Resource Type
Serial/Series Title
NACA Research Memorandums
150
Atomic Energy Commission Reports
40
Hanford Works Reports
35
HW (Series)
25
Oak Ridge National Laboratory Reports
11
Battelle Memorial Institute Reports
10
NACA Technical Reports
9
University of California Radiation Laboratory Reports
9
BMI (Series)
8
Report (U.S. Atomic Energy Commission)
7
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Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination
Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date:
November 20, 1957
Creator:
Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
Object Type:
Report
System:
The UNT Digital Library
Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date:
January 20, 1958
Creator:
Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of a Turbojet Engine Using Pentaborane Fuel
Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.
Date:
May 20, 1957
Creator:
Sivo, Joseph N.
Object Type:
Report
System:
The UNT Digital Library
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
Date:
May 20, 1958
Creator:
Gertsma, L. W. & Beheim, M. A.
Object Type:
Report
System:
The UNT Digital Library
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
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
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
Temperature and pressure distributions in dual parallel jets impinging on the ground from a turbojet engine
Report presenting an investigation to determine the temperature and pressure distributions in the jets issuing from two parallel nozzles of a turbojet engine located close together and impinging on the ground at an angle of 20 degrees. Results regarding the jet-nozzle pressure ratio, constant-temperature parameters, and temperature contours are provided.
Date:
February 20, 1950
Creator:
Farmer, J. Elmo; Stepka, Francis S. & Garrett, Floyd B.
Object Type:
Report
System:
The UNT Digital Library
Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
"Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).
Date:
April 20, 1950
Creator:
Fisher, Lloyd J. & Morris, Garland J.
Object Type:
Report
System:
The UNT Digital Library
Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the D-558-I Research Airplane Through a Mach Number Range of 0.80 to 0.89 and Throughout the Normal-Force-Coefficient Range at Mach Numbers of 0.61, 0.70, 0.855, and 0.88
"Tabulated pressure coefficients and aerodynamic characteristics obtained in flight from pressure distributions over six chordwise rows of orifices on the right wing of the D-558-I research airplane (BuAero No. 37972) are presented. The data were obtained through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.70, 0.855, and 0.88. This paper supplements similar tabulated data which have been presented in NACA RM L50J10 and NACA RM L50L12a" (p. 1).
Date:
August 20, 1951
Creator:
Keener, Earl R. & Bandish, Rozalia M.
Object Type:
Report
System:
The UNT Digital Library
The Effect on Zero-Lift Drag of an Indented Fuselage or a Thickened Wing-Root Modification to a 45 Degree Sweptback Wing-Body Configuration as Determined by Flight Tests at Transonic Speeds
Report presenting a study of rocket-powered models at transonic speeds to determine the effect on the zero-lift drag coefficient of an indented fuselage modification and a thickened wing-root modification of a swept-wing airplane configuration. Results regarding the variation of drag coefficient with Mach number, effect of wing root thickening, and wing-plus-interference drag coefficients for the tested models are provided.
Date:
September 20, 1951
Creator:
Pepper, William B.
Object Type:
Report
System:
The UNT Digital Library
Experimental downwash and wake characteristics at subsonic and supersonic Mach numbers behind an unswept, tapered wing, of aspect ratio 2.67 with leading-and trailing-edge flaps
Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.
Date:
April 20, 1951
Creator:
Stivers, Louis S., Jr.; Walker, Harold J. & Beard, Luther, Jr.
Object Type:
Report
System:
The UNT Digital Library
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback: a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40
Report discussing a pressure-distribution investigation of a wing of a supersonic aircraft in the presence of a fuselage at a specified Mach number and aerodynamic chord. The wing had a quarter chord swept back 40 degrees, an aspect ratio of 4, a taper ratio of 0.5, and 10-percent-thick circular-arc sections perpendicular to the quarter-chord line. The results were compared to a similar investigation at a different Mach number.
Date:
April 20, 1951
Creator:
Smith, Norman F.; Kainer, Julian H. & Webster, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Effects of Several Arrangements of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short 2:1 Diffuser
Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators, other arrangements investigated, and a comparison with results from previous diffuser research are provided.
Date:
February 20, 1951
Creator:
Valentine, E. Floyd & Carroll, Raymond B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)
Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle of attack and angle of attack except over the aft leeward side of body. At angle of attack, pitot pressure measurements in plane of model base indicated a pair of symmetrically disposed vortices on leeward side of body.
Date:
July 20, 1950
Creator:
Luidens, Roger W. & Simon, Paul C.
Object Type:
Report
System:
The UNT Digital Library
Effect of ram-jet pressure pulsations on supersonic-diffuser performance
Experimental study of effects of combustion roughness and controlled mechanical oscillations on diffuser operation was conducted on an 8-inch ram jet at Mach number 1.87. Within experimental accuracy, the optimum mean combustion-chamber static pressure occurred when the maximum instantaneous static pressure equalled the optimum steady-flow value and the corresponding decrement in optimum mean static pressure was equal to one-half the total amplitude of the pressure pulsations. A marked attenuation of amplitude of cold-buzz pressure fluctuations was effected over limited range of subcritical diffuser operation by means of properly tuned rotating disk located in combustion chamber.
Date:
November 20, 1950
Creator:
Connors, James F.
Object Type:
Report
System:
The UNT Digital Library