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Wind tunnel test results for the direction controlled antitank DCAT missile at Mach numbers from 0.64 to 2.50Wind tunnel test results are presented to show aerodynamic characteristics over the Mach number range of 0.64 to 2.50 of the DCAT missile. Data are presented showing the interference created by the rear mounted reaction control system. Two candidate fins were installed on the model during tests: a flat folding fin and a curved wrap around fin.
Document ID
19750002949
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Martin, T. A. (Chrysler Corp. New Orleans, LA, United States)
Spring, D. J. (Chrysler Corp. New Orleans, LA, United States)
Date Acquired
September 3, 2013
Publication Date
October 12, 1973
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AD-784121
NASA-CR-140750
RD-73-27
Report Number: AD-784121
Report Number: NASA-CR-140750
Report Number: RD-73-27
Accession Number
75N11021
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
PROJECT: DA PROJ. 1M2-62303-A-214
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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