The Influence of Heat Transfer on the Drag of Airfoils.
- 1 April 1981
- report
- Published by Defense Technical Information Center (DTIC)
Abstract
An experimental and theoretical study was performed to determine the effects of surface temperature on the drag of airfoils. Models of an aft-loaded profile and of a NACA 65A413 were tested with separate models providing pressure distributions and drag data from cooling or heating at a Mach number of 0.4 and Reynolds number of 2,500,000. Simultaneously an airfoil boundary layer analysis was performed using available theories and empirical correlations for laminar, transitional and turbulent boundary layers. Cooling was found to provide a lower drag and heating a higher value, as expected, for both profiles and the reduction by cooling was substantial for the aft-loaded profile at the condition tested. The measurements agreed well with the theoretical predictions which may then be used to evaluate the effects of both heat transfer and pressure gradients on airfoil transition and drag. (Author)Keywords
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