Accession Number:

AD0829015

Title:

1/30 SCALE XSM-65A MISSILE BASE RECIRCULATION MODEL TESTS,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV

Personal Author(s):

Report Date:

1958-01-31

Pagination or Media Count:

44.0

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

Subject Categories:

  • Surface-Launched Guided Missiles
  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE