scholarly journals Aerodynamic Interaction between Delta Wing and Hemisphere-Cylinder in Hypersonic Flow

2004 ◽  
Vol 52 (606) ◽  
pp. 289-294 ◽  
Author(s):  
Atsuhiro Nishino ◽  
Takafumi Ishikawa ◽  
Takumi Okada ◽  
Yoshiaki Nakamura
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Aerodynamic Interaction

Errata: "Hypersonic Flow over a Delta Wing of Moderate Aspect Ratio"

AIAA Journal ◽  
1966 ◽  
Vol 4 (7) ◽  
pp. 1312c-1312c ◽  
Author(s):  
N. D. MALMUTH
Keyword(s):  
Aspect Ratio ◽  
Hypersonic Flow ◽  
Delta Wing

GS14 TSP Measurements on Aerodynamic Interaction between Side-jet and Hypersonic Flow

2015 ◽  
Vol 2015 (0) ◽  
pp. _GS14-1_-_GS14-3_
Author(s):  
Masato TAGUCHI ◽  
Keiichi KITAMURA ◽  
Koichi MORI
Keyword(s):  
Hypersonic Flow ◽  
Aerodynamic Interaction

Hypersonic flow past delta wing of finite thickness

1973 ◽  
Vol 5 (3) ◽  
pp. 394-402 ◽  
Author(s):  
A. L. Gonor ◽  
N. A. Ostepenko
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Finite Thickness ◽  
Flow Past

Supersonic and hypersonic flow with attached shock waves over delta wings

1971 ◽  
Vol 325 (1561) ◽  
pp. 251-268 ◽  
Keyword(s):  
Shock Waves ◽  
Flow Field ◽  
Hypersonic Flow ◽  
Delta Wing ◽  
Cross Flow ◽  
Flow Region ◽  
Lower Surface ◽  
Uniform Flow ◽  
Nonuniform Flow ◽  
Sonic Line

A unified theory is developed for supersonic and hypersonic flow with attached shock waves over the lower surface of a delta wing at an angle of attack. The flow field on the lower surface of a delta wing consists of uniform flow regions near the leading edges, where the cross flow is supersonic and a nonuniform flow region near the central part, where the cross flow is subsonic. In the nonuniform flow region, the theory is based on the assumption that the flow differs slightly from the corresponding two-dimensional flow over a flat plate. Thus a linearized perturbation on a nonlinear flow field is first calculated and then strained and corrected so that the flow is matched continuously to the uniform flow which is obtained exactly. When compared with available exact numerical solutions the theory gives, in all cases, almost identical results, except near the crossflow sonic line where existing numerical methods fail to produce a discontinuous slope in the pressure curve, whereas the present theory predicts such a discontinuity and shows that the slope has a square root singularity at the crossflow sonic line similar to that in the supersonic linear theory.

Aerodynamic characteristics of a delta wing in hypersonic flow

1994 ◽  
Vol 35 (2) ◽  
pp. 224-227
Author(s):  
V. Ya. Kiselev ◽  
A. A. Maslov ◽  
A. N. Shiplyuk
Keyword(s):  
Hypersonic Flow ◽  
Delta Wing ◽  
Aerodynamic Characteristics
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