A new, improved method for separating turbulent boundary layer for aerodynamic performance prediction of trailing edge stall airfoilsA method based on integral techniques is presented to determine the turbulent separation location and separation pressure for trailing edge stall airfoils exhibiting extensive separated flow regions during prestall and poststall conditions. The method and experimental laser velocimetry data in the turbulence amplification region are used to establish a relationship between fluctuating velocity components and mean velocity in the boundary layer. The method is demonstrated for symmetrical, cambered, conventional and supercritical airfoils in the 5-to-21-percent thickness ratio range, and over a Reynolds number range of 2 to 22 million. Good agreement with experimental data is found, and the method is used in conjunction with the NASA Multi-Component Airfoil Computer Program to predict maximum L/D ratios and maximum section/lift coefficients.
Document ID
19860064852
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goradia, S. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Morgan, H. L., Jr. (NASA Langley Research Center Hampton, VA, United States)