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The aerodynamic characteristics of large angled cones with retrorocketsAnalytical and experimental phases of the subject investigation are described. The analytical program for the single jet determines the terminal shock location, the jet boundary, the interface profile, the bow shock profile, the shear layer growth and the dead air region pressure. The experimental program described was conducted over the range from free stream Mach 0.4 to 2.0 at angles-of-attack up to 18 deg and at thrusting coefficients up to C sub T = T/q sub infinity A sub m = 30. Variables investigated included aeroshell angle, number of nozzles, engine thrust, size of nozzles, nozzle throttling and gas composition. The influence of these variables on the aeroshell stability, drag, and loads was determined by integrating pressure measurements on the aeroshell. The total system forces consist of components due to pure thrust and components due to pressure on the aeroshell arising from the jet-free stream interaction. Shadowgraphs provided flow field geometries which proved to be within 10% of those predicted analytically.
Document ID
19720005324
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Jarvinen, P. O. (Mithras, Inc. Cambridge, MA, United States)
Adams, R. H. (Mithras, Inc. Cambridge, MA, United States)
Date Acquired
September 2, 2013
Publication Date
February 1, 1970
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-124720
MC-70-3001-R2(BNY)
Accession Number
72N12973
Funding Number(s)
CONTRACT_GRANT: NAS7-576
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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