Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction /
Joseph F. Wasserbauer.

APA Citation

Wasserbauer, J. F., Lewis Research Center., United States. National Aeronautics and Space Administration. (1969). Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction. Washington, D.C.: National Aeronautics and Space Administration .

MLA Citation

Wasserbauer, Joseph F, Lewis Research Center, and United States. National Aeronautics and Space Administration. Dynamic Response of a Mach 2.5 Axisymmetric Inlet With Engine Or Cold Pipe And Utilizing 60 Percent Supersonic Internal Area Contraction. Washington, D.C.: National Aeronautics and Space Administration , 1969.