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Light aircraft lift, drag, and moment prediction: A review and analysisThe historical development of analytical methods for predicting the lift, drag, and pitching moment of complete light aircraft configurations in cruising flight is reviewed. Theoretical methods, based in part on techniques described in the literature and in part on original work, are developed. These methods form the basis for understanding the computer programs given to: (1) compute the lift, drag, and moment of conventional airfoils, (2) extend these two-dimensional characteristics to three dimensions for moderate-to-high aspect ratio unswept wings, (3) plot complete configurations, (4) convert the fuselage geometric data to the correct input format, (5) compute the fuselage lift and drag, (6) compute the lift and moment of symmetrical airfoils to M = 1.0 by a simplified semi-empirical procedure, and (7) compute, in closed form, the pressure distribution over a prolate spheroid at alpha = 0. Comparisons of the predictions with experiment indicate excellent lift and drag agreement for conventional airfoils and wings. Limited comparisons of body-alone drag characteristics yield reasonable agreement. Also included are discussions for interference effects and techniques for summing the results above to obtain predictions for complete configurations.
Document ID
19750016605
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Smetana, F. O.
(North Carolina State Univ. Raleigh, NC, United States)
Summey, D. C.
(North Carolina State Univ. Raleigh, NC, United States)
Smith, N. S.
(North Carolina State Univ. Raleigh, NC, United States)
Carden, R. K.
(North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1975
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2523
Accession Number
75N24677
Funding Number(s)
PROJECT: RTOP 760-60-01-0900
CONTRACT_GRANT: NGR-34-002-179
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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