AERODYNAMIC LOADING CHARACTERISTICS AT MACH NUMBERS FROM 0.80 TO 1.20 OF A 1/10-SCALE THREE-STAGE SCOUT MODEL
Abstract
Aerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach num ers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angleof-attack range from -8 to 8 degrees at an average test Reynolds number per foot of about 4.0 x 10 to the 6th power. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carr over from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1961
- Accession Number
- AD0263076
Entities
People
- Thomas C. Kelly
Organizations
- National Aeronautics and Space Administration