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Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Description: Report presenting a free-flight investigation of a rocket-propelled model at a range of Mach numbers from 0.7 to 1.53 to determine the drag at zero lift of a configuration with a large fuselage cavity and partially submerged store. Testing was performed out of a desire to determine if large stores can be attached to aircraft wings without negatively affecting the aerodynamic properties. Results regarding total drag and pressure drag are provided.
Date: February 26, 1957
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Free-Flight Tests to Determine the Power-on and Power-Off Pressure Distribution and Drag of the NACA RM-10 Research Vehicle at Large Reynolds Numbers Between Mach Numbers 0.8 and 3.0

Description: Memorandum presenting an investigation of the effect of a propulsive jet on the drag and pressure distribution of the NACA RM-10 missile configuration at large Reynolds numbers that utilized rocket models between Mach numbers 0.8 and 3.0. Pressures were measured along the body, near the fin root, and at the base. Results regarding basic data, body pressures, fin pressures, and drag are provided.
Date: September 20, 1955
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Supersonic-Area-Rule Design and Rocket-Propelled Flight Investigation of a Zero-Lift Straight-Wing-Body-Nacelle Configuration Between Mach Numbers 0.8 and 1.53

Description: Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.
Date: April 26, 1956
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation at Mach Numbers From 0.8 to 1.5 of the Effect of a Fuselage Indentation on the Zero-Lift Drag of a 52.5 Degree Sweptback-Wing-Body Configuration With Symmetrically Mounted Stores on the Fuselage

Description: Memorandum presenting two rocket-propelled models flight tested at Mach numbers from 0.8 to 1.5 to determine the effect of a fuselage indentation on the drag of a 52.5 degree sweptback-wing-body configuration with two large strut-mounted store symmetrically located above and below the fuselage. The fuselage had a symmetrical, Mach number 1.0 indentation designed to cancel the wing area normal to the plane of symmetry. Results regarding total drag and pressure drag are provided.
Date: February 20, 1958
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation of the Drag of a Model of a 60 Degree Delta-Wing Bomber With Strut-Mounted Siamese Nacelles and Indented Fuselage at Mach Numbers From 0.80 to 1.35

Description: Memorandum presenting a model of a 60 degree delta-wing bomber with strut-mounted Siamese nacelles, which was designed, with the use of a symmetrical fuselage indentation, to have a smooth average area distribution at a Mach number of 1.20. The results show that the configuration drag rise was significantly higher than that from the equivalent-body tests and area-rule theory throughout the Mach number range. Results regarding total drag and pressure drag are provided.
Date: September 25, 1957
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.
Date: June 25, 1951
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

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 combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3

Description: Investigation of the effect on zero-lift drag of varying the size and number of symmetrically mounted nacelles on a 45 degree sweptback wing and body combination as determined by free-flight tests of rocket-propelled models over a range of Mach and Reynolds numbers. The nacelle configuration consisted of a twin-engine nacelle near the fuselage, a combination of single-engine nacelles at the wing tip and fuselage, a large nacelle at the wing tip, and a large nacelle near the fuselage.
Date: June 22, 1953
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Description: Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
Date: September 26, 1956
Creator: Hoffman, Sherwood & Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department

Transonic flight tests to compare the zero-lift drags of 45 degree sweptback wings of aspect ratio 3.55 and 6.0 with and without nacelles at the wing tips

Description: Report presenting tests of rocket-propelled models at transonic speeds to compare the zero-lift drags of 45 degree sweptback wings with and without solid nacelles at the wing tips. The wing drag coefficient was lowered at high subsonic and supersonic speeds when the aspect ratio was reduced from 6.0 to 3.55. Results regarding the favorability of the wing-tip nacelles and the force-break Mach number of the varying configurations are also provided.
Date: March 6, 1952
Creator: Hoffman, Sherwood & Mapp, Richard C., Jr.
Partner: UNT Libraries Government Documents Department

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

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
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

Free-Flight Investigation to Determine the Drag of Flat- and Vee- Windshield Canopies on a Parabolic Fuselage With and Without Transonic Indentation Between Mach Numbers of 0.75 and 1.35

Description: Note presenting a free-flight investigation between Mach numbers of 0.75 and 1.35 to determine the effects on model total drag and pressure drag of (a) canopy location, (b) canopy windshield shape, (c) canopy fineness ratio, and (d) transonic-area-rule indentation.
Date: September 1958
Creator: Kouyoumjian, Walter L. & Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.
Date: May 23, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Chordwise Positions at the Wing Tip of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the chordwise position of a nacelle at the wing tip of a 45 degree sweptback wing and body combination as determined through transonic flight tests at zero lift. The drag of the configuration with nacelles in the rear chordwise positions was equal to or less than the drag of the configuration without nacelles over most of the speed range.
Date: September 17, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

A Flight Investigation to Determine the Effectiveness of Mach Number 1.0, 1.2, and 1.41 Fuselage Indentations for Reducing the Pressure Drag of a 45 Degree Sweptback Wing Configuration at Transonic and Low Supersonic Speeds

Description: Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.
Date: May 16, 1957
Creator: Blanchard, Willard S., Jr. & Hoffman, Sherwood
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