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Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber
Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated without any appreciable sacrifice in engine acceleration time.
Date:
September 21, 1956
Creator:
McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
System:
The UNT Digital Library
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.
Date:
September 10, 1958
Creator:
Turner, Howard L. & Heinle, Donovan R.
System:
The UNT Digital Library
Performance Characteristics of Several Divergent-Shroud Aircraft Ejectors
Report presenting an investigation of ten divergent- and two cylindrical-shroud ejectors to determine internal ejector performance over a range of pressure ratios and expansion area ratios for Mach numbers up to about 3. Results regarding jet-thrust and air-handling characteristics and net-thrust performance are provided.
Date:
September 8, 1955
Creator:
Greathouse, William K. & Beale, William T.
System:
The UNT Digital Library
Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2
Report discussing testing of the effects of aeroelasticity on the rolling effectiveness on a model of a McDonnell F-101A airplane wing. The aeroelastic losses varied based on the Mach number and altitude.
Date:
September 2, 1955
Creator:
English, Roland D.
System:
The UNT Digital Library
Minimum Drag of Four Versions of a Swept-Wing Fighter Airplane Obtained From Flight Tests of Rocket-Boosted Models at Mach Numbers From 0.81 to 1.71
Memorandum presenting tests conducted with four specific versions of a swept-wing fighter airplane, which indicate that a large reduction in external-drag coefficient was accomplished by redesigning the original configuration. The forebody modifications, which consisted of a smaller canopy, slimmer nose, and sharper inlet lip, reduced the value of the external-drag coefficient from 0.044 to 0.042 at a Mach number of 1.05 and from 0.042 to 0.040 at a Mach number of 1.28.
Date:
September 7, 1956
Creator:
Hastings, Earl C., Jr.
System:
The UNT Digital Library
Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53
Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date:
September 28, 1953
Creator:
Bland, William M., Jr. & Nelson, Robert L.
System:
The UNT Digital Library
Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18
Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date:
September 17, 1958
Creator:
Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
System:
The UNT Digital Library
A Method for Estimating the Components of Lift of Wing-Body Combinations at Supersonic Speeds
Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.
Date:
September 16, 1952
Creator:
Tucker, Warren A.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Wing-Root Inlet Configuration With Various Modifications at Mach Numbers of 1.41, 1.81, and 2.01
Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.
Date:
September 26, 1957
Creator:
Robins, A. Warner
System:
The UNT Digital Library
Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7
Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.
Date:
September 23, 1952
Creator:
Chubb, Robert S.
System:
The UNT Digital Library
The Effect of Curvature on the Transition From Laminar to Turbulent Boundary Layer
Note presenting a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer that had been found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing.
Date:
September 1937
Creator:
Clauser, Milton & Clauser, Francis
System:
The UNT Digital Library
Simplified Method for Determination of Critical Height of Distributed Roughness Particles for Boundary-Layer Transition at Mach Numbers From 0 to 5
Note presenting a simplified method for determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components in a wind tunnel with zero heat transfer. The method has been applied to various types of configurations in several wind-tunnel investigations.
Date:
September 1958
Creator:
Braslow, Albert L. & Knox, Eugene C.
System:
The UNT Digital Library
Impingement of Cloud Droplets on 36.5-Percent-Thick Joukowski Airfoil at Zero Angle of Attack and Discussion of Use as Cloud Measuring Instrument in Dye-Tracer Technique
"The trajectories of droplets in the air flowing past a 36.5-percent-thick Joukowski airfoil at zero angle of attack were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and cover a large range of flight and atmospheric conditions. With the detailed impingement information available, the 36.5-percent-thick Joukowski airfoil can serve the dual purpose of use as the principal element in instruments for making measurements in clouds and of a basic shape for estimating impingement on a thick streamlined body" (p. 1).
Date:
September 1957
Creator:
Brun, R. J. & Vogt, Dorothea E.
System:
The UNT Digital Library
Tests of the Northrop XB-62 Missile in the Ames 40- by 80-Foot Wind Tunnel
Memorandum presenting a series of tests made on a full-scale Northrop XB-62 missile to determine the cause of a directional out-of-trim condition which was encountered on the initial missile flight tests. The results indicated that the directional out-of-trim condition was caused by aerodynamic loads induced by engine operation.
Date:
September 27, 1954
Creator:
Graham, David
System:
The UNT Digital Library
An Empirical Method Permitting Rapid Determination of the Area, Rate and Distribution of Water-Drop Impingement on an Airfoil of Arbitrary Section at Subsonic Speeds
"An empirical method for the determination of the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The procedure represents an initial step toward the development of a method which is generally applicable in the design of thermal ice-prevention equipment for airplane wing and tail surfaces. Results given by the proposed empirical method are expected to be sufficiently accurate for the purpose of heated-wing design, and can be obtained from a few numerical computations once the velocity distribution over the airfoil has been determined" (p. 1).
Date:
September 1951
Creator:
Bergrun, Norman R.
System:
The UNT Digital Library
Impingement of water droplets on an NACA 65(sub 1) -212 airfoil at an angle of attack of 4 degrees
The trajectories of droplets in the air flowing past an NACA 651-212 airfoil at an angle of attack of 40 were determined. The collection efficiency, the area of droplet impingement, and the rate of droplet impingement were calculated from the trajectories and are presented herein.
Date:
September 10, 1952
Creator:
Brun, Rinaldo J.; Serafini, John S. & Moshos, George J.
System:
The UNT Digital Library
Impingement of droplets in 90 degree elbows with potential flow
Trajectories were determined for droplets in air flowing through 90 deg elbows especially designed for two-dimensional potential motion with low pressure losses. The elbows were established by selecting as walls of each elbow two streamlines of the flow field produced by a complex potential function that establishes a two-dimensional flow around a 90 deg bend. An unlimited number of elbows with slightly different shapes can be established by selecting different pairs of streamlines as walls. The elbows produced by the complex potential function selected are suitable for use in aircraft air-intake ducts.
Date:
September 1953
Creator:
Hacker, Paul T.; Brun, Rinaldo J. & Boyd, Bemrose
System:
The UNT Digital Library
An Instrument Employing a Coronal Discharge for the Determination of Droplet-Size Distribution in Clouds
From Summary: "A flight instrument that uses electric means for measuring the droplet-size distribution in above-freezing clouds has been devised and given preliminary evaluation in flight. An electric charge is placed on the droplets and they are separated aerodynamically according to their mass. Because the charge placed on the droplets is a. function of the droplet size, the size spectrum can 'be determined by measurement of the charge deposited on cylinders of several different sizes placed to intercept the charged droplets. An expression for the rate of charge acquisition by a water droplet in a field of coronal discharge is derived."
Date:
September 1951
Creator:
Brun, Rinaldo J.; Levine, Joseph & Kleinknecht, Kenneth S.
System:
The UNT Digital Library
Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds
"A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date:
September 18, 1951
Creator:
Levine, Joseph & Kleinknecht, Kenneth S.
System:
The UNT Digital Library
Comparison of Heat Transfer from Airfoil in Natural and Simulated Icing Conditions
"An investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investigation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icing was indicated by the forward movement of transition from laminar to turbulent heat transfer" (p. 1).
Date:
September 1951
Creator:
Gelder, Thomas F. & Lewis, James P.
System:
The UNT Digital Library
Investigation of Flow Coefficient of Circular, Square, and Elliptical Orifices at High Pressure Ratios
Note presenting an experimental investigation conducted to determine the orifice coefficient of a jet directed perpendicularly to an air stream as a function of pressure ratio and jet Reynolds number for circular, square, and elliptical orifices. The effect of air-stream velocity on the jet flow was also determined for three tunnel-air velocities. Results regarding jets discharging into still air and effect of tunnel-air velocity on jet flow.
Date:
September 1949
Creator:
Callaghan, Edmund E. & Bowden, Dean T.
System:
The UNT Digital Library
A General Correlation of Temperature Profiles Downstream of a Heated-Air Jet Directed Perpendicularly to an Air Stream
"An experimental investigation was conducted to determine the temperature profile downstream of a heated-air jet directed perpendicularly to an air stream. The profiles were determined at several positions downstream of the jet as functions of jet density, jet velocity, free-stream density, free-stream velocity, jet temperature, and orifice flow coefficient. A method is presented which yields a good approximation of the temperature profile in terms of dimensionless parameters of the flow and geometric conditions" (p. 1).
Date:
September 1951
Creator:
Callaghan, Edmund E. & Ruggeri, Robert S.
System:
The UNT Digital Library
High-Altitude Cooling 3: Radiators
Report details the methods of determining the heat-transfer rate, pressure drop, and drag power of high-altitude radiators. Performance charts are provided for a wide range of design variables.
Date:
September 1944
Creator:
Nielsen, Jack Norman
System:
The UNT Digital Library
Icing Properties of Noncyclonic Winter Stratus Clouds
Note presenting measurements of the vertical distribution of liquid water concentration and drop size in winter stratus clouds in the absence of significant cyclonic or frontal activity. The observations indicate that the clouds are formed by turbulent mixing of the lower layers of the atmosphere, resulting in a region of constant specific humidity and adiabatic lapse rates. Calculations based on the observations were used to construct a graph that gives the liquid water concentration in terms of the temperature at the cloud base and the height above the base.
Date:
September 1947
Creator:
Lewis, William
System:
The UNT Digital Library