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Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research
Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date:
July 20, 1948
Creator:
Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Sweptback Wing and Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method
Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test surface, and the effectiveness of a wing flap with a sweepback of 45 degrees.
Date:
July 23, 1948
Creator:
Sawyer, Richard H. & Lina, Lindsay J.
System:
The UNT Digital Library
Free-Flight-Tunnel Tests of a Target-Seeking Glide-Bomb Model With Flicker Lateral Control
Report presenting an investigation of control systems suitable for target-seeking missiles. Testing occurred in the free-flight tunnel of the GB-5 glide bomb equipped with a light-seeker control unit which applied flicker control. Results indicated that good stability could be obtained with the control system, but was somewhat less stable than with a proportional control system.
Date:
July 28, 1948
Creator:
McKinney, Marion O., Jr. & Drake, Hubert M.
System:
The UNT Digital Library
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet
Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.
Date:
July 30, 1948
Creator:
Wilcox, Fred A.; Perchonok, Eugene & Wishnek, George
System:
The UNT Digital Library
Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock
Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.
Date:
July 23, 1948
Creator:
Zalovcik, John A. & Luke, Ernest P.
System:
The UNT Digital Library
Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane
"An investigation of the rolling effectiveness at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane has been made by means of a rocket-propelled test vehicle. The variation of rolling effectiveness with Mach number is similar to that obtained previously for tapered sweptback wings having full-span, 0.2-chord ailerons" (p. 1).
Date:
July 21, 1948
Creator:
Sandahl, Carl A.
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
Investigation of High-Temperature Operation of Liquid-Cooled Gas Turbines 1: Turbine Wheel of Aluminum Alloy, a High-Conductivity Nonstrategic Material
Report presenting an investigation of turbine operating temperatures as affected by liquid cooling, especially if materials of high conductivity are used, at gas temperatures up to 1925 degrees Fahrenheit. Results regarding the statio heat-transfer rig and turbine rig are provided. The investigation showed that nonstrategic material such as aluminum alloy can be used in liquid-cooled turbine wheels at high gas temperatures.
Date:
July 22, 1948
Creator:
Kottas, Harry & Sheflin, Bob W.
System:
The UNT Digital Library
Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 1: nacelle with offset air inlet
Report presenting aerodynamic and icing investigations on a model of a turbojet-engine nacelle in order to provide icing protection for the engine, protective screen, and accessory housing by the introduction of hot gases into the inlet-air stream. Adequate ice protection was afforded when the minimum kinetic temperature in the protective screen was greater than 32 degrees Fahrenheit.
Date:
July 9, 1948
Creator:
Callaghan, Edmund E.; Ruggeri, Robert S. & Krebs, Richard P.
System:
The UNT Digital Library
Investigation of Low-Speed Aileron Control Characteristics at a Reynolds Number of 6,800,000 of a Wing With Leading Edge Swept Back 42 Degrees With and Without High-Lift Devices
Report presenting an investigation at a Reynolds number of 6,800,000 to determine the low-speed lateral control characteristics of a 20-percent-chord half-span outboard aileron on a wing with 42 degrees of sweepback at the leading edge. The lateral control, aileron hinge-moment, aileron load, and balance-chamber-pressure characteristics were determined for the wing with and without high-lift and stall-control devices for an angle-of-attack range from -4 degrees through the stall.
Date:
July 19, 1949
Creator:
Bollech, Thomas V. & Pratt, George L.
System:
The UNT Digital Library
Two-dimensional wind tunnel investigation of a symmetrical airfoil section with a sealed internally balanced control surface and a leading tab
Report presenting an investigation in the two-dimensional low-turbulence tunnel of a symmetrical airfoil section equipped with a 0.30-airfoil-chord sealed internally balanced flap with a 0.70-flap-chord overhang and a 0.33-flap-chord leading tab. Results regarding airfoil lift, surface pressure, flap hinge-moment, and flap-balance-chamber pressure characteristics at various flap deflections.
Date:
July 18, 1949
Creator:
Nuber, Robert J. & Fullmer, Felicien F., Jr.
System:
The UNT Digital Library
Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds
Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date:
July 13, 1947
Creator:
Alexander, Sidney R. & Nelson, Robert L.
System:
The UNT Digital Library
Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers
Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date:
July 8, 1949
Creator:
Hemenover, Albert D.
System:
The UNT Digital Library
Preliminary experimental investigation of effects of aerodynamic shape of concentrated weights on flutter of a straight cantilever wing
Report presenting the effect of flutter characteristics of variation on the aerodynamic shape of concentrated weights rigidly mounted on a simplified wing structure. Two general types of weights with similar mass and moment-of-inertia properties were employed. Results regarding effects of aerodynamic shape of concentrated weights, effects of spanwise variation of light concentrated weights, and effects of moment of inertia of light concentrated weights.
Date:
July 18, 1949
Creator:
Sewall, John L. & Woolston, Donald S.
System:
The UNT Digital Library
The NACA 2000-horsepower propeller dynamometer and tests at high speed of an NACA 10-(3)(08)-03 two-blade propeller
This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented.
Date:
July 20, 1948
Creator:
Corson, Blake W., Jr. & Maynard, Julian D.
System:
The UNT Digital Library
Investigation of the Loads on a Typical Bubble-Type Canopy
Report presenting an investigation of the surface pressures of the outer and inner surface of the bubble-type canopy in order to determine their load requirements. Testing was performed on a Grumman F8F-1 airplane. The forces on the canopy was found to be the highest when the airplane is operating at high speed with the canopy closed.
Date:
July 10, 1947
Creator:
Cocke, Bennie W., Jr.
System:
The UNT Digital Library
Performance of several air ejectors with conical mixing sections and small secondary flow rates
An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection of ejector design are provided.
Date:
July 19, 1948
Creator:
Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Airplane Model at Transonic Speeds as Obtained by the Transonic-Bump Method
Memorandum presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the longitudinal stability and control characteristics of a semispan airplane model at transonic speeds. The results indicated an increase in the maneuvering stability through the transonic range, but regions of instability were indicated by the slope of the curve stabilizer incidence for trim against Mach number at all positions tested.
Date:
July 19, 1948
Creator:
Weil, Joseph & Spearman, M. Leroy
System:
The UNT Digital Library
The Linear Perturbation Theory of Axially Symmetric Compressible Flow With Application to the Effect of Compressibility on the Pressure Coefficient at the Surface of a Body of Revolution
Memorandum discussing four related methods for the study of compressible flow by means of the linear perturbation theory for the case of three-dimensional flow with axial symmetry. A general method which includes the other is also discussed briefly. In each case, the properties of the compressible flow are obtained from those of a corresponding incompressible flow.
Date:
July 18, 1947
Creator:
Herriot, John G.
System:
The UNT Digital Library
A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models
Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date:
July 15, 1947
Creator:
Jessen, Henry, Jr.
System:
The UNT Digital Library
Measurements of the damping in roll of large-scale swept-forward and swept-back wings
Report presenting wind-tunnel testing of five large-scale tapered wings with a variety of angles of sweep to determine the effects of scale and sweep on the damping-in-roll parameter. Rolling moment and pressure distribution were measured for each plain wing while in steady roll for a range of angles of attack. Results regarding the effects of sweep at zero lift, effects of lift, and aurorotational characteristics are provided.
Date:
July 30, 1947
Creator:
Hunton, Lynn W. & Dew, Joseph K.
System:
The UNT Digital Library
Performance Investigation of a Jumo 004 Combustor
Report presenting an investigation of a German Jumo 004 combustor under conditions simulating zero-ram operation of a 24C jet-propulsion engine over ranges of altitude and engine speed to obtain the altitude operating limits and characteristics. Combustion efficiency, outlet-temperature distribution, and total-pressure drop were determined. The performance of the combustor with 62-octane and JP-1 fuels were also compared.
Date:
July 16, 1947
Creator:
Miller, Robert C.
System:
The UNT Digital Library
Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber
Report presenting an investigation with a ram-jet combustion chamber to determine the effect of fuel-air ratio and the inlet-air parameters of pressure, temperature, and velocity on combustion limit, combustion efficiency, and flame length.
Date:
July 22, 1948
Creator:
Cervenka, A. J. & Miller, R. C.
System:
The UNT Digital Library
Measurement Through the Speed of Sound of Static Pressures on the Rear of Unswept and Sweptback Circular Cylinders and on the Rear and Sides of a Wedge by the NACA Wing-Flow Method
Report presenting static-pressure measurements made through the speed of sound by the NACA wing-flow method at the back of two unswept circular cylinders and one sweptback cylinder. Static pressures were found to decrease considerably with an increase in Mach number. Information about the length and diameter of the cylinders and how it affects measurements is provided.
Date:
July 21, 1948
Creator:
Sawyer, Richard H. & Daum, Fred L.
System:
The UNT Digital Library