5.3 Typical Supersonic Wind Tunnels
131
Fig. 5.20 Test section of the ISL trisonic wind tunnel (© ISL)
from −7° to +24°. The Reynolds number, based on the maximum diameter of the
model, is between 5 × 10
5 and 2.2 × 10
6 , for a turbulence intensity of less than 1%.
5.4 Mach 6 Quiet Wind Tunnel
The challenges involved in reproducing the phenomenon of laminar to turbulent transition in a wind tunnel due to its sensitivity to ambient disturbances produced by the
facility itself has already been pointed out in previous chapters. Figure 5.21 illustrates the sources of environmental disturbance in a supersonic or hypersonic wind
Fig. 5.21 Perturbations sources in a supersonic wind tunnel (© Purdue University)
131
Fig. 5.20 Test section of the ISL trisonic wind tunnel (© ISL)
from −7° to +24°. The Reynolds number, based on the maximum diameter of the
model, is between 5 × 10
5 and 2.2 × 10
6 , for a turbulence intensity of less than 1%.
5.4 Mach 6 Quiet Wind Tunnel
The challenges involved in reproducing the phenomenon of laminar to turbulent transition in a wind tunnel due to its sensitivity to ambient disturbances produced by the
facility itself has already been pointed out in previous chapters. Figure 5.21 illustrates the sources of environmental disturbance in a supersonic or hypersonic wind
Fig. 5.21 Perturbations sources in a supersonic wind tunnel (© Purdue University)