漂亮才会豪华
发表于 2025-3-28 17:20:40
http://reply.papertrans.cn/87/8667/866675/866675_41.png
DRILL
发表于 2025-3-28 20:46:05
Effects of Leading-Edge Bluntness on Control Flap Effectiveness at Hypersonic Speedsin a hypersonic gun tunnel facility at .. = 8.2 and ../. = 9.0 × 10.. The flow structure over a low aspect ratio flat plate with a full span trailing edge flap has been investigated using high speed Schlieren photography as well as surface pressure and heat transfer measurements.
一骂死割除
发表于 2025-3-28 23:17:32
Measuring the Effect of Nose Bluntness on Drag of a Cone in a Hypervelocity Shock Tunnel Facilitynd hypervelocity (flight speed & 5 km/s) regime. Experiments were performed in a free-piston driver shock tunnel facility. Drag measurements were made using the de convolution force balance (Sanderson and Simmons 1991) for measuring drag in hypervelocity impulse facilities where test times may be of
Nebulizer
发表于 2025-3-29 05:09:58
http://reply.papertrans.cn/87/8667/866675/866675_44.png
商店街
发表于 2025-3-29 10:07:22
http://reply.papertrans.cn/87/8667/866675/866675_45.png
揭穿真相
发表于 2025-3-29 13:43:48
http://reply.papertrans.cn/87/8667/866675/866675_46.png
轻浮思想
发表于 2025-3-29 15:40:30
http://reply.papertrans.cn/87/8667/866675/866675_47.png
IVORY
发表于 2025-3-29 23:46:50
Oblique Shock Interactions with Mach Number Distributions-Hugoniot shock jump conditions. This equation essentially describes the shape an oblique shock assumes as it traverses a region of varying Mach number. Because the analysis also provides a flow solution downstream of the shock, it is seen as a particularly useful tool in the study of shock wave — m
遭受
发表于 2025-3-30 00:34:38
Strength of Characteristics at a Curved Shock Wavee gradient and streamline curvature are used to determine the relative strengths (the reflection coefficient) of characteristics just downstream of a two-dimensional curved shock wave. It is shown that the characteristics’ strengths are a complex function of the specific heat ratio, the upstream Mac
Enthralling
发表于 2025-3-30 06:55:01
Blunt Body Flow — The Transonic Regionthe downstream surface of the shock wave and the limiting characteristics. Using curved shock theory, we establish the conditions under which the shock surface is (type I), or is not (type II), a boundary of the transonic region. It is found that the existence of type I or type II flow is determined