Statistical Determination of the Lift and Drag of Fighter Aircraft.
Abstract
Multiple linear regression analysis was used to develop two statistical equations representing the coefficients of lift and drag due to lift as functions of 14 non-dimensional geometric parameters and Reynolds number. A set of regression coefficients were computed for each of the parameters to permit prediction of the coefficients of lift and drag due to lift for Mach numbers in the range of 0.4 to 2.5 and angles of attack in the range of 0 to 18 degrees. A computer program is available to perform the required computations and plot the resulting drag polars. The wind tunnel data used in the regression analysis consisted of 104 configurations and a computer program is available for recomputing the regression coefficients as new data becomes available. Error less than 10 percent can be expected except in the transonic speed range. Results were compared to wind tunnel test data for the F-5E and F-8U aircraft. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1972
- Accession Number
- AD0769491
Entities
People
- Thomas A. Tomasetti
Organizations
- Air Force Institute of Technology