Accession Number : AD0829015
Title : 1/30 SCALE XSM-65A MISSILE BASE RECIRCULATION MODEL TESTS,
Corporate Author : GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV
Personal Author(s) : Hendershot, K. C. ; Leo, P. P.
Report Date : 31 JAN 1958
Pagination or Media Count : 44
Abstract : As a result of the flight test observations, a scale model test program was initiated at the Thermodynamics Laboratories to determine whether recirculation of the turbine exhaust gases could occur under simulated flight conditions and to arrive at a suitable 'fix' if a problem was found to exist. One-thirtieth scale model tests of the Atlas missile base and turbine exhaust duct configuration have indicated a bent duct directed into the free stream should prevent recirculation and burning of hot turbine exhaust gases during low altitude, subsonic flight. A straight exhaust duct, extended approximately eight feet downstream of the base of the missile, would probably also provide reasonable assurance of no turbine exhaust gas recirculation. (Author)
Descriptors : *GAS TURBINES), (*SURFACE TO SURFACE MISSILES, (*EXHAUST GASES, GAS FLOW), MODEL TESTS, GAS GENERATING SYSTEMS, DUCTS, BASE FLOW, FLIGHT TESTING, SIMULATION, SCALE, TEST METHODS, BURNING RATE, LOW ALTITUDE, TURBOPUMPS, TURBOJET EXHAUST NOZZLES.
Subject Categories : Surface-launched Guided Missiles
Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE