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424 Matching Results
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Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback
Report presenting a wind-tunnel investigation of two semispan wing models with 45 degrees of sweepback, an aspect ratio of 5, and a taper ratio of 0.565. One wing had no camber or twist while the other was cambered for a design lift coefficient of 0.4 and twisted to relieve loading at the tip. Results regarding the plane wing, cambered and twisted wing, wing-body combinations, effect of camber and twist, effect of fences, effect of surface roughness, and lift-drag ratio are provided.
Date:
July 12, 1951
Creator:
Johnson, Ben H., Jr. & Shibata, Harry H.
System:
The UNT Digital Library
Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios
Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
Date:
July 6, 1948
Creator:
Wollner, Bertram C.
System:
The UNT Digital Library
Chemical and physical factors affecting combustion in fuel-nitric acid systems
Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chemical and physical factors affecting combustion are provided.
Date:
July 28, 1958
Creator:
Baker, Louis, Jr.
System:
The UNT Digital Library
Comparative Study of Turbofan and Turbojet Engines
Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date:
July 19, 1957
Creator:
Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
System:
The UNT Digital Library
Comparison of calculated and experimental temperatures of water-cooled turbine blades
Report presenting analytical methods to calculate average and local turbine-blade temperatures. The temperatures were compared with experimental data obtained in a forced-convection, water-cooled aluminum turbine over a range of turbine-inlet-gas temperatures and coolant-mass velocities. Results regarding comparison of calculated and experimental aluminum turbine blade temperatures, comparison of calculated and experimental stationary-blade temperatures, stationary water-cooled blade operating data, and turbine operating data are provided.
Date:
July 15, 1952
Creator:
Schum, Eugene F.; Freche, John C. & Stelpflug, William J.
System:
The UNT Digital Library
Comparison of normal load factors experienced with jet fighter airplanes during combat operations with those of flight tests conducted by the NACA during operational training
Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.
Date:
July 7, 1954
Creator:
Hamer, Harold A.; Huss, Carl R. & Mayer, John P.
System:
The UNT Digital Library
Comparison of outside-surface heat-transfer coefficients for cascades of turbine blades
A comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated.
Date:
July 17, 1950
Creator:
Hubbartt, James E.
System:
The UNT Digital Library
Comparison of Water-Load Distributions Obtained during Seaplane Landings with Bureau of Aeronautics Specifications. TED No. NACA 2413
"Bureau of Aeronautics Design Specifications SS-IC-2 for water loads in sheltered water are compared with experimental water loads obtained during a full--scale landing investigation. This investigation was conducted with a JRS-1 flying boat which has a 20 degrees dead-rise V-bottom with a partial chine flare. The range of landing conditions included airspeeds between 88 and 126 feet per second, sinking speeds between 1.6 and 9.1 feet per second, flight angles less than 6 degrees, and trims between 2 degrees and 12 degrees" (p. 1).
Date:
July 1949
Creator:
Smiley, Robert F. & Haines, Gilbert A.
System:
The UNT Digital Library
Comparison With Theory of Landing Impacts of a Model of a Seaplane Incorporating a Hydro-Ski With and Without a Shock Absorber
Report presenting experimental data from calm- and rough-water landing impacts with a dynamic model of a seaplane incorporating a flat-bottom hydro-ski mounted on a rigid strut and on a shock-absorber strut. Results regarding the fixed-ski case and translating-ski case are provided.
Date:
July 11, 1956
Creator:
Hoffman, Edward L.
System:
The UNT Digital Library
Compatibility of Pentaborane With Materials Used for Seals, Gaskets, and Construction
Memorandum presenting the compatibility of pentaborane with aluminum foil, 24S-T and 17S-T aluminum, and 50-50 tin-lead solder in the range of -30 to -50 degrees F for 7 hours, at 90 degrees F for 6.5 hours, and at 70 degrees F for 28 days. Results were evaluated by determination of the loss in weight after the test period, metallographic inspection, and comparison with blanks carried through test conditions without exposure to the liquid. The evaluation of results was made by visual inspection and physical tests of dimensional stability, tensile strength, elasticity, and gain or loss of weight.
Date:
July 19, 1954
Creator:
Kaye, Samuel & Sordyl, Frank V.
System:
The UNT Digital Library
Compilation and review of effects of design parameters on ditching characteristics
From Summary: "This paper supplements a previously published one on the effect of design parameters on ditching characteristics. The supplementary information is based on additional data available from both model tests and full-scale experience. In addition, summary tables compiled from the NACA model ditching investigations are presented."
Date:
July 10, 1951
Creator:
Fisher, Lloyd J. & Hoffman, Edward L.
System:
The UNT Digital Library
Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers
Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date:
July 10, 1952
Creator:
Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
System:
The UNT Digital Library
Contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan model of a supersonic airplane configuration at transonic speeds from tests by the NACA wing-flow method
Report presenting an investigation using the NACA wing-flow method at transonic speeds to determine the contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan airplane model with a long slender fuselage and straight wing and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections 4.6 percent of the chord in thickness. Results regarding the drag, pitching moment, downwash, and lift are provided.
Date:
July 11, 1951
Creator:
Silsby, Norman S. & McKay, James M.
System:
The UNT Digital Library
Control characteristics at transonic speeds of a linked flap and spoiler on a tapered 45 degrees sweptback wing of aspect ratio 3
Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.
Date:
July 11, 1952
Creator:
Lockwood, Vernard E. & Fikes, Joseph E.
System:
The UNT Digital Library
Design and Experimental Investigation of Light-Weight Bases for Air-Cooled Turbine Rotor Blades
Memorandum presenting an investigation of the problem of air-cooled turbine rotor-blade weight reduction for aircraft gas turbines as part of the NACA turbine-cooling research program. A bulb-root-type blade-base design was achieved which utilized forming and brazing techniques in its manufacture and was combined with an axial-flow turbojet engine aerodynamic profile. Results regarding the sheet-metal bulb-root-type air-cooled base designs, air-cooled pinned-type base design, and some weight reduction considerations are provided.
Date:
July 2, 1954
Creator:
Freche, John C. & McKinnon, Roy A.
System:
The UNT Digital Library
Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B
Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date:
July 7, 1955
Creator:
Hamrick, Joseph T. & Osborn, Walter M.
System:
The UNT Digital Library
Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties
Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.
Date:
July 8, 1952
Creator:
Black, John M. & Blomquist, R. F.
System:
The UNT Digital Library
Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane
"An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).
Date:
July 13, 1955
Creator:
Windham, John O.
System:
The UNT Digital Library
Downwash and Dynamic Pressure at the Horizontal Tail of a Six-Engine Pusher-Propelled Airplane
Report discussing an investigation of the vertical plane of the elevator hinge line of a powered model of a bomber to determine the values of downwash and the dynamic-pressure ratio. The equations for calculating these values and the testing procedures are described.
Date:
July 19, 1948
Creator:
Furlong, G. Chester
System:
The UNT Digital Library
Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber
Report presenting an investigation using rocket-propelled model of the Convair B-58 supersonic bomber. Drag at trim lift was obtained for a range of Mach and Reynolds numbers and is compared to data from several other testing facilities.
Date:
July 13, 1956
Creator:
Hopko, Russell N. & Kinard, William H.
System:
The UNT Digital Library
Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber
Memorandum presenting an investigation utilizing a 1/15-scale rocket-propelled model of the Convair B-58 supersonic bomber. The drag at model trim lift was obtained at a range of Mach and Reynolds numbers. A comparison of the drag at transonic speeds and approximately the same Reynolds number showed excellent agreement.
Date:
July 13, 1956
Creator:
Hopko, Russell N. & Kinard, William H.
System:
The UNT Digital Library
Drag Investigation of a Swept-Wing Fighter-Airplane Model Incorporating Two Drag-Rise-Reducing Fuselage Revisions
Report discussing several configurations of a swept-wing fighter airplane to determine the effects of modified applications of the transonic and supersonic area rules on the transonic drag-rise characteristics. Information about the lift and pitching-moment characteristics is also provided.
Date:
July 19, 1955
Creator:
Whitcomb, Charles F. & Lee, Edwin E., Jr.
System:
The UNT Digital Library
Dynamic corrosion of a stainless-steel specimen by water at 500 degrees F using a toroid circulating apparatus
A slug of air-saturated distilled water was circulated for 317 hours at a velocity of 15 feet per second in an AISI 347 stainless-steel toroid with a wall temperature of 500 F and a 30 F difference in temperature between the hot and cold sections. The depth of corrosion layer was 0.001 inch (0.028 in./yr) in the hot sector and 0.0007 inch (0.019 in./yr) in the cold sector; no mass transfer was observed. The results of gas,water,and X-ray diffraction analyses are given together with photomicrographs of sections taken from the hot and cold sections of the specimen.
Date:
July 16, 1952
Creator:
Desmon, Leland G. & Mosher, Don R.
System:
The UNT Digital Library
Effect of a nacelle on the low-speed aerodynamic characteristics of a swept-back wing
Wind-tunnel tests of a simplified nacelle on a semispan wing having approximately 35 degrees of sweepback were made at low speeds to evaluate the effects of the nacelle on the aerodynamic characteristics of the wing. Force, moment, and pressure-distribution measurements are presented for the nacelle underslung and centrally mounted on the wing and mounted on a strut below the wing.
Date:
July 21, 1948
Creator:
Hanson, Frederick H., Jr. & Dannenberg, Robert E.
System:
The UNT Digital Library