A wind tunnel test of a one-thirtieth scale 'B' series Atlas missile with operating rocket engines was run at the NACA Lewis 8-by-6 foot supersonic wind tunnel. The primary test objective was to determine the amount of rocket and gas turbine exhaust recirculation into the missile base region; a secondary objective was to determine the effect of operating rockets on missile skin and base pressure. Only the pressure data are considered in this report. (Author)
A Preliminary Analysis of Rocket Exhaust Jet Effects on Missile Skin and Base Pressures at Mach 0.6 and 1.5 - Naca Lewis Flight Propulsion Laboratory Test 2093
1958
16 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Fluid Mechanics , Liquid propellant rocket engines , Captive tests , Surface to surface missiles , Model tests , Wind tunnel models , Supersonic characteristics , Secondary flow , Base pressure , Airframes , Gas turbines , Exhaust gases , Base flow , Force(Mechanics) , Scale , Rocket nozzles , Thermal radiation , Turbojet exhaust nozzles , Sustainer engines , Booster rockets , Distribution , Pressure , Skin(Structural member)
Propulsion wind tunnel at naca lewis laboratory
NTRS | 1956
|Propulsion wind tunnel at NACA Lewis Laboratory
Engineering Index Backfile | 1956
|DataCite | 1885