Interaction between an external compression shock and a blunt body in a hypersonic stream

1977 ◽  
Vol 11 (1) ◽  
pp. 84-89 ◽  
Author(s):  
G. A. Shmanenkova
Keyword(s):  
Blunt Body ◽  
Compression Shock ◽  
External Compression ◽  
Hypersonic Stream

Flow in vicinity of blunt body stagnation point in diverging hypersonic stream

1973 ◽  
Vol 5 (3) ◽  
pp. 444-447 ◽  
Author(s):  
V. V. Lunev ◽  
N. E. Khramov
Keyword(s):  
Stagnation Point ◽  
Blunt Body ◽  
Hypersonic Stream

Erosion of a blunt body in a dusty hypersonic stream

1985 ◽  
Vol 25 (4) ◽  
pp. 591-597 ◽  
Author(s):  
A. P. Trunev ◽  
V. M. Fomin
Keyword(s):  
Blunt Body ◽  
Hypersonic Stream

Assessing the Impact of the Inlet Total Pressure Distortion on the Turbofan Thrust

2018 ◽  
pp. 19-30
Author(s):  
Yu. A. Ezrokhi ◽  
E. A. Khoreva
Keyword(s):  
Total Pressure ◽  
External Compression ◽  
Average Value ◽  
Inlet Distortion ◽  
Air Inlet ◽  
Engine Thrust ◽  
Relative Value ◽  
Main Effect ◽  
Pressure Recovery Factor ◽  
The Impact

The paper considers techniques to develop a mathematical model using a method of «parallel compressors». The model is intended to estimate the impact of the air inlet distortion on the primary parameters of the aero-engine.  The paper presents rated estimation results in the context of twin spool turbofan design for two typical cruiser modes of flight of the supersonic passenger jet. In estimation the base values σbase and the average values of the inlet ram recovery σave remained invariable. Thus, parametrical calculations were performed for each chosen relative value of the area of low-pressure region.The paper shows that an impact degree of the inlet distortion on the engine thrust for two modes under consideration is essentially different. In other words, if in the subsonic mode the impact assessment can be confined only to taking into account the influence of decreasing average values of the inlet total pressure, the use of such an assumption in the supersonic cruiser mode may result in considerable errors.With invariable values of the pressure recovery factor at the engine intake, which correspond to the speed of flight for a typical air inlet of external compression σbase, and average value σave, a parameter Δσuneven  has the main effect on the engine thrust, and degree of this effect essentially depends on a difference between σave and σbase values.

Blunt-body wave drag reduction using focused energy deposition

AIAA Journal ◽  
1999 ◽  
Vol 37 ◽  
pp. 460-467 ◽  
Author(s):  
David Riggins ◽  
H. F. Nelson ◽  
Eric Johnson
Keyword(s):  
Drag Reduction ◽  
Energy Deposition ◽  
Blunt Body ◽  
Body Wave ◽  
Wave Drag ◽  
Wave Drag Reduction

Survey of blunt body flows including wakes at hypersonic low-density conditions

10.2514/3.900 ◽  
1997 ◽  
Vol 11 ◽  
pp. 321-329
Author(s):  
Daniel C. Hammerand ◽  
Rakesh K. Kapania ◽  
James N. Moss ◽  
Joseph M. Price
Keyword(s):  
Blunt Body ◽  
Low Density
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