Resource Type
Serial/Series Title
NACA Research Memorandums
181
Atomic Energy Commission Reports
99
Hanford Works Reports
42
NACA Technical Reports
37
HW (Series)
32
University of California Radiation Laboratory Reports
17
Oak Ridge National Laboratory Reports
16
Report (U.S. Atomic Energy Commission)
15
GJBX
13
Battelle Memorial Institute Reports
10
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439 Matching Results
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Pressure Distributions at Mach Numbers of 1.6 and 1.9 of a Conically Cambered Wing of Triangular Plan Form With and Without Pylon-Mounted Engine Nacelles
Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.
Date:
April 20, 1956
Creator:
Phelps, E. Ray
Object Type:
Report
System:
The UNT Digital Library
The Influence of Surface Injection on Heat-Transfer and Skin Friction Associated With the High-Speed Turbulent Boundary Layer
Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.
Date:
February 20, 1956
Creator:
Rubesin, Morris W.
Object Type:
Report
System:
The UNT Digital Library
Investigation to Determine Effects of Center-of-Gravity Location on the Transonic Flutter Characteristics of a 45 Degree Sweptback Wing
Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.
Date:
February 20, 1956
Creator:
Jones, George W., Jr. & Unangst, John R.
Object Type:
Report
System:
The UNT Digital Library
Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385
From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date:
October 20, 1955
Creator:
Blanchard, Ulysse J. & Carter, Arthur W.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Modified Baffles and Auxiliary-Cooling Ducts on the Cooling of a Double-Row Radial Engine
Report discussing testing to determine the cooling effect of modified baffles and auxiliary-cooling ducts on the rear-row cylinders of a double-row radial engine. The modified baffles were found to reduce the temperatures of the exhaust-valve seats, but did not have an effect on the valve-guide temperatures. The auxiliary-cooling ducts reduced temperatures of the exhaust-valve seats and rear spark plug gaskets.
Date:
March 20, 1945
Creator:
Gendler, Stanley L. & Geisenheyner, Robert M.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Radome Icing and Icing Protection
Memorandum presenting an investigation conducted in the icing research tunnel to determine the icing characteristics, the effects of icing on radar operation, and the protection requirements for two radome configurations. The radomes were for the F-89 airplane and were investigated at airspeeds up to 290 miles per hour, air total temperatures from -15 to 20 degrees Fahrenheit, water contents up to 1.0 gram per cubic meter, and angles of attack of 0 and 4 degrees.
Date:
January 20, 1953
Creator:
Lewis, James P. & Blade, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.
Date:
May 20, 1957
Creator:
Lee, John B.
Object Type:
Report
System:
The UNT Digital Library
A Heated-Wire Liquid-Water-Content Instrument and Results of Initial Flight Tests in Icing Conditions
Memorandum presenting an investigation of a flight version of the NACA heated-wire liquid-water-content instrument, which was constructed and flight tested in natural icing conditions. Data obtained simultaneously with rotting multicylinders indicated that reliable flight measurements of liquid-water content could be made with the heated-wire instrument.
Date:
January 20, 1955
Creator:
Neel, Carr B.
Object Type:
Report
System:
The UNT Digital Library
Operation of an Experimental Air-Cooled Turbojet Engine at Turbine-Inlet Temperatures From 2200 R to 2935 R
Memorandum presenting an experimental investigation on a production-model turbojet engine modified by the substitution of special combustors and air-cooled turbine stator and rotor assemblies to determine some of the problems pertinent to the operation of air-cooled engines at turbine-inlet temperatures over 2200 degrees R. The investigation was conducted in an altitude chamber at simulated altitudes of 50,000 and 60,000 feet and a simulated flight Mach number of 0.8. Results regarding the combustion system, turbine stator, turbine rotor blades, turbine disks, and tailcone and other engine parts are provided.
Date:
August 20, 1956
Creator:
Cochran, Reeves P.; Dengler, Robert P. & Esgar, Jack B.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of a High Subsonic Mach Number Turbine Having High Rotor Blade Suction-Surface Diffusion
Memorandum presenting a high subsonic Mach number turbine with high suction-surface diffusion investigated experimentally. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub input.
Date:
November 20, 1956
Creator:
Nusbaum, William J. & Hauser, Cavour H.
Object Type:
Report
System:
The UNT Digital Library
Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine
Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.
Date:
November 20, 1956
Creator:
Breitwieser, Roland & Useller, James W.
Object Type:
Report
System:
The UNT Digital Library
Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58
Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date:
June 20, 1958
Creator:
Hollinger, James A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.
Date:
May 20, 1957
Creator:
Lee, John B.
Object Type:
Report
System:
The UNT Digital Library
Performance of Variable Two-Dimensional Inlet Designed for Engine-Inlet Matching 1 - Performance at Design Mach Number of 3.07
Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.
Date:
November 20, 1956
Creator:
Beheim, M. A. & Gertsma, L. W.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation of Effects of Gamma Radiation on Age-Hardening Rate of an Aluminum-Copper Alloy
"A preliminary investigation was made to determine the effects of gamma radiation on the age-hardening rate of an aluminum-copper alloy at temperatures of 32 and 70 degrees Fahrenheit. The gamma radiation from a 100-milligram radium source appeared to have no significant effect on the age-hardening rate of the alloy. A metallographic examination of the test specimens showed no microstructural changes that could be attributed to gamma radiation" (p. 1).
Date:
June 20, 1947
Creator:
Kittel, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics Including Scale Effect of Several Wings and Bodies Alone and in Combination at a Mach Number of 1.53
From Introduction: "In the present report, the results for the wings and bodies of revolution alone are first analyzed in comparison with exiting theory."
Date:
December 20, 1946
Creator:
Van Dyke, Milton D.
Object Type:
Report
System:
The UNT Digital Library
Drag Measurements of a 34 Degree Swept-Forward and Swept-Back NACA 65-009 Airfoil of Aspect Ratio 2.7 as Determined by Flight Tests at Supersonic Speeds
Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.
Date:
February 20, 1947
Creator:
Alexander, Sidney R.
Object Type:
Report
System:
The UNT Digital Library
Determination of Coupled Modes and Frequencies of Swept Wings by Use of Power Series
"A solution is presented for the coupled modes and frequencies of swept wings mounted on a fuselage. The energy method is used in conjunction with power series to obtain the characteristic equations for both symmetrical and asymmetrical vibration. A numerical example which is susceptible to exact solution is presented, and the results for the exact solution and the solution presented in this paper show excellent agreement" (p. 1).
Date:
October 20, 1947
Creator:
Anderson, Roger A.
Object Type:
Report
System:
The UNT Digital Library
Measurements of the effects of thickness ratio and aspect ratio on the drag of rectangular-plan-form airfoils at transonic speeds
Report presenting testing conducted on two airfoils from a series of rectangular-plan-form airfoils of aspect ratios 7.6 and 5.1 and with NACA 65-006, 65-009, and 65-012 sections using the free-fall method. Results regarding the time histories, ground-velocity data, airfoil drag measurements, and drag coefficients are provided.
Date:
June 20, 1947
Creator:
Thompson, Jim Rogers & Mathews, Charles W.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Lateral Control Characteristics as Measured in Abrupt Aileron Rolls at Mach Numbers Up to 0.86
Report presenting flight measurements of the lateral control characteristics of the Douglas D-558-II airplane in abrupt rudder-fixed aileron rolls. Results regarding the aileron rolling effectiveness, time histories, and aileron effectiveness variation with Mach number are provided.
Date:
July 20, 1950
Creator:
Wilmerding, J. V.; Stillwell, W. H. & Sjoberg, S. A.
Object Type:
Report
System:
The UNT Digital Library
Cooling of gas-turbines 7: effectiveness of air cooling of hollow turbine blades with inserts
Report presenting an analytical investigation to determine primarily the reduction in cooling-air requirement and the increase in effective gas temperature for the same quantity of cooling air resulting from the use of an insert in the cooling-air passage of a hollow air-cooled turbine blade.
Date:
October 20, 1947
Creator:
Bressman, Joseph R. & Livingood, John N. B.
Object Type:
Report
System:
The UNT Digital Library
Calculated condenser performance for a steam turbine power plant for aircraft
Report presenting calculations to determine the effect of several operating conditions on the performance of condensers for steam-turbine power plants. The analysis covered a range of turbine-inlet pressures and turbine-outlet pressures for various condenser cooling-air pressure drops, flight speeds, and altitudes. Results regarding steam-cycle performance, effect of turbine-outlet pressure on condenser performance, effect of cooling-air pressure drop on condenser performance, effect of turbine-inlet temperature on condenser performance, and power-plant-weight estimates are provided.
Date:
May 20, 1948
Creator:
Humble, Leroy V. & Doyle, Ronald B.
Object Type:
Report
System:
The UNT Digital Library
Measurements of Aileron Effectiveness of Bell X-1 Airplane Up to a Mach Number of 0.82
"Abrupt, rudder-fixed aileron rolls have been made with the Bell X-1 airplane having a 10-percent-thick wing in glides to a Mach number of 0.82 at about 30,000 feet pressure altitude. Aileron movements were between one-fourth and one-half of full deflection. These aileron rolls indicate that Mach number has little effect on the aileron effectiveness up to a Mach number of 0.82" (p. 1).
Date:
June 20, 1949
Creator:
Drake, Hubert M.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Effect of Boundary-Layer Suction on Profile-Drag Coefficient at Supercritical Mach Numbers
Memorandum presenting flight tests with a fighter airplane to study the effect of boundary-layer suction aft of the shock wave on airfoil drag at supercritical Mach numbers and high Reynolds numbers. Airfoil chord force was determined from pressure-distribution measurements obtained at a range of Mach numbers at steady dives. Results of the tests showed no measurable effect of suction for the suction coefficient available.
Date:
September 20, 1949
Creator:
Skoog, Richard B.
Object Type:
Report
System:
The UNT Digital Library