ATMOSPHERIC ENTRY TEST FACILITIES: LIMITATIONS OF CURRENT TECHNIQUES AND PROPOSAL FOR A NEW TYPE FACILITY
Abstract
The theoretical and practical limitations of various types of wind tunnels, aeroballistic ranges, and counterflow facilities are examined in terms of velocity-altitude duplication. It is concluded that these aerodynamic test facilities can not provide the desired low altitude, orbital-to-escape-velocity capability to test the atmospheric entry phenomena associated with large models. It is suggested that this capability might be achieved by the application of rocket propulsion to aeroballistic-range-type testing. The proposed system for launching models consists of a multistage rocket booster travelling inside a straight tube evacuated to a low pressure. On attainment of the desired velocity, the model proceeds into the test range which is a variable pressure tank that is instrumented for aerophysical, erosion, impact, stability, and drag studies. It is estimated that model/sabot packages weighing from 10 to 1 lb could be launched at speeds from 25 to 35 kft/sec, respectively. The proposed test technique as applied to lower hypersonic speeds, to the duplication of high Reynolds numbers, and to hypersonic ramjet testing is discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1969
- Accession Number
- AD0681487
Entities
People
- J. Lukasiewicz
Organizations
- Arnold Engineering Development Complex