Accession Number : AD0769491
Title : Statistical Determination of the Lift and Drag of Fighter Aircraft.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
Personal Author(s) : Tomasetti,Thomas A.
Report Date : JUN 1972
Pagination or Media Count : 97
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)
Descriptors : (*Jet fighters, Lift to drag ratio), Wing body configurations, Angle of attack, Lift, Aerodynamic drag, Regression analysis, Computerized simulation
Subject Categories : Aerodynamics
Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE