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Accession Number:
AD0481301
Title:
FORCE TESTS ON A SEPARABLE-NOSE CREW ESCAPE CAPSULE WITH COLD FLOW ROCKET JET SIMULATION AT MACH NUMBERS 1.5 THROUGH 6
Corporate Author:
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Report Date:
1966-04-01
Abstract:
Static force tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility on a separable-nose crew escape capsule having cold flow simulation of the separation rocket jet plume. Data were obtained at Mach numbers from 1.5 to 6 at angles of attack from -30 to 30 deg and angles of sideslip from -15 to 15 deg. Reynolds number, based on a model length of 18.1 in., ranged from 1,360,000 to 12,300,000. Selected results are presented showing the effects of the rocket exhaust jet on the static stability and drag characteristics of the vehicle.
Descriptive Note:
Technical rept. 2 Jun 1965-17 Jan 1966 on Phase 1
Supplementary Note:
Prepared in cooperation with ARO, Inc., Tullahoma, Tenn.
Pages:
0035
Distribution Statement:
Approved for public release; distribution is unlimited.
Contract Number:
AF 40(600)-1200
File Size:
1.76MB
