6 Wind and Water Tunnel Equipment
431
Fig. 6.59 2.4 m × 2.4 m transonic wind tunnel
Fig. 6.60 2.4 m × 2.4 m transonic wind tunnel test section
6.7 Hypersonic Wind Tunnel
When the shuttle returned to the ground, it reentered the atmosphere at flight
Ma = 30 from a flight altitude of about 150 km. The hypersonic flight of
the space shuttle has to go through different stages from the free molecular
flow zone to the hypersonic continuous flow zone. In the hypersonic continuous flow area, although the flight Mach number is not very high (about
5−12.5), the flight Reynolds number is high, the total temperature and total
entropy of the flow are high, and there are real gas effects. The so-called real
gas effect mainly refers to the effect of high-temperature heating. When the
space shuttle flies in the hypersonic continuous flow zone, both the compression of the strong bow shock wave in front of the body and the airflow caused
by the viscous blockage of hypersonic flow in the boundary layer will generate
431
Fig. 6.59 2.4 m × 2.4 m transonic wind tunnel
Fig. 6.60 2.4 m × 2.4 m transonic wind tunnel test section
6.7 Hypersonic Wind Tunnel
When the shuttle returned to the ground, it reentered the atmosphere at flight
Ma = 30 from a flight altitude of about 150 km. The hypersonic flight of
the space shuttle has to go through different stages from the free molecular
flow zone to the hypersonic continuous flow zone. In the hypersonic continuous flow area, although the flight Mach number is not very high (about
5−12.5), the flight Reynolds number is high, the total temperature and total
entropy of the flow are high, and there are real gas effects. The so-called real
gas effect mainly refers to the effect of high-temperature heating. When the
space shuttle flies in the hypersonic continuous flow zone, both the compression of the strong bow shock wave in front of the body and the airflow caused
by the viscous blockage of hypersonic flow in the boundary layer will generate