Wind Tunnel Investigation of a 0.10-Scale North American Aviation AMSA Inlet at Transonic and Supersonic Mach Numbers
Wind Tunnel Investigation of a 0.10-Scale North American Aviation AMSA Inlet at Transonic and Supersonic Mach Numbers
- Neue Suche nach: H. E. McDill
- Neue Suche nach: J. F. Riddell
- Neue Suche nach: H. E. McDill
- Neue Suche nach: J. F. Riddell
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. (Author)
Dokumentinformationen
Wind Tunnel Investigation of a 0.10-Scale North American Aviation AMSA Inlet at Transonic and Supersonic Mach Numbers
1967
76 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Aircraft , Jet bombers , Turbojet inlets , Advanced weapons , Strategic weapons , Wind tunnel models , Model tests , Transonic characteristics , Supersonic characteristics , Angle of attack , Yaw , Aerodynamic configurations , Flow fields , Performance(Engineering) , Pressure , Recovery , Distortion , Amsa(Advanced manned strategic aircraft)