An Experimental Study of Plume Effects on Lifting Re-entry Vehicles
Abstract
Tests were conducted at Mach numbers of 6, 8, and 10 on a representative lifting body entry vehicle and a Mach number of 10 on a flat plate using heated air and other gases to simulate rocket exhaust plumes. Extensive flow separation resulting from the plumes was observed on both configurations during the test program and the most powerful parameters which affected plume induced separation included: model shape, angle of attack, Reynolds number, nozzle expansion ratio, nozzle total pressure, and nozzle gas temperature and specific heat. The flat plate model showed much less flow separation than the delta planform at similar test conditions, however, serious problems in control effectiveness were indicated on both models for the aft mounted elevon. The data did not correlate well with existing semi-empirical correlations developed for control surface induced separation and plume shape. New semi-empirical correlations were developed for predicting plume shape in a region of plume induced separation and for predicting the pressure and the extent of the separated region.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1971
- Accession Number
- AD0516032
Entities
People
- John R. Rausch
Organizations
- General Dynamics