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Airfoil section data obtained in the NACA variable-density tunnel as affected by support interference and other corrections
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Author and Affiliation: Jacobs, Eastman N
Abbott, Ira H
Abstract: The results of an investigation of the effect of support interference on airfoil drag data obtained in the variable-density tunnel are presented. As a result of the support interference, previously published airfoil data from the variable-density tunnel have shown too large drag coefficients and too large a rate of increase of drag coefficients and too large a rate increase of drag coefficients with airfoil thickness. The practical effect of the corrections on the choice of the optimum section is briefly considered and corrected data for a selected list of airfoils are presented as a convenience to the designer. Methods of correcting published data for other airfoils are presented.
Publication Date: Jan 01, 1939
Document ID:
19930091744
(Acquired Sep 01, 1996)
Accession Number: 93R21034
Report/Patent Number: NACA-TR-669
Publisher Information: United States
Organization Source: National Advisory Committee for Aeronautics. Langley Aeronautical Lab.; Langley Field, VA, United States
Description: 32p; In English
Relation Information: NACA Technical Report 669.
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AERODYNAMIC COEFFICIENTS; AERODYNAMIC DRAG; AERODYNAMIC INTERFERENCE; AIRFOIL PROFILES; AIRFOILS; BIPLANES; DRAG COEFFICIENTS; LIFT; LIFT DRAG RATIO; STRUTS; SUPPORTS; THICKNESS; WIND TUNNEL TESTS
Miscellaneous Notes: Also bound with NACA Annual Report 25, p. 507-538.
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