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HSCT Propulsion Airframe Integration StudiesThe Lockheed Martin spillage study was a substantial effort and is worthy of a separate paper. However, since a paper was not submitted a few of the most pertinent results have been pulled out and included in this paper. The reader is urged to obtain a copy of the complete Boeing Configuration Aerodynamics final 1995 contract report for the complete Lockheed documentation of the spillage work. The supersonic cruise studies presented here focus on the bifurcated - axisymmetric inlet drag delta. In the process of analyzing this delta several test/CFD data correlation problems arose that lead to a correction of the measured drag delta from 4.6 counts to 3.1 counts. This study also lead to much better understanding of the OVERFLOW gridding and solution process, and to increased accuracy of the force and moment data. Detailed observations of the CFD results lead to the conclusion that the 3.1 count difference between the two inlet types could be reduced to approximately 2 counts, with an absolute lower bound of 1.2 counts due to friction drag and the bifurcated lip bevel.
Document ID
20000044624
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Chaney, Steve (Boeing Aerospace Co. Seattle, WA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop
Issue: Part 1
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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