The Performance of a Supersonic Airplane

Author: Weldon, Thomas Franklin

Year: 1947

Degree: Engineer's thesis

Advisor: Puckett, Allen E.

Committee Member: Unknown, Unknown

Option: Electrical Engineering; Aeronautics

DOI: 10.7907/T271-MK09

Abstract

This thesis is primarily a survey of the methods of calculating drag and performance of an airplane capable of supersonic flight. As a basis of presentation of the findings of this survey the drag and performance calculations are worked out for a single place airplane which has a rocket power plant, sweptback wings and other low drag features. These calculations reveal that this airplane should be able to attain a Mach number of 2 at an altitude of 42,000 feet.

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