Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 /
A.B. Blair, Jr.

Description

Main Author

Blair, A. B.

Related Names

United States. National Aeronautics and Space Administration.

Language(s)

English

Published

Washington : National Aeronautics and Space Administration ; 1977.

Subjects

Supersonic wind tunnels.
Supersonic speeds.
Lift drag ratio.
Control stability.
Tail assemblies.
Missile design.
Aerodynamic characteristics.
Guided missiles > Guided missiles / Control systems.

Summary

An experimental wind tunnel investigation has been made to determine the longitudinal and lateral aerodynamic stability and control characteristics of two tail fin arrangements of a monowing missile model. Both a conventional cruciform and a low profile tail arrangement were tested. The results indicate that the tail surfaces of both configurations were effective in producing pitch control. It was also concluded that both are effective in producing roll and yaw control that is accompanied by proverse yaw and roll, respectively. The conventional cruciform tail produces the most roll and yaw control.

Note

Issued Aug. 1977.

Physical Description

95 p. : ill. ; 27 cm.

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