SUPERSONIC TUNNEL INVESTIGATION BY MEANS OF INC LINED-PLATE TECHNIQUE TO DETERMINE PERFORMANCE OF SEVERAL NOSE INLETS OVER MACH NUMBER RANGE OF 1.72 TO 2.18

摘要

A suspended flat plate was used to continuously vary the Mach number in the NACA Levis 48- by 18-inch Mach number 1.91 supersonic, tunnel. The useful range of the tunnel was extended over a range of Mach numbers from 1.72 to 2.18. Maximum variations in the Mach number. of the flow produced at the vicinity of nose inlets at zero angle, of attack were ±0.01 and flow angularities were less than approximately 0.35°nThe technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced.