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An experimental investigation of the aerodynamics and cooling of a horizontally-opposed air-cooled aircraft engine installationA flight-test based research program was performed to investigate the aerodynamics and cooling of a horizontally-opposed engine installation. Specific areas investigated were the internal aerodynamics and cooling mechanics of the installation, inlet aerodynamics, and exit aerodynamics. The applicable theory and current state of the art are discussed for each area. Flight-test and ground-test techniques for the development of the cooling installation and the solution of cooling problems are presented. The results show that much of the internal aerodynamics and cooling technology developed for radial engines are applicable to horizontally opposed engines. Correlation is established between engine manufacturer's cooling design data and flight measurements of the particular installation. Also, a flight-test method for the development of cooling requirements in terms of easily measurable parameters is presented. The impact of inlet and exit design on cooling and cooling drag is shown to be of major significance.
Document ID
19810013485
Document Type
Contractor Report (CR)
Authors
Miley, S. J. (Texas A and M Univ. College Station, United States)
Cross, E. J., Jr. (Texas A and M Univ. College Station, United States)
Owens, J. K. (Mississippi State Univ. Mississippi State, MS, United States)
Lawrence, D. L. (Turbo West Corporate Aircraft Center Broomfield, Colo., United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1981
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-CR-3405
Funding Number(s)
CONTRACT_GRANT: NSG-1083
PROJECT: RTOP 505-41-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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