Accession Number : ADA098822


Title :   The Influence of Heat Transfer on the Drag of Airfoils.


Descriptive Note : Final rept. May 79-Sep 80,


Corporate Author : OHIO STATE UNIV COLUMBUS AERONAUTICAL AND ASTRONAUTICAL RESEARCH LAB


Personal Author(s) : Lee,John D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a098822.pdf


Report Date : Apr 1981


Pagination or Media Count : 47


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)


Descriptors :   *HEAT TRANSFER , *AIRFOILS , *AERODYNAMIC DRAG , *BOUNDARY LAYER TRANSITION , PRESSURE GRADIENTS , TURBULENT BOUNDARY LAYER , SUPERCRITICAL FLOW , SUBSONIC FLOW , AEROTHERMODYNAMICS , SURFACE TEMPERATURE , TRANSONIC FLOW , DRAG REDUCTION , LAMINAR BOUNDARY LAYER


Subject Categories : Fluid Mechanics
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE