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Serial/Series Title
NACA Research Memorandums
162
Atomic Energy Commission Reports
52
NACA Technical Reports
35
Oak Ridge National Laboratory Reports
23
Hanford Works Reports
22
University of California Radiation Laboratory Reports
15
HW (Series)
14
ORNL (Series)
9
BNL (Series)
7
Brookhaven National Laboratory Reports
7
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339 Matching Results
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Experimental investigation of air-cooled turbine blades in turbojet engine 9: evaluation of the durability of noncritical rotor blades in engine operation
The durability of five different structural or cooling configurations or combination of both of air-cooled blades made of noncritical materials was investigated in a modified turbojet engine. The greater part of the investigation was conducted at an engine speed of 11,500 rpm, a turbine-inlet temperature of approximately 1670 degrees F, and a cooling-air to combustion gas flow ratio per blade of 0.05. The results of the investigation indicated that air-cooled blades made of noncritical metals can be operated for extended periods of time in engines at current inlet temperatures; however, before these blades are considered completely satisfactory for gas-turbine application, some means such as coatings is required to inhibit the oxidation of the blades.
Date:
December 5, 1951
Creator:
Stepka, Francis S. & Hickel, Robert O.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel
Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Date:
November 5, 1951
Creator:
Sleeman, William C., Jr.; Klevatt, Paul L. & Linsley, Edward L.
Object Type:
Report
System:
The UNT Digital Library
Investigation of dynamic characteristics of a turbine-propeller engine
Time constants that characterize engine speed response of a turbine-propeller engine over the cruising speed range for various values of constant fuel flow and constant blade angle were obtained both from steady-state characteristics and from transient operation. Magnitude of speed response to changes in fuel flow and blade angle was investigated and is presented in the form of gain factors. Results indicate that at any given value of speed in the engine cruising speed range, time constants obtained both from steady-state characteristics and from transient operation agree satisfactorily for any given constant fuel flow, whereas time constants obtained from transient operation exceed time constants obtained from steady-state characteristics by approximately 14 percent for any given blade angle.
Date:
September 5, 1951
Creator:
Oppenheimer, Frank L. & Jacques, James R.
Object Type:
Report
System:
The UNT Digital Library
The effects of oscillation amplitude and frequency on the experimental damping in pitch of a triangular wing having an aspect ratio of 4
Memorandum presenting the results of a wind-tunnel investigation of the damping in pitch of a model triangular wing with an aspect ratio of 4 combined with a slender pointed body. The investigation was conducted at Mach numbers from 0.10 to 0.95 for Reynolds numbers of 550,000 and 1,250,000 with additional data obtained at Reynolds numbers of 3,000,000 and 6,000,000 at Mach number 0.23. Results regarding the effects of oscillation amplitude, Mach number, Reynolds number, angle of attack, frequency, and pitching axis position are provided.
Date:
September 5, 1952
Creator:
Beam, Benjamin H.
Object Type:
Report
System:
The UNT Digital Library
Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers
Report presenting a study and experimental investigation on the pressure rise across shock waves required to cause separation of the boundary layer on a flat plate. The interaction of shock wave and boundary layer was investigated experimentally when the boundary layer was caused to separate from the surface of a tube. Results regarding testing and correlation with other results are provided.
Date:
May 5, 1952
Creator:
Donaldson, Coleman duP. & Lange, Roy H.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Low-Speed Stalling and Lift Characteristics
Report presenting the low-speed stalling and lift characteristics of the Douglas D-558-II airplane measured in a series of 1 g stalls in four different airplane configurations. Various combinations of landing gear, flaps, inlet-duct flaps, and slats were tested at a range of altitudes.
Date:
September 5, 1950
Creator:
Stillwell, W. H.; Wilmerding, J. V. & Champine, R. A.
Object Type:
Report
System:
The UNT Digital Library
Measurements in Flight of the Longitudinal Characteristics of Two Jet Aircraft, One With a Diving Tendency and the Other With a Climbing Tendency at High Mach Numbers
Memorandum presenting flight tests conducted on two straight-wing jet airplanes of generally similar configuration, one exhibiting a diving tendency and the other a climbing tendency, in order to investigate the cause for the particular type of behavior of each airplane at high Mach numbers. The results showed that the diving tendency experienced by the one airplane was due to the predominant effect of an increased angle of attack of the horizontal tail.
Date:
October 5, 1951
Creator:
Anderson, Seth B.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance of annular combustor type turbojet engine with JFC-2 fuel
An investigation was made comparing the performance of JFC-2 fuel and unleaded, clear gasoline in a 3000-pound-thrust turbojet engine. The JFC-2 fuel was a blend of percent diesel fuel and 25 percent aviation gasoline. Engine combustion efficiency was equal to that obtained with gasoline at rated engine speed and altitudes up to 35,000 feet, but at lower engine speeds or at higher altitudes the JFC-2 fuel gave lower combustion efficiency. No discernible difference was obtained in starting or low-speed combustiion blow-out characteristics of the two fuels. Turbine-discharge radial temperature profiles were nearly the same at altitudes up to 35,000 feet.
Date:
February 5, 1952
Creator:
Useller, James W.; Harp, James L., Jr. & Barson, Zelmar
Object Type:
Report
System:
The UNT Digital Library
Characteristics of a Wedge With Various Holder Configurations for Static-Pressure Measurements in Subsonic Gas Streams
The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less than that of the conventional probe for corresponding change of yaw angle.
Date:
September 5, 1951
Creator:
Gettelman, Clarence C. & Krause, Lloyd N.
Object Type:
Report
System:
The UNT Digital Library
Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds
Report presenting the results of an investigation to determine the effects of simulated skin wrinkling of the wing surface on the aerodynamic characteristics of two wing-body combinations. The lift, drag, and pitching moment of a low-wing wing-body combination with a plane triangular wing of aspect ratio 3 are presented for a range of Mach and Reynolds numbers.
Date:
August 5, 1952
Creator:
Heitmeyer, John C. & Smith, Willard G.
Object Type:
Report
System:
The UNT Digital Library
An analysis of the effect of a curved ramp on the take-off performance of catapult-launched airplanes
From Summary: "Results of flight-path computations are presented for launchings from a straight deck and the curved ramp under conditions of insufficient lift at the instant of take-off."
Date:
November 5, 1952
Creator:
Reed, Wilmer H., III
Object Type:
Report
System:
The UNT Digital Library
Instrumentation and calibration technique for flight calibration of angle-of-attack systems on aircraft
From Summary: "Data are presented on the instrumentation and calibration technique used in determining the position error of angle-of-attack sensors mounted on the fuselage of a 35 degree swept-wing fighter airplane. The true angle of attack was determined by the use of a nose boom with five angle-of-attack vanes spaced 20 inches apart on alternate sides of the boom. Errors due to boom bending, upwash around the boom, and vane floating angle were measured and corrections applied to all indicated angles of attack."
Date:
December 5, 1952
Creator:
McFadden, Norman M.; Holden, George R. & Ratcliff, Jack W.
Object Type:
Report
System:
The UNT Digital Library
Some Low-Speed Studies of the Effects of Wing Location on Wing-Deformation-Body-Freedom Flutter
Report presenting an investigation of flutter of wings mounted on the after portion of a body free to pitch was made in the flutter research tunnel. Uniform wings of 0 and 45 degrees sweep were tested at various positions rearward of the pitch axis. A low-frequency flutter was observed on the unswept wing, but no flutter was obtained for the swept wings.
Date:
November 5, 1952
Creator:
Widmayer, E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Analytical study of static and low-speed performance of thin propellers using two-speed gear ratios to obtain optimum rotational speeds
From Introduction: "The purpose of the present paper is to investigate the effect of two-speed gearing on the take-off efficiency under certain conditions. The present paper gives charts from which the efficiencies can be readily computed for optimum rotational speeds. Also included is a brief discussion of the static thrust of thin propellers, including the effect of camber on the static thrust."
Date:
November 5, 1952
Creator:
Gilman, Jean, Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds - drag due to lift and lift-drag ratio
Report presenting a method for predicting the drag due to lift and lift-drag ratio of all-movable wing and body combinations and all-movable wings in the presence of bodies at supersonic speeds. The method is used to calculate the factors for configurations at which experimental data are available.
Date:
December 5, 1952
Creator:
Katzen, Elliott D. & Pitts, William C.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the effects of geometric changes in an underwing pylon suspended external store installation on the aerodynamic characteristics of a 45 degree sweptback wing at high subsonic speeds
Report presenting an investigation in the high-speed 7- by 10-foot tunnel through a range of Mach numbers to determine the effects of external-store fineness ratio, store shape, store chordwise position, pylon thickness, pylon length, and pylon sweep angle on the aerodynamic characteristics of a number of underwing pylon-suspended external stores in combination with a 45 degree sweptback semispan wing and fuselage.
Date:
March 5, 1951
Creator:
Spreemann, Kenneth P. & Alford, William J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution, cambered and twisted for a trapezoidal span load distribution
Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, which has been twisted and cambered for a trapezoidal span load distribution at subsonic and supersonic Mach numbers.
Date:
February 5, 1951
Creator:
Smith, Willard G. & Phelps, E. Ray
Object Type:
Report
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle
Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach number of 0.19.
Date:
September 5, 1951
Creator:
Conrad, E. William & McAulay, John E.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of tail-pipe-burner design variables
Report summarizing several experimental tail-pipe-burner investigations to indicate the effects of tail-pipe-burner design variables on the performance and operating characteristics. Most of the configurations were investigated over a wide range of altitudes and flight Mach numbers. The results indicate the desirable design features of a tail-pipe burner that will operate with high combustion efficiency and exhaust-gas temperature up to an altitude of approximately 50,000 feet.
Date:
March 5, 1951
Creator:
Fleming, W. A.; Conrad, E. William & Young, W. A.
Object Type:
Report
System:
The UNT Digital Library
Altitude investigation of performance of turbine-propeller engine and its components
From Introduction: "Results presented herein show the altitude performance of the turbine-propeller engine and its components and the applicability of the generalization method for predicting engine and component performance at altitudes other than the test altitude. Data from a brief investigation of windmilling and altitude starting characteristics of the engine also presented."
Date:
October 5, 1950
Creator:
Wallner, Lewis E. & Saari, Martin J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method
Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Date:
May 5, 1950
Creator:
Lockwood, Vernard E.
Object Type:
Report
System:
The UNT Digital Library
Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-Lift Drag of Sweptback Low-Aspect-Ratio Wings
Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.
Date:
September 5, 1950
Creator:
Pittel, Murray
Object Type:
Report
System:
The UNT Digital Library
Characteristics of flow over inclined bodies of revolution
From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly accurately predicted by the theory but that the actual center of pressure is more rearward than the theory indicates."
Date:
March 5, 1951
Creator:
Allen, H. Julian & Perkins, Edward W.
Object Type:
Report
System:
The UNT Digital Library
Flight determined buffet boundaries of ten airplanes and comparisons with five buffeting criteria
Report presenting the flight-determined buffet boundaries of ten airplanes. Comparisons are made with five possible buffeting criteria related to airfoil-section characteristics. The primary factors that determine buffeting criteria are critical Mach number, Mach number of sonic flow at the crest, lift-divergence Mach number, lift-peak Mach number, and empirical buffeting criterion are provided.
Date:
January 5, 1951
Creator:
Gadeberg, Burnett L. & Ziff, Howard L.
Object Type:
Report
System:
The UNT Digital Library