Transonic pressure and load distributions for a group of simulated launch vehicles
Abstract
Pressure and load distributions for a related group of simulated launch vehicle configurations are presented. The configurations were selected so that the nose cone and interstage transition flare components were relatively close to one another and subject to mutual interference effects. Tests extended over a Mach number range from 0.40 to 1.20 at angles of attack from 0 deg to about 10 deg. The test Reynolds numbers, based on main stage diameter, were of the order of 0.00000098.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- April 1980
- Bibcode:
- 1980STIN...8022394K
- Keywords:
-
- Aerodynamic Interference;
- Aircraft Models;
- Launch Vehicle Configurations;
- Load Distribution (Forces);
- Pressure Distribution;
- Transonic Flow;
- Angle Of Attack;
- Mach Number;
- Nose Cones;
- Reynolds Number;
- Stage Separation;
- Tables (Data);
- Launch Vehicles and Space Vehicles