An experimental and theoretical comparison at M=4 of the lift-to-drag ratio of some possible aircraft shapes

Abstract

Summary. An experimental and theoretical comparison has been made between two different methods of combining excess cross-sectional area (due to the engine exhaust nozzle exit being larger than the intake entry) with the volume and lifting surface elements in an aircraft configuration. Comparisons of measured and calculated values of (L/D)max have been made using linear theory and in general fair agreement is achieved. A systematic study of the effect of varying the proportions of the configurations studied leads to finding the optimum proportions for either approach.