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Effect on Drag of Longitudinal Positioning of Half-Submerged and Pylon-Mounted Douglas Aircraft Stores on a Fuselage with and without Cavities between Mach Numbers 0.9 and 1.8

Description: From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities."
Date: July 15, 1954
Creator: Hoffman, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department

The effect of nacelle location on the zero-lift drags of 45 degree sweptback wing-body configurations having boattail and cylindrical afterbodies as determined by flight tests at transonic speeds

Description: Report presenting the effects of nacelle location on the zero-lift drag of 45 degree sweptback wing-body combinations with boattail and cylindrical afterbodies at a range of Mach and Reynolds numbers. The nacelles were located at three different areas and the afterbody shape was also altered by replacing the boattail afterbody with a cylinder. Results regarding faired curves of the variations of total drag, base drag, and fin drag coefficients, and applicability of the transonic area rule are provided.
Date: March 25, 1954
Creator: Hoffmann, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department

Transonic flight tests to determine zero-lift drag and pressure recovery of nacelles located at the wing root on a 45 degree sweptback wing and body configuration

Description: Report presenting the zero-lift drag of a sweptback wing and body configuration with nacelles as determined by flight tests of rocket-propelled models at Mach numbers 0.8 to 1.3. Results regarding pressure recovery are also provided.
Date: September 29, 1953
Creator: Hoffman, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department

Flight investigation of the supersonic area rule for a straight wing-body configuration at Mach numbers between 0.8 and 1.5

Description: Report discussing an investigation of the supersonic area rule using rocket-propelled zero-lift models of straight wing-body configurations at a range of Mach and Reynolds numbers. The body was modified with symmetrical indentations according to area-rule considerations in order to reduce wave drag. The indentations were found to have an effect at Mach numbers 1.10 and 1.41 but did not have any benefit above Mach number 1.3.
Date: April 29, 1955
Creator: Hoffman, Sherwood; Wolff, Austin L. & Faget, Maxime A.
Partner: UNT Libraries Government Documents Department