Theorems Concerning the Reduction of Drag for Supersonic Aircraft

Citation

Rodriguez, Alexander Martin (1956) Theorems Concerning the Reduction of Drag for Supersonic Aircraft. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/R1JD-WT10. https://resolver.caltech.edu/CaltechETD:etd-08302006-133358

Abstract

In this report the problem of drag reduction or minimization for aircraft in supersonic flight is investigated within the framework of linearized theory of inviscid flow for fixed flight Mach number. General theorems applicable to complete aircraft configurations are developed. These theorems state defining properties of distributions of thickness and normal force restricted to a particular region of the aircraft configurations that minimize the drag of the complete aircraft under the condition that the distribution of thickness and normal force on the remainder of the aircraft is specified in advance. These optimum distributions are further required to satisfy some of the various types of constraints that are commonly specified for aircraft. The problem of finding the optimum distribution of thickness, lift and sideforce on a slender body of revolution is also studied under the assumption that the body carries no total lift or sideforce and can be represented by placing the distributions along the body axis. The case for which the Mach envelope of the body does not include all of the remaining portion of the aircraft configuration, upon with the thickness and normal force are specified, is solved. This solution covers the previously known case for which the Mach envelope of the body includes the entire aircraft.

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