Design of a High Reynolds Number Mach Number 8 Contoured Nozzle for the Hypervelocity Wind Tunnel (F).
Final rept. Jan-Jun 71,
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
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The report describes the aerodynamic design of a Mach 8 contoured nozzle for a hypervelocity wind tunnel. The nozzle is expected to operate over a broad range of reservoir conditions including temperatures and pressures which will allow the simulation of flight conditions at 70,000-ft altitude. Both tunnel blockage considerations and tunnel core size estimates indicate that 4.5-in.-diam very blunt 6-in. diam hemisphere models, and larger diameter sharp nose models could be tested. This method may be used to extrapolate boundary-layer predictions to higher Reynolds numbers. Author
- Test Facilities, Equipment and Methods