TRANSONIC WIND-TUNNEL INVESTIGATION OF THE FIN LOADS ON A 1/8-SCALE MODEL SIMULATING THE FIRST STAGE OF THE SCOUT RESEARCH VEHICLE
Abstract
An investigati n to determine the fin loads on a 1/8-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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1961
- Accession Number
- AD0258299
Entities
People
- Thomas C. Kelly
Organizations
- National Aeronautics and Space Administration