Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction /
by Robert J. Baumbick, Robert E. Wallhagen, and Robert C. Seidel.

Description

Main Author

Baumbick, Robert J.

Related Names

Seidel, Robert C.
Wallhagen, Robert E.
Lewis Research Center.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration ; 1974.

Subjects

Air ducts > Air ducts / Aerodynamics.
Aerodynamics, Supersonic.
Airplanes > Airplanes / Turbofan engines.
Airplanes > Airplanes / Turbojet engines > Airplanes / Turbojet engines / Air intakes > Airplanes / Turbojet engines / Air intakes / Automatic control.
Turbofan engines.
Transfer functions.
Static pressure.
Pressure recovery.
Inlet flow.
Feedback control.
Wind tunnel tests.
Supersonic inlets.
Shock wave control.

Summary

Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was coupled to either a choked orifice plate or a long duct which had a variable-area choked exit plug. Closed-loop frequency responses of selected diffuser static pressures used in the terminal-shock control system are presented. Results are shown for Mach 2.5 conditions with the inlet coupled to either the choked orifice plate or the long duct. Inlet unstart-restart traces are also presented. High-response inlet bypass doors were used to generate an internal disturbance and also to achieve terminal-shock control.

Note

"NASA TM X-2992."
Performing organization report no.: E-7688.
"February 1974."
Cover title.
Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 9/14/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740008381_1974008381.pdf.

Physical Description

18 p. : ill. ; 27 cm.

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