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Unsteady transonic small disturbance theory with strong shock wavesA theory to correct the transonic small disturbance (TSD) equation to treat strong shock waves in unsteady flow is developed. The technique involves the addition of higher order terms, which are formally of negligible magnitude, to the low frequency TSD equation. These terms are then chosen such that any shock waves in the flow have strengths approximately equal to the appropriate Rankine-Hugoniot shock strength. Two correcting approaches are investigated. The first is to derive a correction for the mean steady flow and then simply use this corrected form for oscillatory flows. The second is to derive a correction for both steady and oscillatory parts of the flow. This second development is the most satisfactory and comparisons of the present results with Euler equation results are generally favorable, particularly regarding shock location, although there are some discrepancies in the pressure distribution in the leading edge region.
Document ID
19810010494
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Kerlick, G. D. (NASA Ames Research Center Moffett Field, CA, United States)
Nixon, D. (NASA Ames Research Center Moffett Field, CA, United States)
Ballhaus, W. F., Jr. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166157
NEAR-TR-230
Accession Number
81N19020
Funding Number(s)
CONTRACT_GRANT: NASA ORDER A-70215-B
CONTRACT_GRANT: NASA ORDER A-77455-B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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