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Prediction of span loading of straight-wing/propeller combinations up to stallA method is presented for calculating the spanwise lift distribution on straight-wing/propeller combinations. The method combines a modified form of the Prandtl wing theory with a realistic representation of the propeller slipstream distribution. The slipstream analysis permits calculations of the nonuniform axial and rotational slipstream velocity field of propeller/nacelle combinations. This nonuniform field was then used to calculate the wing lift distribution by means of the modified Prandtl wing theory. The theory was developed for any number of nonoverlapping propellers, on a wing with partial or full-span flaps, and is applicable throughout an aspect ratio range from 2.0 and higher. A computer program was used to calculate slipstream characteristics and wing span load distributions for a number of configurations for which experimental data are available, and favorable comparisons are demonstrated between the theoretical predictions and the existing data.
Document ID
19760004918
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mcveigh, M. A.
(United Technology Corp. Blue Bell, PA, United States)
Gray, L.
(United Technology Corp. Blue Bell, PA, United States)
Kisielowski, E.
(United Technology Corp. Blue Bell, PA, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1975
Publication Information
Publisher: NASA
Subject Category
Aeronautics (General)
Report/Patent Number
UTR-004
NASA-CR-2602
Report Number: UTR-004
Report Number: NASA-CR-2602
Accession Number
76N12006
Funding Number(s)
CONTRACT_GRANT: NAS1-12238
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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