STATIC LONGITUDINAL STABILITY OF A ROCKET VEHICLE HAVING A REAR-FACING STEP AHEAD OF THE STABILIZING FINS
Abstract
Tests were conducted at Mach numbers of 3.96 and 4.65 in the Langley Unitary Plan wind tunnel to determine the static longitudinal stability characteristics of a fin-stabilized rocket-vehicle configuration with a rearward facing step located upstream of the fins. Two fin sizes and planforms, a delta and a clipped delta, were tested. The angle of attack was varied from 6 to -6 degrees and the Reynolds number based on model length was about 10 times 10 to the 6th power. The configuration with the larger fins (clipped delta) had a center of pressure slightly rearward of and an initial normal-force-curve slope slightly higher than that of the configuration with the smaller fins (delta) as would be expected. Calculations of the stability parameters gave a slightly lower initial slope of the normal-force curve than measured data. The calculated center of pressure agreed well with the measured data. Measured and calculated increments in the initial slope of the normalforce curve and in the center of pressure, due to changing fins, were in excellent agreement indicating that separated flow downstream of the step did not influence flow over the fins. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1961
- Accession Number
- AD0266833
Entities
People
- Robert J. Keynton
Organizations
- National Aeronautics and Space Administration