Analysis of Wind Tunnel Test Results of Fluidic Generator for High-Altitude Rocket.

摘要

A ram-air-driven power supply for a proposed high-altitude rocket was tested in the Naval Surface Weapons Center supersonic wind tunnel facility. The wind tunnel data that corresponded to points on the trajectory providing the least ram-air energy showed that the generator operated throughout the test and produced a minimum of 26.4 Vrms into a simulated fuze load near the apex where pneumatic power input is minimal. A method of predicting generator voltage in flight from laboratory calibration data and expected flight conditions was verified for Mach numbers from 1.5 to 2.02 and free-stream total pressures of up to 20 lb/in sq in. abs (137 kPa). (Author)