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
- Language(s)
-
English
- Published
-
Washington, D.C. : National Aeronautics and Space Administration ; 1974.
- 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.
Viewability
Item Link |
Original Source |
Full view
|
University of Illinois at Urbana-Champaign
|