamic Leading- and Trailing-Edge Flaps." Journal of Aircraft 46, no. 3 (2009): 1076–81. http://dx.doi.org/10.2514/1.42431.

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21

Moore, F. G., and T. C. Hymer. "Semiempirical Method for Predicting Aerodynamics of Trailing-Edge Flaps." Journal of Spacecraft and Rockets 40, no. 1 (2003): 39–48. http://dx.doi.org/10.2514/2.3913.

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22

Oltmann, Nils-Christan, Dorit Sobotta, and Arndt Hoffmann. "Load reduction of wind turbines using trailing edge flaps." Energy Procedia 136 (October 2017): 176–81. http://dx.doi.org/10.1016/j.egypro.2017.10.316.

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23

Lim, In-Gyu, and In Lee. "Aeroelastic analysis of rotor systems using trailing edge flaps." Journal of Sound and Vibration 321, no. 3-5 (2009): 525–36. http://dx.doi.org/10.1016/j.jsv.2008.10.029.

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24

Dehaeze, F., K. D. Baverstock, and G. N. Barakos. "CFD simulation of flapped rotors." Aeronautical Journal 119, no. 1222 (2015): 1561–83. http://dx.doi.org/10.1017/s0001924000011404.

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AbstractThe use of active trailing edge flaps on rotors may lead to performance benefits as well as noise and vibration reduction. In this work, computational fluid dynamics, using the HMB2 solver, is used to assess the effect of the trailing edge flaps on the whole flight domain of a modern main rotor. Starting from a baseline blade design, multiple techniques are demonstrated. The flap is first assessed using 2D pitching aerofoil simulations, followed by dMdt simulations, that account for the simultaneous variations of pitch and Mach around the azimuth. It was shown that enhanced lift was ob

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25

Jost, Eva, Annette Fischer, Galih Bangga, Thorsten Lutz, and Ewald Krämer. "An investigation of unsteady 3-D effects on trailing edge flaps." Wind Energy Science 2, no. 1 (2017): 241–56. http://dx.doi.org/10.5194/wes-2-241-2017.

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Abstract. The present study investigates the impact of unsteady 3-D aerodynamic effects on a wind turbine blade with trailing edge flap by means of computational fluid dynamics (CFD). Harmonic oscillations are simulated on the DTU 10 MW rotor with a morphing flap of 10 % chord extent ranging from 70 to 80 % blade radius. The deflection frequency is varied in the range between 1 and 6 p. To quantify 3-D effects, rotor simulations are compared to 2-D airfoil computations and the 2-D theory by Theodorsen. It was found that the deflection of the flap on the 3-D rotor causes a complex wake developm

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26

Miyata, Katsuhiro, and Kenichi Rinoie. "Estimation of Take-Off Performance for Supersonic Transport with Leading-Edge Vortex Flaps and Trailing-Edge Flaps." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51, no. 593 (2003): 327–29. http://dx.doi.org/10.2322/jjsass.51.327.

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27

LAUK, Peep, Karl-Erik SEEGEL, and Toivo TÄHEMAA. "IMPACT OF VARIABLE GEOMETRY MINIFLAPS ON SAILPLANE FLIGHT CHARACTERISTICS." Aviation 21, no. 4 (2017): 119–25. http://dx.doi.org/10.3846/16487788.2017.1415228.

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Miniflaps (also known as mini-TED, active Gurnay flaps, etc.) located at the wing trailing edge enable to increase wing lift and reduce the aerodynamic drag. Variable geometry miniflaps (VGMF) elaborated at the Estonian Aviation Academy enable to expand the wing area up to 6.5%, when extended, and, at the same time, deflect 16.7 degrees downwards. The use of VGMF is especially promising for reducing the airspeed and sink speed of modern high wing loading sailplanes flying in thermals. The VGMFs were built in cooperation with the Lithuanian company JSC “Sportine Aviacija ir Ko”. They were fixed

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28

Hao, Li-Shu, and Yong-Wei Gao. "Effect of Gurney Flap Geometry on a S809 Airfoil." International Journal of Aerospace Engineering 2019 (July 18, 2019): 1–8. http://dx.doi.org/10.1155/2019/9875968.

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In this paper, the effect of Gurney flap shapes on wind turbine blade airfoil S809 has been studied by numerical simulation. First, the O-type grid is used in the numerical simulation. By comparing with experimental data, such as the lift force, the drag coefficient, and the pressure distribution, the accuracy of the simulation method is validated. Second, the research on the widths of three kinds of rectangular Gurney flaps at the trailing edge of the S809 airfoil is carried out. Rectangular Gurney flaps can considerably increase the lift in both the linear and nonlinear sections, and the max

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29

Milgram, Judah, and Inderjit Chopra. "A Parametric Design Study for Actively Controlled Trailing Edge Flaps." Journal of the American Helicopter Society 43, no. 2 (1998): 110. http://dx.doi.org/10.4050/jahs.43.110.

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30

Falls, Jaye, Anubhav Datta, and Inderjit Chopra. "Integrated Trailing-Edge Flaps and Servotabs for Helicopter Primary Control." Journal of the American Helicopter Society 55, no. 3 (2010): 32005–3200515. http://dx.doi.org/10.4050/jahs.55.032005.

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31

Ravichandran, Kumar, Inderjit Chopra, Brian E. Wake, and Benjamin Hein. "Trailing-Edge Flaps for Rotor Performance Enhancement and Vibration Reduction." Journal of the American Helicopter Society 58, no. 2 (2013): 1–13. http://dx.doi.org/10.4050/jahs.58.022006.

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32

Yonaga, Ryuji, Masahide Hatano, and Toshihiko Okamoto. "Smoke Tunnel Flow Visualization Study on Miniature Trailing-Edge Flaps." Journal of the Visualization Society of Japan 18, Supplement1 (1998): 157–60. http://dx.doi.org/10.3154/jvs.18.supplement1_157.

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33

Maurice, J. B., F. A. King, W. Fichter, A. Rabourdin, and P. K. Konstanzer. "Helicopter Rotor In-Plane Stability Enhancement Using Trailing-Edge Flaps." Journal of Guidance, Control, and Dynamics 36, no. 5 (2013): 1477–89. http://dx.doi.org/10.2514/1.57323.

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34

Centolanza, Louis R., Edward C. Smith, and Brian Munsky. "Induced-shear piezoelectric actuators for rotor blade trailing edge flaps." Smart Materials and Structures 11, no. 1 (2002): 24–35. http://dx.doi.org/10.1088/0964-1726/11/1/303.

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35

SPENCER, MICHAEL G., ROBERT M. SANNER, and INDERJIT CHOPRA. "Adaptive Neurocontrol of Simulated Rotor Vibrations Using Trailing Edge Flaps." Journal of Intelligent Material Systems and Structures 10, no. 11 (1999): 855–71. http://dx.doi.org/10.1106/rx0w-uj7m-qel9-e58p.

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36

Spencer, Michael G., Robert M. Sanner, and Inderjit Chopra. "Adaptive Neurocontrol of Simulated Rotor Vibrations Using Trailing Edge Flaps." Journal of Intelligent Material Systems and Structures 10, no. 11 (1999): 855–71. http://dx.doi.org/10.1106/rxow-uj7m-qel9-e58p.

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37

Lim, In-Gyu, and In Lee. "Aeroelastic Characteri stics of Rotor Blades with Trailing Edge Flaps." International Journal of Aeronautical and Space Sciences 8, no. 1 (2007): 115–21. http://dx.doi.org/10.5139/ijass.2007.8.1.115.

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38

Jost, E., A. Fischer, T. Lutz, and E. Krämer. "An investigation of unsteady 3D effects on trailing edge flaps." Journal of Physics: Conference Series 753 (September 2016): 022009. http://dx.doi.org/10.1088/1742-6596/753/2/022009.

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39

Tuck, E. O. "Thin airfoils with small trailing-edge flaps at arbitrary angles." Journal of the Australian Mathematical Society. Series B. Applied Mathematics 29, no. 2 (1987): 142–55. http://dx.doi.org/10.1017/s0334270000005695.

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AbstractThe method of matched asymptotic expanisions is used to solve the problem of flow over a thin airfoil possessing a trailing-edge appendage, which may be of a general character, but is confined to a region of small size compated to the airfoil' chord. A feature of this asymptotic solution is effective de-coupling of the flow problems for the main airfoil and the flap. The special case of an attached flat flap set at an arbitrary angle is solved in detail.

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40

David, M. Jimreeves, R. N. Govardhan, and J. H. Arakeri. "Thrust generation from pitching foils with flexible trailing edge flaps." Journal of Fluid Mechanics 828 (August 31, 2017): 70–103. http://dx.doi.org/10.1017/jfm.2017.491.

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In the present experimental study, we investigate thrust production from a pitching flexible foil in a uniform flow. The flexible foils studied comprise a rigid foil in the front (chord length $c_{R}$) that is pitched sinusoidally at a frequency $f$, with a flexible flap of length $c_{F}$ and flexural rigidity $EI$ attached to its trailing edge. We investigate thrust generation for a range of flexural rigidities ($EI$) and flap length to total chord ratio ($c_{F}/c$), with the mean thrust ($\overline{C_{T}}$) and the efficiency of thrust generation ($\unicode[STIX]{x1D702}$) being directly mea

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41

Sekula, Martin K., and Matthew L. Wilbur. "Analysis of a Multiflap Control System for a Swashplateless Rotor." Journal of the American Helicopter Society 57, no. 3 (2012): 1–12. http://dx.doi.org/10.4050/jahs.57.032006.

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An analytical study was conducted examining the feasibility of a swashplateless rotor controlled through two trailing-edge flaps (TEFs), where the cyclic and collective controls were provided by separate TEFs. This analysis included a parametric study examining the impact of various design parameters on TEF deflections. Blade pitch bearing stiffness; blade pitch index; and flap chord, span, location, and control function of the inboard and outboard flaps were systematically varied on a utility-class rotorcraft trimmed in steady level flight. Gradient-based optimizations minimizing flap deflect

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42

Hardy, B. C., and S. P. Fiddes. "Prediction of vortex lift of non-planar wings by the leading-edge suction analogy." Aeronautical Journal 92, no. 914 (1988): 154–64. http://dx.doi.org/10.1017/s0001924000025562.

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SummaryA three-dimensional panel method has been used to calculate edge-suction forces for thin sharp-edged wings in incompressible flow. The suction forces have been used to estimate the vortex lift on the wings by means of the leading-edge suction analogy due to Polhamus.The results for planar wings are in acceptable agreement with other methods based on the suction analogy. A limited comparison with results from experiments for non-planar wings revealed good prediction of lift and drag increments associated with the deflection of leading and trailing edge flaps for ‘conventional’ wings of h

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43

Jeffrey, David, Xin Zhang, and David W. Hurst. "Some Aspects of the Aerodynamics of Gurney Flaps on a Double-Element Wing." Journal of Fluids Engineering 123, no. 1 (2000): 99–104. http://dx.doi.org/10.1115/1.1334376.

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Gurney flaps of different heights have been fitted to a generic double-element wing, and the effects at two typical flap angles have been observed using force and pressure measurements, and by performing flow surveys using Laser Doppler Anemometry. At a low flap setting angle of 20 deg the suction-surface flow remains attached to the trailing edge of the flap, and vortex flow features and perturbation velocities are all similar to those observed when Gurney flaps are fitted to single element wings. At a high flap deflection of 50 deg there is an extensive region of separated flow over the flap

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44

Baldo, L., J. M. Cejudo Ruiz, and M. D. L. Dalla Vedova. "Novel active control technique of aircraft flaps asymmetry." Journal of Physics: Conference Series 2526, no. 1 (2023): 012004. http://dx.doi.org/10.1088/1742-6596/2526/1/012004.

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Abstract This paper proposes an active monitoring strategy to control aircraft trailing-edge high-lift devices (flaps) asymmetry. A variety of system failures can cause asymmetry in the control surfaces, including the transmission torsion bar break down and control surface actuator wear and tear. The authors’ novel asymmetry active monitoring approach detects and identifies flaps position asymmetry. Once the failure side has been identified, the active control activates the wingtip brakes to stop the uncontrolled flap surface. The still controlled flaps are driven to the damaged surface brakin

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45

Singh, B. K., and B. C. Basu. "A numerical model for analysis of thin wings in inviscid incompressible flow." Aeronautical Journal 91, no. 907 (1987): 333–37. http://dx.doi.org/10.1017/s000192400002145x.

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Summary A planar vortex sheet model for analysis of thin wings in inviscid incompressible flow is presented. In this model a network of spanwise quadratically varying semi-infinite doublet sheets is introduced which produces a continuous trailing vortex wake. The present method has been applied to wings fitted with partial span trailing edge flaps after appropriate modification to account for the flap juncture. Also, the problem of wings in sideslip is attempted by incorporating the zero load condition at the down stream wing tip. The comparison of results shows that the proposed model retains

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46

Reiswich, Artur, Max Finster, Martin Heinrich, and Rüdiger Schwarze. "Effect of Flexible Flaps on Lift and Drag of Laminar Profile Flow." Energies 13, no. 5 (2020): 1077. http://dx.doi.org/10.3390/en13051077.

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Experiments with elastic flaps applied on a common airfoil profile were performed to investigate positive effects on lift and drag coefficients. An NACA0020 profile was mounted on a force balance and placed in a wind tunnel. Elastic flaps were attached in rows at different positions on the upper profile surface. The Reynolds number of the flow based on the chord length of the profile is about 2 × 10 5 . The angle of attack is varied to identify the pre- and post-stall effects of the flaps. Polar diagrams are presented for different flap configurations to compare the effects of the flaps. The r

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47

Patidar, Vijay, and Sudhir Joshi. "Numerical analysis of stagger Supersonic biplane at off-design condition with trailing edge flap." FME Transactions 51, no. 2 (2023): 253–61. http://dx.doi.org/10.5937/fme2302253p.

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Supersonic biplanes can achieve low-boom and low-drag supersonic flights. In the present study, aerodynamic analysis of a two-dimensional stagger Bussmann biplane (staggered upper element by 0.5c) at zero degrees angle of attack with trailing edge flap was investigated with the help of computational fluid dynamics (CFD) tools. Due to the wave cancellation effect, the Busemann biplane delivers a positive drag reduction at design supersonic Mach values. However, when operating outside of its intended parameters, it performs worse, and the wave cancellation effect has no beneficial effects on red

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Allaei, Daryoush, Benjamin Reydel, and James Rall. "High Lift Device Modifications for Reducing Airport Noise - A Review." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (2021): 635–40. http://dx.doi.org/10.3397/in-2021-1610.

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Aircraft noise has been one of the top environmental issues at and near airports across the country because of its negative impact on communities. The growth of the nation's air transportation system is restricted predominantly due to regulations on limiting aircraft noise generated around airports. Reducing aircraft noise will lead to wider community acceptance of new or larger airports, lower airline operating costs by reducing noise quota fees, and increase air traffic growth through operating more flights. One of the most significant contributors to aircraft noise, structural vibrations ca

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49

Milgram, Judah, Inderjit Chopra, and Friedrich Straub. "Rotors with Trailing Edge Flaps: Analysis and Comparison with Experimental Data." Journal of the American Helicopter Society 43, no. 4 (1998): 319–32. http://dx.doi.org/10.4050/jahs.43.319.

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Straub, Friedrich K., and Bruce D. Charles. "Aeroelastic Analysis of Rotors with Trailing Edge Flaps Using Comprehensive Codes." Journal of the American Helicopter Society 46, no. 3 (2001): 192. http://dx.doi.org/10.4050/jahs.46.192.

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