SOME INTERNAL-FLOW CHARACTERISTICS AT ZERO FLIGHT SPEED OF AN ANNULAR SUPERSONIC INLET AND AN OPEN-NOSE INLET WITH SHARP AND ROUNDED LIPS

摘要

Static tests of an annular conical-shock inlet and an open-nose conical inlet with three lip shapes were conducted at the Langley 8-foot transonic tunnel. Measurements of pressure recovery, surface pressure, and total pressure were made through a mass-flow range extending to choking. The results indicate that the two inlets with thin sharp lips had about the same relatively poor pressure-recovery characteristics and choked at a mass-flow rate of about 78 percent of the theoretical maximum. However, both the pressure recovery and choking mass-flow rate were greatly improved by replacing the sharp lip by two alternate shapes with lip roundness and internal contraction just behind the inlet lip.