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Combined linear theory/impact theory method for analysis and design of high speed configurationsPressure distributions on a wing body at Mach 4.63 are calculated. The combined theory is shown to give improved predictions over either linear theory or impact theory alone. The combined theory is also applied in the inverse design mode to calculate optimum camber slopes at Mach 4.63. Comparisons with optimum camber slopes obtained from unmodified linear theory show large differences. Analysis of the results indicate that the combined theory correctly predicts the effect of thickness on the loading distributions at high Mach numbers, and that finite thickness wings optimized at high Mach numbers using unmodified linear theory will not achieve the minimum drag characteristics for which they are designed.
Document ID
19800021772
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Brooke, D. (McDonnell-Douglas Research Labs. Saint Louis, MO, United States)
Vondrasek, D. V. (McDonnell-Douglas Research Labs. Saint Louis, MO, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3314
Accession Number
80N30273
Funding Number(s)
CONTRACT_GRANT: NAS1-15535
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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