Accession Number : AD0439948


Title :   JET INTERFERENCE DURING STAGE SEPARATION AT VERY HIGH ALTITUDES


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Binion, Jr, T W


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/439948.pdf


Report Date : May 1964


Pagination or Media Count : 72


Abstract : Pressure and force measurements were obtained on two upper stage and three lower stage missile models during simulated stage separation. The upper stage rocket engine exhaust was simulated with high pressure carbon dioxide. Data were also obtained at a limited number of test conditions using gaseous nitrogen to simulate the rocket engine exhaust. Data were obtained at ten separation distances with an upper stage nozzle exit pressure ratio variation from 5.5 to 12,914. The test cell pressure ranged from 1.2 to 6300 microns of mercury, which corresponds to an altitude range from 290,000 to 106,000 ft. The results indicate that interference on the upper stage is dependent on the lower stage configuration and upper stage chamber pressure and is independent of the ambient pressure.


Descriptors :   *AERODYNAMIC CONFIGURATIONS , *STAGING , ALTITUDE CHAMBERS , CARBON DIOXIDE , EXPERIMENTAL DATA , GUIDED MISSILE MODELS , HIGH ALTITUDE , INTERFERENCE , LOW PRESSURE , MODEL TESTS , OPTIMIZATION , PHOTOGRAPHS , PRESSURE , SEPARATION , SIMULATION , TEST METHODS , THRUST


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE