Journal ArticleDOI
Applying slender wing benefits to military aircraft
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In this article, a review of aerodynamic research performed at the Langley Research Center related to the application of slender wing benefits in the design of high-speed military aircraft is presented.Abstract:
1Therefore, in keeping with the spirit of the Wright brothers research and design accomplishments, as well as the scope of this meeting, I have elected to review some of the aerodynamic research performed at the Langley Research Center related to the application of slender wing benefits in the design of high-speed military aircraft In the context of this paper, slender wing benefits refer primarily to the supersonic performance and leading edge vortex flow associated with very highly sweptback wings Following a review of some early slender wing research, the paper presents several case histories of Langley contributions to the development of aircraft incorporating slender wing benefits and then summarizes some vortex flow technology that may contribute to future aircraftread more
Citations
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Experimental Surface Pressure Data Obtained on 65 deg Delta Wing Across Reynolds Number and Mach Number Ranges
Julio Chu,James M. Luckring +1 more
TL;DR: In this article, an experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was conducted in the Langley National Transonic Facility (NTF) to investigate the effects of Reynolds and Mach numbers on slender-wing leading-edge vortex flows with four values of wing leading edge bluntness.
Journal ArticleDOI
High Angle-of-Attack Aerodynamics
TL;DR: High angle-of-attack (high-IX) aerodynamics has been a key element in airplane design beginning with the first attempts at unpowered manned flight using gliders in the 1 800s and extending to the present day with civil and military airplanes.
Journal ArticleDOI
Vortical flow management techniques
TL;DR: The aerodynamic performance and controllability of advanced, highly maneuverable supersonic aircraft can be enhanced by means of vortex management, which refers to the purposeful manipulation and reordering of stable and concentrated vortical structures due to flow separations from highly swept leading edges and slender forebodies at moderate-to-high angles-of-attack as discussed by the authors.
Journal ArticleDOI
Effect of a fuselage on delta wing vortex breakdown
Journal ArticleDOI
The discovery and prediction of vortex flow aerodynamics
TL;DR: The discovery of separation-induced vortex flows and the development of methods to predict these flows for wing aerodynamics are reviewed.
References
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Journal ArticleDOI
Predictions of vortex-lift characteristics based on a leading-edge suction analogy.
TL;DR: In this article, the leading edge suction analogy for predicting low speed lift and drag due-to-lift characteristics of sharp edge delta and related wing planforms was used to predict a low speed aircraft.
Journal ArticleDOI
Improved calculations of leading-edge separation from slender, thin, delta wings
TL;DR: In this article, the authors used an automatic digital computer to locate the vortex sheet and determine its strength in terms of the two boundary conditions on it; assesses the credibility of the results; and relates them to the observations.
On Slender Delta Wings with Leading-edge Separation
TL;DR: In this paper, the slender-body approximation of linearized compressible flow was applied to the problem of a delta wing in which flow separation occurs at the leading edges, and the leading edge separation was found to produce an increase in lift over that given by the Jones slender-wing theory and that lift does not linearly increase with angle of attack.
Journal ArticleDOI
Augmentation of Vortex Lift by Spanwise Blowing
TL;DR: In this paper, an investigation has been conducted to evaluate the aerodynamic effects associated with blowing a jet spanwise over a wing's upper surface in a direction parallel to the leading edge.
Subsonic aerodynamic characteristics of interacting lifting surfaces with separated flow around sharp edges predicted by a vortex-lattice method
J. E. Lamar,B. B. Gloss +1 more
TL;DR: In this paper, the authors applied the vortex-lattice method to computing side-edge suction force for isolated or interacting planforms, and found that the results obtained for a number of different isolated planforms produced acceptable agreement with results obtained from a method employing continuous induced-velocity distributions.