Accession Number:

AD0328597

Title:

TRANSONIC DYNAMIC LONGITUDINAL STABILITY CHARACTERISTICS OF SIX BALLISTIC REENTRY CONFIGURATIONS DESIGNED FOR SUPERSONIC IMPACT

Descriptive Note:

Technical memo.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Personal Author(s):

• HILLJE, ERNEST R.
• KILGORE, ROBERT A.

Report Date:

1962-03-01

Pagination or Media Count:

17.0

Abstract:

An investigation has been made in the Langley 8-foot transonic pressure tunnel to determine the damping-in-pitch and the oscillatory longitudinal stability characteristics of six bluntnose cylinder-flare reentry configurations that were designed for supersonic impact. Tests were made at Mach numbers from 0.80 to 1.15 and at mean angles of attack from 0 to 14 degrees. Reynolds numbers, based on 0.333 foot, varied from 0.62 to 0.69 times 10 to the 6th power. The amplitude of the forced oscillation was 2 degrees with reduced frequencies from 0.012 to 0.036. Some of the effects of flare angle, nose shape, and fins are noted.

Descriptors:

• *NOSE CONES
• *REENTRY VEHICLES
• DAMPING
• MOMENTS
• MODEL TESTS
• AERODYNAMIC CHARACTERISTICS
• SUPERSONIC FLOW
• OSCILLATION
• BLUNT BODIES
• WIND TUNNEL MODELS
• SURFACE TO SURFACE
• TRANSONIC CHARACTERISTICS
• PITCH(MOTION)
• STABILITY
• GUIDED MISSILES

Subject Categories:

• Guided Missile Dynamics, Configurations and Control Surfaces
• Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE