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Additional testing of the inlets designed for a tandem fan V/STOL nacelleThe wind tunnel testing of a scale model of a tandem fan nacelle designed for a type (subsonic cruise) V/STOL aircraft configuration is discussed. The performance for the isolated front inlet and for the combined front and aft inlets is reported. Model variables include front and aft inlets with aft inlet variations of short and long aft inlet cowls, with a shaft simulator and diffuser vortex generators, cowl lip fillets, and nacelle strakes. Inlet pressure recovery, distortion, and inlet angle-to-attack separation limits were evaluated at tunnel velocity from 0 to 240 knots, angles-of-attack from -10 to +40 degrees and inlet flow rates corresponding to throat Mach number from 0.0 to 0.6. Combined nacelle pitch and yaw runs up to 30 deg. were also made.
Document ID
19810017539
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ybarra, A. H. (Vought Corp. Dallas, TX, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-165310
TR-2-53020/IR-52726
Accession Number
81N26075
Funding Number(s)
PROJECT: RTOP 505-42-62
CONTRACT_GRANT: NAS3-21468
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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