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NACA Research Memorandums
183
Atomic Energy Commission Reports
63
Oak Ridge National Laboratory Reports
33
Hanford Works Reports
26
NACA Technical Reports
24
University of California Radiation Laboratory Reports
21
HW (Series)
16
ORNL (Series)
12
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11
AEC research and development report
10
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367 Matching Results
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Stability of Ballistic Reentry Bodies
Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date:
August 11, 1958
Creator:
Bird, John D. & Reese, David E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands
Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date:
August 11, 1958
Creator:
Cheatham, Donald C. & Brissenden, Roy F.
Object Type:
Report
System:
The UNT Digital Library
Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles
Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date:
February 11, 1952
Creator:
Rousso, Morris D. & Baughman, L. Eugene
Object Type:
Report
System:
The UNT Digital Library
Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel
Report discussing tests of a model of a B-36J/RF-84F tip-coupled airplane to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain information about the dynamic stability characteristics. The variables studied were the skew angle of the fighter-bomber coupling, the fighter longitudinal position, the fighter and bomber loading, angle of sideslip, degrees of body freedom, and number of fighters. Flutter was primarily found to occur when the fighter roll frequency was near the natural chordwise-bending frequency of the bomber wing.
Date:
January 11, 1956
Creator:
Neely, Robert H.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance
Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date:
October 11, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14
From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date:
August 11, 1958
Creator:
Stoney, William E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder
"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).
Date:
May 11, 1955
Creator:
Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane
Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date:
October 11, 1951
Creator:
Draper, John W.
Object Type:
Report
System:
The UNT Digital Library
Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5
Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date:
June 11, 1953
Creator:
Hall, James R. & Hopko, Russell N.
Object Type:
Report
System:
The UNT Digital Library
Effect of Dissociation on Exhaust-Nozzle Performance
Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Net jet thrusts for equilibrium flow were three to five times that for frozen flow at Mach 10 for the three fuels cited, a hydrocarbon, hydrogen, and pentaborane. Results regarding dissociation energies, reaction rate, residence time, and estimated minimum performance are provided.
Date:
June 11, 1958
Creator:
Reynolds, T. W.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder
Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.
Date:
May 11, 1955
Creator:
Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
Object Type:
Report
System:
The UNT Digital Library
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
"Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date:
February 11, 1955
Creator:
Arbic, Richard G.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds
Report presenting an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures for a range of Mach numbers and Reynolds numbers. The cause of fin failure was determined to be the launching shoes that caused the missiles to trim at increasingly negative angles of attack. Additional testing with wing spoilers and alternate booster fins was also conducted.
Date:
December 11, 1950
Creator:
Nelson, Warren H.
Object Type:
Report
System:
The UNT Digital Library
Effect of pressure level on afterburner-wall temperatures
Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date:
June 11, 1958
Creator:
Shillito, Thomas B. & Smolak, George R.
Object Type:
Report
System:
The UNT Digital Library
Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane
Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.
Date:
October 11, 1954
Creator:
Vargo, Donald J.
Object Type:
Report
System:
The UNT Digital Library
Experimental Sea-Level Static Investigation of a Short Afterburner
Sea-level static testing of turbojet engine afterburner.
Date:
May 11, 1954
Creator:
Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Date:
March 11, 1947
Creator:
Loving, Donald L.
Object Type:
Report
System:
The UNT Digital Library
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections
Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Date:
December 11, 1947
Creator:
Turner, Howard L.
Object Type:
Report
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine 3: performance with tail-pipe burning in standard-size tail pipe
From Introduction: "Evaluation of tail-pipe burning in this engine with a larger tail-pipe combustion chamber is discussed in reference 1. Results of investigations on tail-pipe burning in this engine at static sea-level conditions are presented in reference 2. An investigation of thrust augmentation by means of injecting water at the inlet of an axial-flow compressor engine is discussed in reference 3."
Date:
August 11, 1947
Creator:
Fleming, William A. & Golladay, Richard L.
Object Type:
Report
System:
The UNT Digital Library
Observations on an aileron-flutter instability encountered on a 45 degree swept-back wing in transonic and supersonic flight
Report presenting a flight test of a supersonic research pilotless aircraft in which large-amplitude aileron oscillations, most likely aileron compressibility flutter, were encountered in the transonic and supersonic speed ranges. Results regarding power-on flight and coasting flight are provided.
Date:
April 11, 1947
Creator:
Pitkin, Marvin; Gardner, William N. & Curfman, Howard J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane
Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date:
March 11, 1947
Creator:
Bartlett, Walter A., Jr. & Goral, Edwin B.
Object Type:
Report
System:
The UNT Digital Library
Calculated Performance of Nuclear Turbojet Powered Airplane at Flight Mach Number of 0.9
"An analysis was made at flight Mach number of 0.9 to estimate performance of nuclear-energy-powered turbojet engine and optimum engine operating conditions and to determine gross weight and load-carrying capacity of airplane powered by such an engine. The size of airplane required to carry disposable load of 20,000 pounds was found to vary from approximately 300,000 to 900,000 pounds depending on assumptions. For a reactor tube-wall mean temperature of 2500 degrees R, turbine-inlet temperature of 2000 degrees R, reactor-free-flow-area ratio of 0.33, reactor-shielding-material specific gravity of 6.0, shielding thickness of 3.0 feet, and altitude of 30,000 feet, the airplane gross weight required to carry a 20,000 payload is 545,000 pounds" (p. 1).
Date:
May 11, 1950
Creator:
Doyle, Ronald B.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle
From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Date:
August 11, 1950
Creator:
Jansen, Emmert T. & Thorman, H. Carl
Object Type:
Report
System:
The UNT Digital Library
Extension of boundary-layer heat-transfer theory to cooled turbine blades
An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Date:
August 11, 1950
Creator:
Brown, W. Byron & Donoughe, Patrick L.
Object Type:
Report
System:
The UNT Digital Library