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Journal articles on the topic 'Delta Wing Aerodynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 10 February 2022

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1

Keshav, R. "Aerodynamics of Reverse Delta Wing." International Journal for Research in Applied Science and Engineering Technology 9, no. VI (2021): 3398–403. http://dx.doi.org/10.22214/ijraset.2021.35618.

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Delta wings are mostly used in supersonic jets and fighter aircrafts. A delta wing is naturally stable and produces vortex lift, so the flow separation can be made into increasing lift. This augmented lift comes at an expense of high drag. A reverse delta wing is nothing but an inverted delta wing, the forward swept wings were inspired from this design. It has low drag coefficient and was used in ground effect vehicle. This paper aims to bring out all the possible studies and research work done on a reverse delta wing. The study was mainly inspired by the works of Alexander Lippisch and his de

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2

Gursul, I. "Recent developments in delta wing aerodynamics." Aeronautical Journal 108, no. 1087 (2004): 437–52. http://dx.doi.org/10.1017/s0001924000000269.

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Abstract Recent developments in delta wing aerodynamics are reviewed. For slender delta wings, recent investigations shed more light on the unsteady aspects of shear-layer structure, vortex core, breakdown and its instabilities. For nonslender delta wings, substantial differences in the structure of vortical flow and breakdown may exist. Vortex interactions are generic to both slender and nonslender wings. Various unsteady flow phenomena may cause buffeting of wings and fins, however, vortex breakdown, vortex shedding, and shear layer reattachment are the most dominant sources. Dynamic respons

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3

Viswanath, P. R., and S. R. Patil. "Aerodynamic characteristics of delta wing–body combinations at high angles of attack." Aeronautical Journal 98, no. 975 (1994): 159–70. http://dx.doi.org/10.1017/s0001924000049848.

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AbstractAn experimental study investigating the aerodynamic characteristics of generic delta wing-body combinations up to high angles of attack was carried out at a subsonic Mach number. Three delta wings having sharp leading edges and sweep angles of 50°, 60° and 70° were tested with two forebody configurations providing a variation of the nose fineness ratio. Measurements made included six-component forces and moments, limited static pressures on the wing lee-side and surface flow visualisation studies. The results showed symmetric flow features up to an incidence of about 25°, beyond which

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4

Muir, Rowan Eveline, Abel Arredondo-Galeana, and Ignazio Maria Viola. "The leading-edge vortex of swift wing-shaped delta wings." Royal Society Open Science 4, no. 8 (2017): 170077. http://dx.doi.org/10.1098/rsos.170077.

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Recent investigations on the aerodynamics of natural fliers have illuminated the significance of the leading-edge vortex (LEV) for lift generation in a variety of flight conditions. A well-documented example of an LEV is that generated by aircraft with highly swept, delta-shaped wings. While the wing aerodynamics of a manoeuvring aircraft, a bird gliding and a bird in flapping flight vary significantly, it is believed that this existing knowledge can serve to add understanding to the complex aerodynamics of natural fliers. In this investigation, a model non-slender delta-shaped wing with a sha

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5

Wang, Jinjun, and Yan Xu. "Experimental Studies on Control of Delta Wing Aerodynamics." AIAA Journal 42, no. 2 (2004): 403–5. http://dx.doi.org/10.2514/1.9101.

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6

Traub, Lance W., Brian Moeller, and Othon Rediniotis. "Low-Reynolds-Number Effects on Delta-Wing Aerodynamics." Journal of Aircraft 35, no. 4 (1998): 653–56. http://dx.doi.org/10.2514/2.2352.

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7

Grismer, Deborah S., Robert C. Nelson, and Wayne L. Ely. "Influence of sideslip on double delta wing aerodynamics." Journal of Aircraft 32, no. 2 (1995): 451–53. http://dx.doi.org/10.2514/3.46740.

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8

Mochizuki, Saya, and Gouji Yamada. "Aerodynamic characteristics and flow field of delta wings with the canard." MATEC Web of Conferences 145 (2018): 03010. http://dx.doi.org/10.1051/matecconf/201814503010.

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Now, many kinds of explorations for outer planets have been proposed around the world. Among them Mars attracts much attention for future exploration. Orbiters and landers have been used for Mars exploration. Recently as a new exploration method, the usage of an airplane has been seriously considered and there are some development projects for Mars airplane. However, the airplane flying on the Earth atmosphere cannot fly on the Mars atmosphere, because atmospheric conditions are much different each other. Therefore, we focused on the usage of the airplane with unfolding wings for Mars explorat

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9

SHI, ZHIWEI, and XIAO MING. "EXPERIMENTAL INVESTIGATION ON A PITCHING MOTION DELTA WING IN UNSTEADY FREE STREAM." Modern Physics Letters B 23, no. 03 (2009): 409–12. http://dx.doi.org/10.1142/s0217984909018527.

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As combat aircraft becomes more and more maneuverable, the need to understand the unsteady behavior of aircraft in dynamic flow fields becomes more important. Usually researchers pay more attention to the effects on the changes of AOA, but ignore the effects of velocity variations. It is known that the velocity of aircraft changes greatly when the aircraft undergoes a high angle of attack maneuver, like "cobra" maneuver. To completely simulate and study the effect of rapid changes in both free stream velocity and angle of attack, a pitching motion setup is developed in the unsteady wind tunnel

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10

Maria Viola, Ignazio, and Richard G. J. Flay. "Sail Aerodynamics: On-Water Pressure Measurements on a Downwind Sail." Journal of Ship Research 56, no. 04 (2012): 197–206. http://dx.doi.org/10.5957/jsr.2012.56.4.197.

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Pressures on three horizontal sections of a downwind sail were measured for several wind directions and sail trims. The pressure distributions were compared with wind tunnel tests; similarities and differences were found, the latter as a result of the dynamic effects, which were not modeled in the wind tunnel. A pressure distribution at the head of the spinnaker resembling that from a delta wing was measured at an apparent wind angle of 120°.

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11

Ericsson, Lars E. "Multifaceted Influence of Fuselage Geometry on Delta-Wing Aerodynamics." Journal of Aircraft 40, no. 1 (2003): 204–6. http://dx.doi.org/10.2514/2.3076.

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12

Wang, Zhi-Jin, Ping Jiang, and Ismet Gursul. "Effect of Thrust-Vectoring Jets on Delta Wing Aerodynamics." Journal of Aircraft 44, no. 6 (2007): 1877–88. http://dx.doi.org/10.2514/1.30568.

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13

Gupta, Gaurav, Pranav Tiwari, Bhanu Pratap Vatsa, Aashish Anand Sahay, K. S. Srikanth, and Shrikant Vidya. "Aerodynamics Characteristics of Compound Delta Wing at Sea Level." IOP Conference Series: Materials Science and Engineering 1149, no. 1 (2021): 012027. http://dx.doi.org/10.1088/1757-899x/1149/1/012027.

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14

Allan, M. R., K. J. Badcock, G. N. Barakos, and B. E. Richards. "Wind-Tunnel Interference Effects on Delta Wing Aerodynamics Computational Fluid Dynamics Investigation." Journal of Aircraft 42, no. 1 (2005): 189–98. http://dx.doi.org/10.2514/1.5324.

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15

Allan, M. R., K. J. Badcock, G. N. Barakos, and B. E. Richards. "Wind-tunnel interference effects on a 70° delta wing." Aeronautical Journal 108, no. 1088 (2004): 505–13. http://dx.doi.org/10.1017/s0001924000000336.

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Abstract This paper considers the effects of both wind-tunnel walls and a downstream support structure, on the aerodynamics of a 70° delta wing. A RANS model of the flow was used with the wind-tunnel walls and supports being modelled with inviscid wall boundary conditions. A consistent discretisation of the domain was employed such that grid dependence effects were consistent in all solutions, thus any differences occurring were due to varying boundary conditions (wall and support locations). Comparing solutions from wind-tunnel simulations and simulations with farfield conditions, it has been

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16

Jiang, Ping, Zhijing Wang, and Ismet Gursul. "Effects of Unsteady Trailing-Edge Blowing on Delta Wing Aerodynamics." Journal of Aircraft 47, no. 2 (2010): 591–602. http://dx.doi.org/10.2514/1.45890.

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17

YANIKTEPE, Bülent, Coşkun ÖZALP, and Çetin CANPOLAT. "Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform." Kahramanmaraş Sütçü İmam Üniversitesi Mühendislik Bilimleri Dergisi 19, no. 1 (2016): 1. http://dx.doi.org/10.17780/ksujes.86852.

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18

Ericsson, L. E., and H. H. C. King. "Effect of leading-edge geometry on delta wing unsteady aerodynamics." Journal of Aircraft 30, no. 5 (1993): 793–95. http://dx.doi.org/10.2514/3.46414.

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19

Hong, John S., Zeki Z. Celik, and Leonard Roberts. "Effects of leading-edge lateral blowing on delta wing aerodynamics." AIAA Journal 34, no. 12 (1996): 2471–78. http://dx.doi.org/10.2514/3.13426.

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20

Er-El, J., D. Seter, and D. Weihs. "Nonlinear aerodynamics of a delta wing in combined pitch and roll." Journal of Aircraft 26, no. 3 (1989): 254–59. http://dx.doi.org/10.2514/3.45754.

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21

Grismer, Deborah S., and Robert C. Nelson. "Double-delta-wing aerodynamics for pitching motions with and without sideslip." Journal of Aircraft 32, no. 6 (1995): 1303–11. http://dx.doi.org/10.2514/3.46879.

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22

Karasu, Ilyas, Besir Sahin, M. Oguz Tasci, and Huseyin Akilli. "Effect of Yaw Angles on Aerodynamics of a Slender Delta Wing." Journal of Aerospace Engineering 32, no. 5 (2019): 04019074. http://dx.doi.org/10.1061/(asce)as.1943-5525.0001066.

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23

Mat, Shabudin, I. S. Ishak, Tholudin Mat Lazim, et al. "Development of Delta Wing Aerodynamics Research in Universiti Teknologi Malaysia Low Speed Wind Tunnel." Advances in Mechanical Engineering 6 (January 2014): 434892. http://dx.doi.org/10.1155/2014/434892.

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24

Qu, Qiulin, Zhe Lu, Hao Guo, Peiqing Liu, and Ramesh K. Agarwal. "Numerical Investigation of the Aerodynamics of a Delta Wing in Ground Effect." Journal of Aircraft 52, no. 1 (2015): 329–40. http://dx.doi.org/10.2514/1.c032735.

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25

Kasim, K. A., P. Segard, S. Mat, et al. "Effects of the Propeller Advance Ratio on Delta Wing UAV Leading Edge Vortex." International Journal of Automotive and Mechanical Engineering 16, no. 3 (2019): 6958–70. http://dx.doi.org/10.15282/ijame.16.3.2019.10.0522.

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Delta wing is a triangular-shaped platform that can be applied into the unmanned aerial vehicle (UAV) or drone applications. However, the flow above the delta wing is governed by complex leading-edge vortex structures which result in complicated aerodynamics behaviour. At higher angles of attack, the vortex burst can take place when the swirling flow is unable to sustain the adverse pressure gradient. More studies are needed to understand these vortex phenomena. This paper addresses an experimental study of active flow control called propeller on a generic 55° swept angle sharp-edged delta win

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26

Lamar, J. "A career in vortices and edge forces." Aeronautical Journal 116, no. 1176 (2012): 101–52. http://dx.doi.org/10.1017/s0001924000006667.

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Abstract This lecture recognises the background and distinguished work of Frederick William Lanchester, and notes that my background has a few similarities with his. These include a shared interest in wings, lift and vortices. My career at the NASA Langley Research Center spans the time-frame from America’s Super Sonic Transport through 2009. An early emphasis involved wind-tunnel testing of research aircraft models and the development of computer codes for subsonic aerodynamics of wing planforms. These attached-flow codes were applied to various configurations, including those with variable-s

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27

Sharifi Ghazijahani, Mohammad, and Mehmet Metin Yavuz. "Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing." Aerospace Science and Technology 88 (May 2019): 298–307. http://dx.doi.org/10.1016/j.ast.2019.03.033.

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28

Richard, Robert E., John A. Rule, and Robert L. Clark. "Genetic Spatial Optimization of Active Elements on an Aeroelastic Delta Wing." Journal of Vibration and Acoustics 123, no. 4 (2001): 466–71. http://dx.doi.org/10.1115/1.1389458.

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This work outlines a cohesive approach for the design and implementation of a genetically optimized, active aeroelastic delta wing. Emphasis was placed on computational efficiency of model development and efficient means for optimizing sensor and actuator geometries. Reduced-order models of potential-flow aerodynamics were developed for facilitation of analysis and design of the aeroelastic system in the early design phase. Using these methods, models capturing “95% of the physics with 8% of the modeling effort” can be realized to evaluate various active and passive design considerations. The

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29

ISHIDE, Tadateru, and Kazuya NAGANUMA. "21011 The Improvement Effect of Aerodynamics Characteristic of Leading Edge Flap in Delta Wing." Proceedings of Conference of Kanto Branch 2015.21 (2015): _21011–1_—_21011–2_. http://dx.doi.org/10.1299/jsmekanto.2015.21._21011-1_.

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30

Gregory, J. W., K. Asai, M. Kameda, T. Liu, and J. P. Sullivan. "A review of pressure-sensitive paint for high-speed and unsteady aerodynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222, no. 2 (2008): 249–90. http://dx.doi.org/10.1243/09544100jaero243.

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The current paper describes the development of pressure-sensitive paint (PSP) technology as an advanced measurement technique for unsteady flow fields and short-duration wind tunnels. Newly developed paint formulations have step response times approaching 1 μs, making them suitable for a wide range of unsteady testing. Developments in binder technology are discussed, which have resulted in new binder formulations such as anodized aluminium, thin-layer chromatography plate, polymer/ceramic, and poly(TMSP) PSP. The current paper also details modeling work done to describe the gas diffusion prope

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31

Marques, Pascual. "Aerodynamics of the UCAV 1303 Delta-wing Configuration and Flow Structure Modification Using Plasma Actuators." International Journal of Unmanned Systems Engineering 2, no. 1 (2014): 15–28. http://dx.doi.org/10.14323/ijuseng.2014.3.

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32

Gueraiche, D., and S. А. Popov. "IMPROVING THE AERODYNAMICS OF A TRANSPORT AIRCRAFT WING USING A DELTA PLANFORM WINGTIP LEADING EDGE EXTENSION." Civil Aviation High TECHNOLOGIES 21, no. 1 (2018): 124–36. http://dx.doi.org/10.26467/2079-0619-2018-21-1-124-136.

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33

Gursul, I., M. R. Allan, and K. J. Badcock. "Opportunities for the integrated use of measurements and computations for the understanding of delta wing aerodynamics." Aerospace Science and Technology 9, no. 3 (2005): 181–89. http://dx.doi.org/10.1016/j.ast.2004.08.007.

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34

Zohar, Y., and J. Er-El. "Influence of the aspect ratio on the aerodynamics of the delta wing at high angle of attack." Journal of Aircraft 25, no. 3 (1988): 200–205. http://dx.doi.org/10.2514/3.45578.

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35

MAKIMO, Toshiaki, Kenji KOBAYASHI, Yutaka KAKEHI, Chiyuki KATOU, and Morishige HATTORI. "Study on a Low-Noise Current Collector and the Aerodynamics Using a Delta-Wing-Shaped Collector Head." Transactions of the Japan Society of Mechanical Engineers Series C 63, no. 611 (1997): 2278–86. http://dx.doi.org/10.1299/kikaic.63.2278.

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36

SONE, Tomohiro, Akira URITA, and Shuji TANAKA. "510 Investigation into Aerodynamics of Delta Wing with A11 Angles of Attack and Its Folw Structures : 1st Report, Aerodynamic Characteristics and Wake Structures." Proceedings of Conference of Tokai Branch 2001.50 (2001): 269–70. http://dx.doi.org/10.1299/jsmetokai.2001.50.269.

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37

SONE, Tomohiro, Akira URITA, and Shuji TANAKA. "K-1342 Investigation into Aerodynamics of Delta Wing with All Angles of Attack and Its Folw Structures : 2nd Report, Effect of Aspect Ratios." Proceedings of the JSME annual meeting II.01.1 (2001): 197–98. http://dx.doi.org/10.1299/jsmemecjo.ii.01.1.0_197.

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38

Wang, J. J., and S. F. Lu. "Effects of leading-edge bevel angle on the aerodynamic forces of a non-slender 50° delta wing." Aeronautical Journal 109, no. 1098 (2005): 403–7. http://dx.doi.org/10.1017/s0001924000000828.

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Abstract The aerodynamic performances of a non-slender 50° delta wing with various leading-edge bevels were measured in a low speed wind tunnel. It is found that the delta wing with leading-edge bevelled leeward can improve the maximum lift coefficient and maximum lift to drag ratio, and the stall angle of the wing is also delayed. In comparison with the blunt leading-edge wing, the increment of maximum lift to drag ratio is 200%, 98% and 100% for the wings with relative thickness t/c = 2%, t/c = 6.7% and t/c = 10%, respectively.

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39

Tran, Ngoc Khanh, Van Khang Nguyen, Phu Khanh Nguyen, Thi Kim Dung Hoang, and Van Quang Dao. "Effect of Shapes and Turbulent Inlet Flow to Vortices on Delta Wings." Applied Mechanics and Materials 889 (March 2019): 434–39. http://dx.doi.org/10.4028/www.scientific.net/amm.889.434.

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This paper aims to estimate the effect of turbulent inlet flow to vortices on Delta wing with four different turbulence intensity from 0.5% to 15% and the effect of taper ratios to aerodynamic characteristics of Delta wings with four taper ratios: 0, 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7. The main purpose of this paper is to find out the formation, development, and breakdown of vortices on Delta wings when changing taper ratios and turbulence intensity thence determining the center of vortices with the range of attack angles from 5o to 40o in low velocities about 2.5 m/s. This research uses Delta

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40

Serrano-Rico, Juan Carlos, Gonzalo G. Moreno-Contreras, and Edwin Rúa-Ramírez. "Análisis del desempeño aerodinámico de un ala delta a baja velocidad." Revista UIS Ingenierías 19, no. 2 (2020): 99–104. http://dx.doi.org/10.18273/revuin.v19n2-2020011.

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En el presente trabajo se presentan los resultados de la medición experimentales de los coeficientes aerodinámicos de un ala delta, los coeficientes determinados fueron el de sustentación, arrastre y el de momento, adicionalmente se realizó una visualización del comportamiento del fluido que pasa sobre el ala mediante la utilización de humo y de un compuesto liquido de aceite sobre la superficie del ala. Los resultados obtenidos son comparables con modelo teórico de Polhamus y con experimentales presentadosen la literatura

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41

., Sutrisno, Febryanto Nugroho, Yogi Adi Pratama, Sigit Iswahyudi, and Setyawan Bekti Wibowo. "Sukhoi SU-47 Berkut and Eurofighter Typhoon Models Flow Visualization and Performance Investigation Using GAMA Water Tunnel." Modern Applied Science 13, no. 2 (2019): 21. http://dx.doi.org/10.5539/mas.v13n2p21.

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Changes and modifications to the wings of fighter aircraft were carried out, one of which was the forward swept wing which was a moderate wing that continues to develop. There were also types of delta wings that had been applied to many fighter planes. Both types of aircraft wings had certainly different aerodynamic characteristics. This research would study the flow visualization that occurs in the aircraft model body to determine the aerodynamic characteristics of the forward swept wing and delta wing. This study used a water tunnel to observe the aerodynamic flow and forces that occurred in

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42

Boumrar, I., and A. Ouibrahim. "Delta Wing-Fuselage Interactions - Experimental Study." Advanced Materials Research 274 (July 2011): 43–52. http://dx.doi.org/10.4028/www.scientific.net/amr.274.43.

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Experiments were conducted on thin delta wings to investigate, for subsonic flow, the effect of both privileged apex angle values and the wing-fuselage interactions on the aerodynamic characteristics, i.e. the distribution of the defect pressure on the extrados, the drag and the lift coefficients. For this purpose, several delta wing models of various apex angle (β = 75, 80 and 85°) were realized and tested without and with fuselages of cylindrical form, with diameters of 20 and 30 mm, downstream the apex and appropriately disposed on the extrados. The impact of the apex angle as well as the i

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43

Mat, Shabudin, I. Shah Ishak, Khidzir Zakaria, and Z. Ajis Khan. "Manufacturing Process of Blended Delta-Shaped Wing Model." Advanced Materials Research 845 (December 2013): 971–74. http://dx.doi.org/10.4028/www.scientific.net/amr.845.971.

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Aerodynamicists have long acknowledged the blended wing body (BWB) aircraft design could produce great aerodynamic advantages due to the integration of the delta wing structure with the thick center body. Therefore the wind tunnel test campaign is crucial to gain information of the flow field that governs the delta-shaped wing which has frequently baffled the aerodynamicists. In such, the wind tunnel test required acceptable quality of delta-shaped wing model for results validity. Consequently, the manufacturing process as well as the selection of the appropriate machinery tools, must be wisel

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44

Kawazoe, Hiromitsu, and Susumu Kato. "Effects of Leading Edge Separation Vortex of Flexible Structure Delta Wing on Its Aerodynamic Characteristics(Wing and Airfoil)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 583–89. http://dx.doi.org/10.1299/jsmeicjwsf.2005.583.

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45

Saeedi Rizi, Behnam, Mahdi Nili-Ahmadabadi, Mehrdad Nafar Sefiddashti, and Hamed Khodabakhshian Naeini. "Experimental study of riblet effects on the aerodynamic performance and flow characteristics of a delta wing." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (2017): 1185–92. http://dx.doi.org/10.1177/0954410017748989.

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The present study investigates the effects of riblet on the aerodynamic performance and flow characteristics of a delta wing. Flow visualizations and measurements of the aerodynamic forces are performed on a smooth-surface as well as few textured-surface models of the delta wing. Flow visualizations were undertaken at flow speed of 2.5 m/s and various angles of attack in a vertical wind tunnel. The effects of riblet are investigated on the diameter of the vortices, location of the vortex breakdown, distance of the vortices from the wing surface, pattern of flow lines around the wing, and separ

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46

Saderla, S., R. Dhayalan, K. Singh, N. Kumar, and A. K. Ghosh. "Longitudinal and lateral aerodynamic characterisation of reflex wing Unmanned Aerial Vehicle from flight tests using Maximum Likelihood, Least Square and Neural Gauss Newton methods." Aeronautical Journal 123, no. 1269 (2019): 1807–39. http://dx.doi.org/10.1017/aer.2019.70.

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ABSTRACTIn this paper, longitudinal and lateral-directional aerodynamic characterisation of the Cropped Delta Reflex Wing (CDRW) configuration–based unmanned aerial vehicle is carried out by means of full-scale static wind-tunnel tests followed by full-scale flight testing. A predecided set of longitudinal and lateral/directional manoeuvres is performed to acquire the respective flight data, using a dedicated onboard flight data acquisition system. The compatibility of the acquired dynamics is quantified, in terms of scale factors and biases of the measured variables, using Kinematic consisten

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47

Chen, Yufeng, Nick Gravish, Alexis Lussier Desbiens, Ronit Malka, and Robert J. Wood. "Experimental and computational studies of the aerodynamic performance of a flapping and passively rotating insect wing." Journal of Fluid Mechanics 791 (February 15, 2016): 1–33. http://dx.doi.org/10.1017/jfm.2016.35.

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Flapping wings are important in many biological and bioinspired systems. Here, we investigate the fluid mechanics of flapping wings that possess a single flexible hinge allowing passive wing pitch rotation under load. We perform experiments on an insect-scale (${\approx}1$ cm wing span) robotic flapper and compare the results with a quasi-steady dynamical model and a coupled fluid–structure computational fluid dynamics model. In experiments we measure the time varying kinematics, lift force and two-dimensional velocity fields of the induced flow from particle image velocimetry. We find that in

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48

Arun, M. P., M. Satheesh, and Edwin Raja J. Dhas. "Optimization of Aerodynamic Parameters of Cropped Delta Wing with Fence at Sonic Mach Number." Journal of Computational and Theoretical Nanoscience 16, no. 2 (2019): 403–9. http://dx.doi.org/10.1166/jctn.2019.7740.

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Manufacturing and maintaining different aircraft fleet leads to various purposes, which consumes more money as well as man power. Solution to this, nations that are leading in the field of aeronautics are performing much research and development works on new aircraft designs that could do the operations those were done by varied aircrafts. The foremost benefit of this delta wing is, along the huge rearward sweep angle, the wing’s leading edge would not contact the boundary of shock wave. Further, the boundary is produced at the fuselage nose due to the speed of aircraft approaches and also goe

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49

Gursul, I., R. Gordnier, and M. Visbal. "Unsteady aerodynamics of nonslender delta wings." Progress in Aerospace Sciences 41, no. 7 (2005): 515–57. http://dx.doi.org/10.1016/j.paerosci.2005.09.002.

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50

Yamada, Takafumi, and Yoshiaki Nakamura. "Aerodynamic Characteristics of a Spinning Delta Wing." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51, no. 591 (2003): 133–40. http://dx.doi.org/10.2322/jjsass.51.133.

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