Accession Number : AD0285280

Title :   AN EXPERIMENTAL STUDY OF AERODYNAMICALLY VARIABLE THROAT AREA (AVT) NOZZLES

Corporate Author : OKLAHOMA STATE UNIV STILLWATER

Personal Author(s) : JACKOMIS,WILLIAM N.

Report Date : AUG 1962

Pagination or Media Count : 1

Abstract : A study was made of thrust nozzles having aerodynamically variable throat areas (AVT Nozzles), developed by providing injection of a secondary gas at high velocity at the throat. If this were applied to a solid propellant rocket having a pressure exponent near unity, the smaller throat area would result in a greatly increased chamber pressure, mass flow rate, and thrust. An approximate analysis of this effect, cold air test results for 3 AVT nozzles having radial secondary injection angles of 0, +15, and -15 degrees relative to the throat plane, and a specific numerical example are presented. Test results indicated that area variation by secondary throat injection was feasible. It is shown that the pressure in the combustion chamber of a solid-propellant rocket is sufficient to provide secondary fluid, if the attendant nozzle heating can be tolerated. Conversely, if cold secondary fluid is provided, a significant nozzle throat cooling effect should be possible. (Author)

Descriptors :   *GASES, *ROCKET NOZZLES, AERODYNAMIC CHARACTERISTICS, COMBUSTION CHAMBER GASES, CONTROL SYSTEMS, EXHAUST GASES, GAS FLOW, INJECTION, MODEL TESTS, PRESSURE, SECONDARY INJECTION, TEST METHODS, THRUST

Distribution Statement : APPROVED FOR PUBLIC RELEASE