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Ground simulation and tunnel blockage for a swept, jet-flapped wing tested to very high lift coefficientsGround effects experiments and large/small tunnel interference studies were carried out on a model with a 20 inch (50.8 cm) 25 degree swept wing. The wing is slatted, has a 60 degree knee-blown flap and can be fitted with unflapped tips. A tail rake of pitch-yaw probes can be fitted to the fuselage. Certain check tests were also made with a very similar straight-wing model.
Document ID
19780005065
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hackett, J. E. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Boles, R. A. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-152032
Report Number: NASA-CR-152032
Accession Number
78N13008
Funding Number(s)
CONTRACT_GRANT: NAS2-9155
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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