Abstract
The GALCIT 5- by 5-in. continuous hypersonic wind tunnels are designed for maximum stagnation temperatures of 400°F. (Leg No. 1) and 1,100°F. (Leg No. 2) and for a maximum reser voir pressure of 1,040 lbs. per sq.in. The hypersonic shock tube is being used to obtain aerodynamic information, and some pre liminary results are presented. By measurements of static and total head pressure in the nozzle, the amount of supersaturation of the air has been determined for a higher range of hypersonic Mach Numbers. On a 26-in. long flat plate an extensive in vestigation at Mach Number 5.8 was conducted to determine the contamination of the laminar boundary layer due to air injection from orifices near the leading edge and the turbulent boundary layer from the side walls. The transition Reynolds Number for a flat plate was at least 5.5 million for a Mach Number of 5.8, and the laminar boundary layer seemed to be extremely stable at this Mach Number and required strong disturbances to produce transition. The static pressure on a flat plate varied due to the interaction of the leading edge shock wave with the boundary layer on the plate.
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