Performance possibilities of the turbojet system as a power plant for supersonic airplanes

George P. Wood
naca-rm-l7h05a
Aug 1947


The performance of hypothetical turbojet systems, without thrust augmentation, as power plants for supersonic airplanes has been calculated. The thrust, thrust power, air-fuel ratio, specific fuel consumption, cross-sectional area, and thrust coefficient are shown for free-stream Mach numbers form 1.2 to 3.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1947/naca-rm-l7h05a.pdf