Preliminary investigation of effect of angle of attack on pressure recovery and stability characteristics for a vertical-wedge-nose inlet at Mach number of 1.90

Leissler, L. Abbott., Hearth, Donald P.
naca-rm-e52e14
1952


A preliminary investigation of an inlet consisting of a vertical wedge compression surface was conducted at a Mach number of 1.90 and at angles of attack from 0 degrees to 10 degrees. With a symmetrical cowling, pressure recovery and stability characteristics comparable to a conical inlet were observed; however, twin-duct flow interaction was observed. Modification of the inlet by cutting back the lower cowl lip and by perforating the wedge centerbody resulted in relatively constant maximum pressure recovery up to 10 degrees angle of attack. These modifications also eliminated the twin-duct instability and increased the stable subcritical range of the inlet.

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