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Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Description: Report presenting tests to determine the effects of sweepback angle and aspect ratio on the drag of an NACA 65-009 airfoil at supersonic speeds. The results indicated that for the range of Mach numbers investigated, increasing the sweepback angle and decreasing the aspect ratio reduced the value of the wing drag coefficient.
Date: February 24, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Partner: UNT Libraries Government Documents Department
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Heat of Combustion of the Product Formed by the Reaction of Acetylene and Diborane (LFPL-CZ-3)

Description: The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion… more
Date: October 24, 1957
Creator: Allen, Harrison, Jr. & Tannenbaum, Stanley
Partner: UNT Libraries Government Documents Department
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Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Description: Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date: August 24, 1948
Creator: Amer, Kenneth B.
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a Twin-Fuselage Pursuit Airplane

Description: Report discussing the aerodynamic characteristics of a twin-fuselage pursuit airplane model, especially at high speeds. Information about the force data and critical Mach numbers for parts of the model is provided. Suggestions for increasing the Mach number of divergence by making modifications to the wing-fuselage fillets and external shape of the radiator are also included.
Date: April 24, 1946
Creator: Anderson, Joseph L. & Tkac, Victor B.
Partner: UNT Libraries Government Documents Department
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Correlation of Flight and Wind-Tunnel Measurements of Roll-Off in Low-Speed Stalls on a 35 Degree Swept-Wing Aircraft

Description: Memorandum presenting flight and wind-tunnel measurements made of the low-speed stalling characteristics on a swept-wing jet aircraft. Included in the study are the effects on the stalling characteristics of a number of wing modifications. Results regarding the roll-off characteristics and maximum lift and stalling characteristics are provided.
Date: September 24, 1953
Creator: Anderson, Seth B.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Lateral- and Directional-Stability and Control Characteristics

Description: "This report contains the flight-test results of the lateral and directional-stability and control phase (including tests with wing-tip tanks) of a general flying-qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). These tests were conducted at indicated airspeeds up to 494 miles per hour (0.691 Mach number) at low altitude and up to 378 miles per hour (0.816 Mach number) at high altitude. These tests showed that the flying qualities of the airplane were for the most par… more
Date: October 24, 1947
Creator: Anderson, Seth B. & Cooper, George E.
Partner: UNT Libraries Government Documents Department
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Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers

Description: From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sens… more
Date: April 24, 1951
Creator: Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Preliminary Results of British Nene II Engine Altitude-Chamber Performance Investigation. I - Altitude Performance Using Standard 18.75-Inch-Diameter Jet Nozzle, 1, Altitude Performance Using Standard 18.75-Inch-Diameter Jet Nozzle

Description: An investigation is being conducted to determine the altitude performance characteristics of the British Nene II engine and its components. The present paper presents the preliminary results obtained using a standard jet nozzle. The test results presented are for conditions simulating altitudes from sea level to 60,000 feet and ram pressure ratios from 1.0 to 2.3. These ram pressure ratios correspond to flight Mach numbers between zero and 1.16 assuming a 100 percent ram recovery.
Date: May 24, 1948
Creator: Barson, Zelmar & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department
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Air-Flow Behavior Over the Wing of an XP-51 Airplane as Indicated by Wing-Surface Tufts at Subcritical and Supercritical Speeds

Description: Report presenting the air-flow behavior over the wing of an XP-51 airplane including photographs of tufts attached to the wing surface and chordwise pressure distributions. A comparison of tuft studies from flight results are compared with results from wind-tunnel testing. Three types of flow were observed: steady flow, unsteady flow, and break-away flow are provided.
Date: April 24, 1947
Creator: Beeler, De E.
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell XF2H-1 Airplane

Description: A spin-recovery investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 20-scale model modified to represent the McDonnell XF2H-1 airplane. The project included tests both with tip tanks installed and with the tanks removed. The results indicated that the recovery characteristics of the airplane would be satisfactory for all loadings by normal recovery technique (full reversal of the rudder, followed 1/2 turn later by movement of the elevator down). The rudder pedal an… more
Date: June 24, 1949
Creator: Berman, Theodore
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.
Partner: UNT Libraries Government Documents Department
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Abstracts Pertaining to Seaplanes

Description: Report discussing about 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.
Date: July 24, 1947
Creator: Bidwell, Jerold M. & King, Douglas A.
Partner: UNT Libraries Government Documents Department
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Effect of three flame-holder configurations on subsonic flight performance of rectangular ram jet over range of altitudes

Description: Report presenting a flight investigation on a rectangular ram jet over a range of fuel air ratios, combustion chamber inlet velocities, and pressure altitudes. A comparative study to determine the effects of altitude, combustion-chamber-inlet velocity, and fuel-air ratio on starting characteristics, minimum blow-out limits, combustion efficiency, gas total-temperature ratio, and net-thrust coefficient for three flame holders was also conducted.
Date: November 24, 1948
Creator: Black, Dugald O. & Messing, Wesley E.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds

Description: Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a wing-nacelle combination at high subsonic speeds. Lift, drag, pitching-moment, and ram-recovery data re presented for a range of Mach and Reynolds numbers.
Date: October 24, 1950
Creator: Boltz, Frederick W. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department
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Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections

Description: From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."
Date: April 24, 1952
Creator: Boxer, Emanuel; Sterrett, James R. & Wlodarski, John
Partner: UNT Libraries Government Documents Department
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Description and bibliography of NACA research on wing controls: January 1946 - February 1955

Description: Report presenting some accompanying tables and bibliography for experimental aerodynamic studies in the field of wing controls during the period between January 1946 and February 1955. The tables are grouped according to the following major classifications: trailing-edge flap controls, leading-edge flap controls, and spoiler controls.
Date: March 24, 1955
Creator: Brewer, Jack D.
Partner: UNT Libraries Government Documents Department
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Flight Determination of the Buffeting Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Description: Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.
Date: May 24, 1954
Creator: Briggs, Donald W.
Partner: UNT Libraries Government Documents Department
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Instrumentation of the Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the equipment used in the Ames supersonic free-flight wind tunnel to obtain the data necessary to measure the aerodynamic characteristics of free-flying models. The model is fired from a gun into the supersonic air stream of a blowdown-type wind tunnel. The action resulting from aerodynamic forces is computed from a time-distance-attitude record of the model flight through the test section.
Date: April 24, 1952
Creator: Briggs, Robert O.; Kerwin, William J. & Schmidt, Stanley F.
Partner: UNT Libraries Government Documents Department
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A Flight Investigation at Transonic Speeds of a Model Having a Triangular Wing of Aspect Ratio 4

Description: Report presenting testing of free-falling recoverable-model tests at transonic speeds on a model with an aspect-ratio-4 triangular wing and a 45 degree sweptback tail in the extended wing-chord plane. Results regarding the lift, drag, stability, tail effectiveness, and buffet boundary are provided.
Date: March 24, 1955
Creator: Bright, Loren G.
Partner: UNT Libraries Government Documents Department
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The Effect of Humidity on Engine Power at Altitude

Description: "From tests made in the altitude chamber of the Bureau of Standards, it was found that the effect of humidity on engine power is the same at altitudes up to 25,000 feet as at sea level. Earlier tests on automotive engines, made under sea-level conditions, showed that water vapor acts as an inert diluent, reducing engine power in proportion to the amount of vapor present. By combining the effects of atmospheric pressure, temperature, and humidity, it is shown that the indicated power obtainable … more
Date: February 24, 1932
Creator: Brooks, D. B. & Garlock, E. A.
Partner: UNT Libraries Government Documents Department
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Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls

Description: Report presenting an investigation to evaluate two methods of decreasing losses of unevaporated fuel from the combustion zone of turbojet-engine combustors. One method had fuel dams on the inner surface of the combustor liner and one had a ceramic coating on the combustor-liner walls. Results regarding the effect of the fuel dams, effect of ceramic coatings, effect of combination of fuel dams and ceramic coatings, and effect of ceramic coating on carbon deposition are provided.
Date: November 24, 1952
Creator: Butze, Helmut F. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department
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Gust-Tunnel Investigation of the Effect of Leading Edge Separation on the Normal Accelerations Experienced by a 45 Degree Sweptback-Wing Model in Gusts

Description: Report presenting an investigation of a 45 degree sweptback-wing model with interchangeable round and sharp leading edges to determine the effect of leading-edge separation on the loads experienced by the models in gusts. Leading-edge separation was found to increase the gust load, which appeared to vary based on the gust-gradient distance and velocity.
Date: November 24, 1953
Creator: Cahen, George L.
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.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Flow Field Behind an Aspect-Ratio-10 Hydrofoil Near the Water Surface

Description: Report presenting an investigation of the flow field behind a hydrofoil with an 8-inch chord and an aspect ratio of 10; the foil was operating at about 0.75 chord below the free-water surface. The downwash and water surface profiles were measured behind the hydrofoil for a variety of positions of interest. Results regarding surface contours, a comparison of surface profiles with theoretical two-dimensional waves, and downwash are presented.
Date: February 24, 1953
Creator: Carter, Arthur W. & Butler, Roger V.
Partner: UNT Libraries Government Documents Department
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