NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Supersonic Test of the 10-Inch Bifurcated Two-Stage Supersonic Inlet (BTSSI)Experimental results from testing of a novel supersonic inlet model in NASA Glenn Research Center's 10- by 10-foot supersonic wind tunnel are presented. The patented inlet concept, called Two-Stage Supersonic Inlet (TSSI), incorporates a large cavity, or throat slot, in the supersonic diffuser intended to enhance the stability of the normal shock. The present embodiment of the concept is a bifurcated twin-duct) design. During the course of testing an unusual 'semi-started' mode of operation was encountered. The inlet was able to spill up to 30 percent of the captured airstream without fully expelling the normal shock. In this mode, the total pressure recovery dropped approximately 6 percent without increasing steady-state distortion. Dynamic instrumentation at the cowl lip station indicates the semi-start mode may be a series of unstart/restart cycles with frequency ranging from 0.2 to 20 Hz. Engine face total pressure measurements indicate a modest impact due to this event. However, since the current test article does not have a representative subsonic diffuser (and is in fact separated), it is unclear how this mode of operation would effect an engine. Further investigation of this phenomenon is required before it is fully understood. Prior testing of the TSSI concept allowed extension of fully started inlet operation to regions of significantly reduced supply flow without reducing recovery. The test article was a smaller scale than the present test and was a single duct design. In the present test, the expanded range of stable operation with high recovery was not realized.
Document ID
20030065839
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Carlin, C. M. (Boeing Co. Seattle, WA, United States)
Frisch, I. (Boeing Co. Seattle, WA, United States)
Kolden, J. J. (Boeing Co. Seattle, WA, United States)
Koncsek, J. L. (Boeing Co. Seattle, WA, United States)
Marrs, K. J. (Boeing Co. Seattle, WA, United States)
Mayer, D. W. (Boeing Co. Seattle, WA, United States)
McMahon, S. L. (Boeing Co. Seattle, WA, United States)
Milligan, K. H. (Boeing Co. Seattle, WA, United States)
Sommerfield, D. M. (Boeing Co. Seattle, WA, United States)
Date Acquired
September 7, 2013
Publication Date
July 1, 2003
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:212313
NASA/CR-2003-212313
E-13902
Funding Number(s)
WBS: WBS-22-714-01-38
CONTRACT_GRANT: NAS3-25963
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available