National Advisory Committee for Aeronautics (NACA) - 150 Matching Results

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Elevated-Temperature Fatigue Properties of Two Titanium Alloys

Description: Report presenting an investigation to evaluate the unnotched fatigue properties of two titanium alloys at elevated temperatures. A variety of temperatures were tested and the results are provided in tabular form and as curves of stress versus cycles to failure for each test temperature. Both alloys were found to have potential use at the temperature ranges investigated.
Date: April 24, 1956
Creator: Rey, William K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Leading-Edge Slat and Trailing-Edge Split Flap on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a Nearly Triangular Wing of Aspect Ratio 2.9 at Mach Numbers From 0.60 to 0.92

Description: Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.
Date: January 24, 1958
Creator: Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Zero Power Reactor Facility Hazards Summary

Description: "The Lewis Flight Propulsion Laboratory of the National Advisory Committee for Aeronautics proposes to build a zero power research reactor facility which will be located in the laboratory grounds near Cleveland, Ohio. The purpose of this report is to inform the Advisory Committee on Reactor Safeguards of the U. S. Atomic Energy Commission in regard to the design of the reactor facility, the characteristics of the site, and the hazards of operation at this location. The purpose of this reactor i… more
Date: June 24, 1957
Creator: Lewis Laboratory Staff
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane in the Swept-Wing Configuration with Slats Extended

Description: "A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/30 -scale model of the Grumman XF10F-1 airplane to determine what effect full-span slats would have on the spin-recovery characteristics of the swept-wing version of the XF10F-1 airplane, which had previously been indicated as possessing undesirable spin-recovery characteristics without slats. The effects of extended nose-wheel doors and of fairing the air-duct inlets were also determined" (p. 1… more
Date: July 24, 1951
Creator: Berman, Theodore & Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds

Description: "This paper presents the results of an investigation of sting-support interference on afterbody drag at transonic speeds. Stings with varying diameter, cone angle, and cylindrical length were tested at the rear of a model with various afterbody shapes. The data were obtained at an angle of attack of 0 deg. and at Mach numbers from 0.80 to 1.10. It was found that, in general, the addition of a sting caused a drag reduction" (p. 1).
Date: September 24, 1956
Creator: Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of the Minimum Drag of Two Versions of a Modified Delta-Wing Fighter as Obtained From Flight Tests of Rocket-Boosted Models and Equivalent Bodies Between Mach Numbers of 0.80 and 1.64

Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
Date: September 24, 1956
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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