Flow field calculation in supersonic mixed-compression aircraft inlets at angle of attack using the three-dimensional method of characteristics with discrete shock wave fitting
Vadyak, Joseph
Flow field calculation in supersonic mixed-compression aircraft inlets at angle of attack using the three-dimensional method of characteristics with discrete shock wave fitting - - n.p. Purdue University, 1977 - xiv,243 p. 22 cm - .
0
Aerodynamics, Supersonic
Shock waves
621.454:533.6.07 Vad
Flow field calculation in supersonic mixed-compression aircraft inlets at angle of attack using the three-dimensional method of characteristics with discrete shock wave fitting - - n.p. Purdue University, 1977 - xiv,243 p. 22 cm - .
0
Aerodynamics, Supersonic
Shock waves
621.454:533.6.07 Vad