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Serial/Series Title
NACA Research Memorandums
151
Atomic Energy Commission Reports
74
NACA Technical Reports
32
Hanford Works Reports
19
University of California Radiation Laboratory Reports
19
Oak Ridge National Laboratory Reports
18
AEC research and development report
14
HW (Series)
10
Report (U.S. Atomic Energy Commission)
10
UCRL (Series)
9
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344 Matching Results
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Wing-flow tests of a triangular wing of aspect ratio two 1: effectiveness of several types of trailing-edge flaps on flat-plate models
Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.
Date:
November 14, 1947
Creator:
Rathert, George A., Jr. & Cooper, George E.
Object Type:
Report
System:
The UNT Digital Library
High-Speed Stability and Control Characteristics of a Fighter Airplane Model with a Swept-Back Wing and Tail
Memorandum presenting wind-tunnel tests conducted to determine the high-speed stability and control characteristics of an airplane model with a sweptback wing and tail. The aerodynamic coefficients and the longitudinal- and lateral-control characteristics of the plain wing-fuselage-tail combination are included. Results regarding lift, drag, and pitching moment, longitudinal characteristics, lateral characteristics, wing leading-edge slate, and fuselage-side dive brakes are provided.
Date:
April 14, 1948
Creator:
Morrill, Charles P., Jr. & Boddy, Lee E.
Object Type:
Report
System:
The UNT Digital Library
High-Speed Wind-Tunnel Investigation of a Sweptback Wing With an Added Triangular Area at the Center
Report discussing an investigation of two sweptback wings of different plan form in order to determine the effects of adding a triangular area to the inboard section of a conventional sweptback wing as a way to create a wing with two stages of sweepback. Lift, drag, and pitching-moment characteristics are provided for a range of Mach numbers.
Date:
January 14, 1949
Creator:
Henry, Beverly Z., Jr.
Object Type:
Report
System:
The UNT Digital Library
Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.
Date:
February 14, 1950
Creator:
Turner, Thomas R.
Object Type:
Report
System:
The UNT Digital Library
Stability and control characteristics at low speed of a 1/4-scale Bell X-5 airplane model: Longitudinal stability and control
Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.
Date:
March 14, 1950
Creator:
Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio
Report presenting a discussion of the aerodynamic forces and moments on inclined bodies of revolution. An approximate theory to allow for the effects of viscosity is developed and applied. Results regarding the variation of lift and pitching moment, and center of gravity are provided.
Date:
November 14, 1949
Creator:
Allen, H. Julian
Object Type:
Report
System:
The UNT Digital Library
An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 3: Characteristics of Wing With Body and Vertical Tail
Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.
Date:
October 14, 1949
Creator:
Anderson, Adrien E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a thin straight wing of aspect ratio 4 by the NACA wing-flow method: Lift and pitching-moment characteristics of the wing alone
This report presents measurements of the lift and pitching-moment characteristics of a straight wing of aspect ratio 4, taper ratio 0.5, having a symmetrical double-wedge airfoil section with a maximum thickness of 4.4-percent chord. The tests were conducted in the Mach number range 0.51 to 1.20, Reynolds numbers 380,000 to 660,000, by the NACA wing-flow method. The results are compared with theory and with wind-tunnel tests of a similar model. It is indicated that in the Mach number range 0.82 to 1.00 the model surface, profile, and test Reynolds number all would be very important considerations in any attempt to study or predict full-scale characteristics from small-model tests.
Date:
February 14, 1949
Creator:
Rathert, George A., Jr.; Hanson, Carl M. & Rolls, L. Stewart
Object Type:
Report
System:
The UNT Digital Library
The Effectiveness at High Speeds of a 10-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section
This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a 10-percent-chord plain flap on the NACA 65-210 airfoil section. The results include an indication of the lift-producing characteristics and the effectiveness of the 10-percent-chord flap. From a comparison of the characteristics of the 10-percent-chord flap with those of a 20-percent-chord flap it was concluded that, although a reduction in flap-chord ratio from 0.20 to 0.10 lessens the severity of the effectiveness loss at supercritical speeds, the 20-percent-chord flap is more effective throughout the entire range of Mach numbers from 0.3 to 0.875.
Date:
June 14, 1948
Creator:
Ilk, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation to Determine Propeller Section Characteristics by Measuring the Pressure Distribution on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions
"An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-section characteristics by measuring the pressure distribution on the airfoil sections of a rotating propeller. The pressures were measured at nine radial stations on an NACA 10-(3)(08)-03 design two-blade propeller. This paper presents the results of the pressure measurements in the form of normal-force and moment coefficients and covers a range of nominal angle of attack (simple blade element theory) from 0 degrees to 4 degrees for a section Mach number range of approximately 0.6 to 1.15 for the outboard stations and approximately 0.3 to 0.6 for inboard stations" (p. 1).
Date:
July 14, 1948
Creator:
Evans, Albert J. & Liner, George
Object Type:
Report
System:
The UNT Digital Library
Effects of several leading-edge modifications on the stalling characteristics of a 45 degree swept-forward wing
Report presenting an investigation to determine the effects of several leading-edge modifications on the maximum lift and pitching-moment characteristics on a large-scale 45 degree swept-forward wing. A full-span leading-edge flap deflected 30 degrees down tended to give the largest gain of maximum lift. Results regarding the plain leading-edge flaps and cambered nose are explored.
Date:
June 14, 1949
Creator:
McCormack, Gerald M. & Cook, Woodrow L.
Object Type:
Report
System:
The UNT Digital Library
A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds
Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.
Date:
September 14, 1949
Creator:
Stevens, Victor I. & Boyd, John W.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions
A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.
Date:
February 14, 1950
Creator:
Gray, W. H. & Hunt, Robert M.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-Scoop Inlet-Body Combination at Mach Numbers of 1.4 and 1.7
Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop inlet-body combination measured at Mach numbers 1.4 and 1.7 at zero angle of attack. Tests were made of the inlet-body combination with an ogival forebody, an ogival forebody with a small amount of bluntness near the tip, and two forebodies of elliptical longitudinal section. Results regarding the effect of forebody bluntness on pressure recovery, effect of forebody bluntness on mass-flow ratio, and the effects of forebody bluntness on drag are provided.
Date:
February 14, 1952
Creator:
Stroud, John F.
Object Type:
Report
System:
The UNT Digital Library
A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number
Report presenting the low-speed longitudinal characteristics of swept wings derived from investigations at high Reynolds numbers. Two different types of flow separation, trialing-edge and leading-edge separation, are identified and discussed.
Date:
August 14, 1952
Creator:
Furlong, G. Chester & McHugh, James G.
Object Type:
Report
System:
The UNT Digital Library
Notes on Heat-Resistant Materials in Britain from Technical Mission October 13 to November 30, 1950
Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.
Date:
May 14, 1951
Creator:
Freeman, J. W. & Cross, Howard C.
Object Type:
Report
System:
The UNT Digital Library
The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing: Effects of Controlling the Chordwise Distribution of Suction Air Velocities
Report discusses the results of an updated investigation into the effectiveness of area suction when used to prevent air-flow separation at the leading edge of a 63 degree swept-back wing. This new report investigates the results of tests with chordwise distribution of the suction-air velocities controlled to give lower total-flow quantity requirements. The primary focus is the delay effected in air-flow separation and improvements made on aerodynamic characteristics of a wing with area suction specifically designed for a lift coefficient of 0.77.
Date:
January 14, 1952
Creator:
Cook, Woodrow L. & Kelly, Mark W.
Object Type:
Report
System:
The UNT Digital Library
Spreading of Exhaust Jet From 16 Inch Ream Jet at Mach Number 2.0
"An investigation of the jet-spreading characteristics of a 16 inch ram-jet engine was conducted in the 8 by 6 foot supersonic tunnel at a Mach number of 2.0; both a converging nozzle having a contraction ratio of 0.71 and a cylindrical extension to the combustion chamber were used. The jet boundaries determined by means of pitot pressure surveys were compared with boundaries calculated from one-dimensional continuity and momentum relations. For the cylindrical nozzle, the jet reaches its maximum diameter, 4 percent greater than calculated, about 0.6 nozzle-exit diameter downstream of the nozzle exit" (p. 1).
Date:
August 14, 1952
Creator:
Wilcox, Fred & Pennington, Donald
Object Type:
Report
System:
The UNT Digital Library
Some fundamental aspects of nitric acid oxidants for rocket applications
From Summary: "The literature pertaining to the preparation, physical properties, corrosiveness, thermal stability, constitution, and analysis of various nitric acids is reviewed primarily with respect to their use as rocket oxidants. Conflicting data are evaluated and recommendations for additional experimental work are indicated. Reactions of nitric acid which could occur during the starting and steady-stage phases of rocket operation are discussed and probable mechanisms are selected on the basis of reported thermal and kinetic data."
Date:
January 14, 1953
Creator:
Ladanyi, Dezso J.; Miller, Riley O.; Karo, Wolf & Feiler, Charles E.
Object Type:
Report
System:
The UNT Digital Library
Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture
Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.
Date:
January 14, 1953
Creator:
Swett, Clyde C., Jr. & Donlon, Richard H.
Object Type:
Report
System:
The UNT Digital Library
The effects of sweepback on longitudinal characteristics of a 1/30-scale semispan model of the Bell X-5 airplane as determined from NACA wing-flow tests at transonic speeds
Report presenting tests using the NACA wing-flow method to determine the effect of sweepback angle on the longitudinal characteristics of a scale semispan model of the Bell X-5 variable-sweep airplane at a range of Mach numbers. Lift, drag, and pitching moments were obtained for a range of angles of attack.
Date:
November 14, 1952
Creator:
Kolnick, Joseph J. & Kennedy, Robert M.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Wind-Tunnel Investigation of the Effects of Propeller Operation at High Thrust on the Longitudinal Stability and Trim of a Twin-Engine Airplane Configuration
Report presenting an investigation to determine the effects of dual-rotation propeller operation at high thrust on the static longitudinal stability characteristics of a semispan powered model representing a twin-engine airplane configuration with flaps retracted. Stability and trim changes associated with an extreme constant power conditions were greatly dependent on tail height and vertical location of the center of gravity. Results regarding basic data, effects of power on overall stability and trim, and tuft-grid flow surveys are provided.
Date:
July 14, 1952
Creator:
Sleeman, William C., Jr. & Linsley, Edward L.
Object Type:
Report
System:
The UNT Digital Library
Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96
Memorandum presenting an investigation of a half-delta wing-tip control on a semispan 60 degree delta-wing-fuselage combination conducted in the 9- by 12-inch supersonic blowdown tunnel. Control-surface hinge moments and bending moments, as well as the characteristics of the complete wing-fuselage combination, were obtained over a large range of control deflection and angle of attack at specified Mach and Reynolds numbers. Results regarding the control bending-moment and hinge-moment characteristics, control effectiveness characteristics, and effect of fence on wing characteristics are provided.
Date:
October 14, 1952
Creator:
Guy, Lawrence D.
Object Type:
Report
System:
The UNT Digital Library
Investigation at high subsonic speeds of bodies mounted from the wing of an unswept-wing-fuselage model, including measurements of body loads
Report presenting an investigation with the dual purpose of determining the effect of two bodies in various positions, symmetrically located from the plane of symmetry, on the aerodynamic characteristics of a wing-fuselage model and determining the aerodynamic loads on one of two bodies. Some of the most significant effects were obtained for the direct-mounted tip bodies which gave a large increase in the lift-curve slope of the basic model.
Date:
November 14, 1952
Creator:
Silvers, H. Norman & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library