An experimental study on the induced rolling moment due to wing-tail interference and roll-controllable two-stage rocket
Abstract
A wind tunnel investigation of a roll-controllable two-stage rocket model was made at free-stream Mach numbers from 0.5 to 2.5. The model has ailerons on front-fins to generate rolling moment and free-rolling tail-fins to eliminate the effect of the induced rolling moment on tail-fins. The results confirmed the feasibility of this type of roll-controllable rocket. The characteristics of the induced rolling moment were investigated by tests of a model with fixed tail-fins. The characteristics were compared with theoretical results based on the strip-theory. Values of roll-damping coefficient of the tail-fins were obtained by analyzing their rolling rate. The effect of the free-rolling tail-fins on other aerodynamic characteristics, such as normal force coefficient, center of pressure and axial force coefficient were also evaluated. A computer simulation of the rolling motion of the TT-500A rocket, which has a similar configuration to the present model, was made based on the results of the present study, whose results agreed well with the flight-data.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- December 1983
- Bibcode:
- 1983STIN...8421599S
- Keywords:
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- Fins;
- Mach Number;
- Rolling Moments;
- Tail Assemblies;
- Wind Tunnel Tests;
- Aircraft Models;
- Computerized Simulation;
- Feasibility Analysis;
- Launch Vehicles and Space Vehicles