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Calculation of viscous effects on transonic flow for oscillating airfoils and comparisons with experimentA method is described for calculating unsteady transonic flow with viscous interaction by coupling a steady integral boundary-layer code with an unsteady, transonic, inviscid small-disturbance computer code in a quasi-steady fashion. Explicit coupling of the equations together with viscous -inviscid iterations at each time step yield converged solutions with computer times about double those required to obtain inviscid solutions. The accuracy and range of applicability of the method are investigated by applying it to four AGARD standard airfoils. The first-harmonic components of both the unsteady pressure distributions and the lift and moment coefficients have been calculated. Comparisons with inviscid calcualtions and experimental data are presented. The results demonstrate that accurate solutions for transonic flows with viscous effects can be obtained for flows involving moderate-strength shock waves.
Document ID
19870018189
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Howlett, James T. (NASA Langley Research Center Hampton, VA, United States)
Bland, Samuel R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2731
L-16289
NAS 1.60:2731
Accession Number
87N27622
Funding Number(s)
PROJECT: RTOP 505-63-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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