WIND TUNNEL INVESTIGATION OF A 0.10-SCALE NORTH AMERICAN AVIATION AMSA INLET AT TRANSONIC AND SUPERSONIC MACH NUMBERS
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
Test results are presented for a study on a 0.10-scale model of the North American Aviation proposed advanced manned strategic aircraft air vehicle. Inlets of various geometries were tested at several Mach numbers, angles of attack, and angles of yaw. Inlet performance in terms of compressor face total- pressure recovery and flow distortion is presented as a function of mass-flow ratio for various inlet geometries at several Mach numbers and model attitudes.