Accession Number:

AD0328596

Title:

THE EFFECT OF BOW-SHOCK-FLARE-SHOCK INTERACTION ON THE STATIC LONGITUDINAL STABILITY OF FLARE-STABILIZED BODIES AT HYPERSONIC SPEEDS

Descriptive Note:

Technical memo.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Personal Author(s):

• FITZGERALD, JR., PAUL E.

Report Date:

1962-03-01

Pagination or Media Count:

55.0

Abstract:

Force and moment data from previously published papers were presented to show that flare stabilized bodies at hypersonic speeds experience a decrease or complete loss in static longitudinal stability at certain definite angles of attack. The reason for this decrease in stability and the mechanism by which it occurs is explained. Pressure data and schlieren photographs obtained from tests at a Mach number of 8.5 of two flare-stabilized missile bodies having a fineness ratio of 10 are presented to substantiate this explanation. Tests of these two missiles were conducted over an angle-of-attack range of 0 to 27 degrees at a Reynolds number of approximately 9.3 x 10 to the 6th power based on model length. A decrease in stability of flare-stabilized at hypersonic speeds is shown to be caused by a bow-shock-flare-shock interaction phenomenon. Pressure tests indicate that the nose bluntness of high-fineness-ratio bodies has no influence on the angle of attack at which this phenomenon occurs.

Descriptors:

• *REENTRY VEHICLES
• *PITCH(MOTION)
• *SHOCK WAVES
• *HYPERSONIC CHARACTERISTICS
• MOMENTS
• PRESSURE
• CONICAL BODIES
• WIND TUNNEL MODELS
• SCHLIEREN PHOTOGRAPHY
• NOSE CONES
• PITCH(MATERIAL)

Subject Categories:

• Test Facilities, Equipment and Methods
• Guided Missile Dynamics, Configurations and Control Surfaces
• Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE