Performance of external-compression bump inlet at Mach numbers of 1.5 and 2.0

Paul C. Simon, Dennis W. Brown, Ronald G. Huff
naca-rm-e56l19
Apr 1957


An experimental investigation of a one-fifth-scale model of the forebody of a proposed supersonic fighter was conducted to determine the internal performance and configuration drag of various twin-side inlets.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1957/naca-rm-e56l19.pdf