Relevant bibliographies by topics / Delta wing

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Delta wing'

Author: Grafiati
Published: 4 June 2021
Last updated: 26 July 2025

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Journal articles on the topic "Delta wing"

1

Zhang, Ming Lu, Yi Ren Yang, and Zhi Yong Lu. "Unsteady Characteristics over Dynamic Delta Wings." Applied Mechanics and Materials 128-129 (October 2011): 350–53. http://dx.doi.org/10.4028/www.scientific.net/amm.128-129.350.

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A study of flow and frequency characteristics of the leading-edge vortices over a delta wing undergoing pitching up-stop motions is presented. The experiments with the dynamic delta wings were conducted in a water channel and a wind tunnel respectively. Among them, the test of the flow visualization was completed in the water channel with the delta wing with pitching up-stop motions. The result shows that in the case of pitching up-stop movement the vortex breakdown position is dependent on the range of incidence at which the wing is subject to pitching up-stop and the reduced frequency k (k=c
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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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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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Rinoie, K. "Studies of vortex flaps for different sweepback angle delta wings." Aeronautical Journal 101, no. 1009 (1997): 409–16. http://dx.doi.org/10.1017/s0001924000065957.

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AbstractLow speed windtunnel measurements were made on a 50° delta wing with leading edge vortex flaps. Improvements in the lift/drag ratio were obtained by deflecting the leading edge vortex flap. Comparisons were made between the previously measured 60° and 70° delta wing results and the present 50° wing results. Improvements in the lift/drag ratio of the 50° delta wing were attained over a wider lift coefficient range than for the 70° delta wing. The highest lift/drag ratio for the 50° delta wing is achieved when the flow attaches to the flap surface without any large area of separation. Es
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Zhang, Ming Lu, Yi Ren Yang, Zhi Yong Lu, and Li Lu. "Unsteady Characteristics of Breakdown Vortices over Delta Wing." Applied Mechanics and Materials 66-68 (July 2011): 1874–77. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.1874.

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Experiment of unsteady pressure measurement on the surface of wing with 75° sweep delta wing has been carried out in a wind tunnel in order to investigate unsteady characteristics of breakdown vortices over delta wing after the leading edge vortices were breakdown. The result of experiment shows that alter of RMS pressure fluctuations and fluid state of leading edge vortices on the top surface of delta wing are correlative. At the angle region with vortex breakdown, RMS of pressure fluctuations are very huge, similarly buffeting strength of delta wing are large. With increasing angle of attack
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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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Bakaul, Saifur Rahman, Yan Kui Wang, Guang Xing Wu, and Qureshi Humayun. "Effect of Nose Tip on Wing Rock of Slender Delta Wing." Applied Mechanics and Materials 232 (November 2012): 178–83. http://dx.doi.org/10.4028/www.scientific.net/amm.232.178.

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The root cause of wing rock is investigated by examining two slender delta wings (700 and 850 sweep back angle) in wind tunnel using force measurement, pressure measurement and PIV techniques. The results show presence of asymmetric flow at 200 angle of attack and initiation of wing rock at the same point for 850 model while there is neither asymmetric flow nor wing rock for 700 model suggesting close relation of flow asymmetry with wing rock. Investigation with three apparently identical nose sections reveals that the asymmetry comes from the area very close to the wing tip. This asymmetric f
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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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Lee, Mario, and Chih-Ming Ho. "Lift Force of Delta Wings." Applied Mechanics Reviews 43, no. 9 (1990): 209–21. http://dx.doi.org/10.1115/1.3119169.

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On a delta wing, the separation vorticies can be stationary due to the balance of the vorticity surface flux and the axial convection along the swept leading edge. These stationary vortices keep the wing from losing lift. A highly swept delta wing reaches the maximum lift at an angle of attack of about 40°, which is more than twice as high as that of a two-dimensional airfoil. In this paper, the experimental results of lift forces for delta wings are reviewed from the perspective of fundamental vorticity balance. The effects of different operational and geometrical parameters on the performanc
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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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Dissertations / Theses on the topic "Delta wing"

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Allan, Mark. "A CFD investigation of wind tunnel interference on delta wing aerodynamics." Thesis, University of Glasgow, 2002. http://theses.gla.ac.uk/4081/.

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To explore the influence of wind tunnel test facilities on delta wing aerodynamics, the interference has been separated into two distinct types, wall interference and support structure interference. The wall interference effects have been split into three further components, tunnel blockage, side wall interference, and roof and floor interference. Splitting the tunnel influence in this way allows us to determine the most detrimental interference effects, thus allowing the wind tunnel engineer to design experiments accordingly. Euler and more realistic RANS simulations of tunnel interference ha
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Elliott, Michael Stephen. "An investigation into the wing rock of an 80 degree delta wing." Thesis, Imperial College London, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341947.

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Trussa, Colin Weidner. "Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636.

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Vaughan, Jon. "Motion induced aerodynamics of a pitching delta wing." Thesis, University of Bath, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.338376.

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Current trends in modem combat aircraft design have seen a move towards canard configurations with all moving foreplanes, providing a manoeuvre advantage with reduced stability. At the same time, with rapid advances in the field of assisted flight control and emphasis now placed on computer controlled, fly-by-wire aircraft, there is an unprecedented requirement for detailed knowledge of motion dependent aerodynamics, such as may be experienced on a foreplane undergoing rapid corrective motions. In this study, investigations have been carried out into the rigid body, motion dependent aerodynami
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Williams, Nathan M. "Active flow control on a nonslender delta wing." Thesis, University of Bath, 2009. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.501373.

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The effects of active flow control by oscillatory blowing at the leading edge of a nonslender delta wing with a Λ=50° sweep angle have been investigated. Pressure measurements and Particle Image Velocimetry measurements were conducted on a half wing to investigate the formation of leading edge vortices for oscillatory blowing, compared to the stalled flow for the no blowing case. Stall has been delayed by up to 8, and significant increases in the upper surface suction force have been observed. Velocity measurements show that shear layer reattachment is promoted with forcing, and a vortex flow
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Jaworski, Artur Jerzy. "A study of pressure fluctuations caused by vortex breakdown." Thesis, Imperial College London, 1996. http://hdl.handle.net/10044/1/8816.

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Worley, John C. Ahmed Anwar. "Yaw-roll coupled oscillations of a slender delta wing." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SUMMER/Aerospace_Engineering/Thesis/Worley_John_37.pdf.

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Görtz, Stefan. "Realistic simulations of delta wing aerodynamics using novel CFD methods." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-125.

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<p>The overall goal of the research presented in this thesis is to extend the physical understanding of the unsteady external aerodynamics associated with highly maneuverable delta-wing aircraft by using and developing novel, more efficient computational fluid dynamics (CFD) tools. More specific, the main purpose is to simulate and better understand the basic fluid phenomena, such as vortex breakdown, that limit the performance of delta-wing aircraft. The problem is approached by going from the most simple aircraft configuration - a pure delta wing - to more complex configurations. As the flow
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Le, Moigne Yann. "Adaptive Mesh Refinement and Simulations of Unsteady Delta-Wing Aerodynamics." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3786.

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<p>This thesis deals with Computational Fluid Dynamics (CFD)simulations of the flow around delta wings at high angles ofattack. These triangular wings, mainly used in militaryaircraft designs, experience the formation of two vortices ontheir lee-side at large angles of attack. The simulation ofthis vortical flow by solving the Navier-Stokes equations isthe subject of this thesis. The purpose of the work is toimprove the understanding of this flow and contribute to thedesign of such a wing by developing methods that enable moreaccurate and efficient CFD simulations.</p><p>Simulations of the for
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Shrivastava, Swapna. "Aeroelastic oscillations of a delta wing with bonded piezoelectric strips." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape8/PQDD_0023/MQ50660.pdf.

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Books on the topic "Delta wing"

1

Tavella, Domingo A. An analysis of conical augmentor/delta wing integration. Stanford University, Department of Aeronautics and Astronautics, 1987.

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2

Wood, Richard M. Study of lee-side flows over conically cambered delta wings at supersonic speeds. Langley Research Center, 1987.

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3

B, Watson Carolyn, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Study of lee-side flows over conically cambered delta wings at supersonic speeds. National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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4

Hu, B. K. The performance of 60 degree delta wings: the effects of leading edge radius on vortex flaps and the wing. Cranfield Institute of Technology, College of Aeronautics, 1990.

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Leonard, Roberts, and United States. National Aeronautics and Space Administration., eds. Controlled vortical flow on delta wings through unsteady leading edge blowing. Stanford University, Dept. of Aeronautics and Astronautics, Joint Institute for Aeronautics and Acoustics, 1990.

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6

Kjelgaard, Scott O. Detailed flow-field measurements over a 75⁰ swept delta wing. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Kjelgaard, Scott O. Detailed flow-field measurements over a 75⁰ swept delta wing. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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8

Lee, Chyang S. Experimental studies of a delta wing with leading edge flaps. Joint Institute for Aeronautics and Acoustics, 1987.

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9

Tiwari, Surendra N. Numerical solutions of Navier-Stokes equations for a Butler wing. Dept. of Mechanical Engineering and Mechanics, School of Engineering, Old Dominion University, 1985.

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A, Tavella D., Roberts Leonard, and United States. National Aeronautics and Space Administration., eds. Numerical study of delta wing leading edge blowing. Joint Institute for Aeronautics and Acoustics, 1988.

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Book chapters on the topic "Delta wing"

1

Ludin@ Jamaluddin, Hani, Ashraf A. Omar, and Waqar Asrar. "Numerical Investigation of the Flow Over Delta Wing and Reverse Delta Wing." In Advanced Structured Materials. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-02836-1_7.

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Chaput, Eric, Alexandre Corjon, Philippe Tran, Bertrand Aupoix, and Robert Houdeville. "Flow Over A Delta Wing." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_70.

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Pallegoix, J. F. "DSMC calculation on a delta wing." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_73.

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Nakamura, Y., Y. Nakajima, and W. Jia. "Aerodynamic Characteristics of Thick Delta Wing." In Fluid Dynamics of High Angle of Attack. Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8_26.

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Cevdet Celenligil, M., and James N. Moss. "DSMC Calculations for The Delta Wing." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-76527-8_68.

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Sarwar, Md Gulam, Syed Shoaib Mohd, Senthil Kumar Raman, and Saista Tabssum. "Detailed Study of Delta Wing Aerodynamics." In Advances in Aerospace Technologies. River Publishers, 2024. http://dx.doi.org/10.1201/9788770046299-3.

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Hirschel, Ernst Heinrich, Arthur Rizzi, Christian Breitsamter, and Werner Staudacher. "Small Aspect-Ratio Delta-Type Wing Flow." In Separated and Vortical Flow in Aircraft Wing Aerodynamics. Springer Berlin Heidelberg, 2020. http://dx.doi.org/10.1007/978-3-662-61328-3_10.

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Schröder, W., and S. Menne. "Hypersonic Delta-Wing Flow, Case VII.4." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_66.

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Abgrall, Rémi, Jean-Antoine Désidéri, Roland Glowinski, Michel Mallet, and Jacques Périaux. "Problem VII: Flow over a Delta Wing." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_7.

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Désidéri, Jean-Antoine, Roland Glowinski, and Jacques Périaux. "Problem 7: Flow over a Delta Wing." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84580-2_19.

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Conference papers on the topic "Delta wing"

1

Otaka, Saimon, Aatsushi Tate, and Takashi Yoshinaga. "Wing rock of double delta wings." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4078.

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Shumsky, Gennady. "Wing Rock on a Delta Wing." In 2006 International Forum on Strategic Technology. IEEE, 2006. http://dx.doi.org/10.1109/ifost.2006.312262.

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Ishide, Tadateru, Kazuya Naganuma, Shinsuke Seiji, Hiroyuki Ishikawa, Ryo Fujii, and Kazuo Maeno. "Aerodynamical Improvement of Delta Wing and Flapping Wing." In ASME/JSME/KSME 2015 Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/ajkfluids2015-13075.

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Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study are researching the aerodynamic improvement of delta wing and flapping wing in low Reynold’s number region to develop an applicative these air vehicle. Various configurations of Leading Edge Flap (LEF) are used to enhance the aerodynamic characteristics in the delta wing. The six kind of elliptical wings made of stainless steel are used in the flapping wing. The effects of flapping amplitude and wing configuration regarding the aerodynamic
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Ericsson, Lars. "Wing rock of non-slender delta wings." In 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-137.

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KONSTADINOPOULOS, P., D. MOOK, and A. NAYFEH. "Subsonic wing rock of slender delta wings." In 23rd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-198.

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Ericsson, Lars. "Delta wing vortex breakdown dynamics." In 33rd Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-367.

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Tarn, J. H., and F. Y. Hsu. "Fuzzy Control of Wing Rock for Slender Delta wings." In 1993 American Control Conference. IEEE, 1993. http://dx.doi.org/10.23919/acc.1993.4793048.

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Bou-Mosleh, Charbel, and Samir Patel. "CFD-Based Aerodynamic Analysis of Damaged Delta Wings." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38420.

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This paper addresses the aerodynamic response of damaged delta wings using steady-state Computational Fluid Dynamics simulations. Two types of delta wings are investigated: a High Speed Civil Transport (HSCT) wing and a F16 Block 40 Wing. These types of analyses are required to help predict wings’ remaining flight capability, after damage is inflicted (during battle). The damage is represented by a hole in the CFD model of both wings. Variations in the shape, size, location and orientation of holes are investigated. The lift and drag (at relatively low angles of attack) of the undamaged and da
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GORDNIER, RAYMOND. "Computation of delta-wing roll maneuvers." In 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2975.

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GORDNIER, RAYMOND, and MIGUEL VISBAL. "Numerical simulation of delta-wing roll." In 31st Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-554.

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Reports on the topic "Delta wing"

1

Telionis, Demetri P. The Transient Development of Vortices Over a Delta Wing. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada231946.

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Rockwell, Donald O. Unsteady Structure of Leading-Edge Vortices on a Delta Wing. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada278988.

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Verhaagen, Nicolaas G. Wind Tunnel Wall Effects on the Flow around a 76/40-deg Double-Delta Wing. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada327879.

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Van Dommelen, L. Thrust-Induced Effects on a Pitching-Up Delta Wing Flow Field: Control of Stalled Wings. Defense Technical Information Center, 1995. http://dx.doi.org/10.21236/ada329654.

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Lourenco, L., C. Shih, L. Van Dommelen, and A. Krothapaili. Thrust-Induced Effects on a Pitching-Up Delta Wing Flow Field. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada310244.

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Gordnier, Raymond E. Computation of a Kelvin-Helmholtz Instability for Delta Wing Vortex Flows. Defense Technical Information Center, 1991. http://dx.doi.org/10.21236/ada244320.

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Ghee, Terence A., Hugo A. Gonzalez, and David B. Findlay. Experimental Investigation of Vortex-Tail Interaction on a 76/40 Degree Double-Delta Wing. Defense Technical Information Center, 1999. http://dx.doi.org/10.21236/ada368657.

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Gonzalez, Hugo, Gary Erickson, Blair McLachlan, and James Bell. Effects of Various Shape Fillets on a 76/40 Double Delta Wing from Mach 0.18 to 0.7. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada389614.

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Russell, Horace, and Reginald G. Williams. Cross Flow Over Double Delta Wings. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada363041.

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Inghram, M. G. Wind data from the Delta Two East Wind Station, 1983. Alaska Division of Geological & Geophysical Surveys, 1988. http://dx.doi.org/10.14509/1381.

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