The Design of Constant-volume Missile Fuselages Having Minimum Drag at Supersonic Speeds

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Rand Corporation, 1948 - Aerodynamics, Supersonic - 60 pages
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The factors influencing the design of missile fuselages are discussed in relation to the problem of obtaining an optimum design from the drag standpoint. On the basis of the factors and assumptions given, a method is developed for determining the fineness ratio that results in minimum drag for a constant-volume fuselage flying at a fixed angle of attack and Mach number. Using drag data for the attitude of zero angle of attack at Mach numbers between 1.5 and 5, numerical values of optimum fineness ratio are presented for the case of a practical, axially-symmetric fuselage whose shape consists of a conical nose of fixed proportions attached to a cylindrical afterbody. Procedures are indicated for the extension of the results of the study to specific designs of the subject or other geometrical configurations.

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Contents

Section 1
2
Section 2
6
Section 3
14

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