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Rotary balance data for a typical single-engine general aviation design for an angle-of-attack range of 8 degrees to 35 degrees, 3. Effect of wing leading-edge modifications, model AAerodynamic characteristics obtained in a rotational flow environment utilizing a rotary balance located in the Langley spin tunnel are presented in plotted form for a 1/5 scale, single-engine, low-wing, general aviation airplane model. The configurations tested included the basic airplane, sixteen wing leading-edge modifications and lateral-directional control settings. Data are presented for all configurations without analysis for an angle of attack range of 8 deg to 35 deg and clockwise and counter-clockwise rotations covering an Omega b/2v range from 0 to 0.85. Also, data are presented above 35 deg of attack for some configurations.
Document ID
19800003810
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bihrle, W., Jr. (Bihrle Applied Research, Inc. Jericho, NY, United States)
Mulcay, W. (Bihrle Applied Research, Inc. Jericho, NY, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3102
Accession Number
80N12060
Funding Number(s)
CONTRACT_GRANT: NAS1-14849
PROJECT: RTOP 505-10-13-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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