Accession Number:

AD0258299

Title:

TRANSONIC WIND-TUNNEL INVESTIGATION OF THE FIN LOADS ON A 1/8-SCALE MODEL SIMULATING THE FIRST STAGE OF THE SCOUT RESEARCH VEHICLE

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

• KELLY,THOMAS C.

Report Date:

1961-06-01

Pagination or Media Count:

1.0

Abstract:

An investigati n to determine the fin loads on a 18-scale model simulating the first stage of the Scout research vehicle was made in the Langley 8-ft transonic tunnel at Mach numbers from 0.40 to 1.20. Tests were conducted over an angleof-attack range from about -10 to 10 degrees and at a Reynolds number per ft of approximately 3.5 x 10 to the 6th power. Results of the tests indicate that for a given angle of attac , negative tip-control deflections caused decrea es in normal-force and fin-bending-moment coefficients and increases in pitching-moment coefficient, as would be expected. The effects were slight at a model angle of attack of -10 degrees where tip-c ntrol stall had probably occurred but increased with an increase in angle of attack. Author

Descriptors:

• *TEST VEHICLES
• ROLL
• SIMULATION
• SPACE PROBES
• STAGING

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE