DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click HERE
to register or log in.
TRANSONIC WIND-TUNNEL INVESTIGATION OF THE FIN LOADS ON A 1/8-SCALE MODEL SIMULATING THE FIRST STAGE OF THE SCOUT RESEARCH VEHICLE
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
Pagination or Media Count:
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
APPROVED FOR PUBLIC RELEASE