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Technical Report Archive and Image Library
266
National Advisory Committee for Aeronautics Collection
159
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118
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82
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62
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2
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1
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153
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39
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26
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21
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8
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449 Matching Results
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Progress Report on AEC Contract on Research and Development Program on Scintillation Crystals: Period 1 January 1956 to 1 April 1956
From Abstract: "This report covers the preliminary literature survey and the screening of activated cesium iodide and several alkali halides to qualitatively determine their luminerscence. The report also includes a proposal of the future work and a proposed budget for the 1957 fiscal year."
Date:
April 25, 1956
Creator:
Beadle, Robert
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01
Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date:
October 25, 1957
Creator:
Morris, Owen G. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From
"An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotless Aircraft Research Division by utilizing rocket-propelled test vehicles. No effects of mutual interference between the midspan spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared with the spoiler because of wing twisting" (p. 1).
Date:
February 25, 1952
Creator:
Strass, H. Kurt & Marley, Edward T.
Object Type:
Report
System:
The UNT Digital Library
A Summary of Results Obtained During Flight Simulation of Several Aircraft Prototypes With Variable-Stability Airplanes
Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.
Date:
May 25, 1956
Creator:
McNeill, Walter E. & Creer, Brent Y.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date:
August 25, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
Object Type:
Report
System:
The UNT Digital Library
A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes
Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.
Date:
February 25, 1958
Creator:
Setze, Paul C. & Nusbaum, William J.
Object Type:
Report
System:
The UNT Digital Library
De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding
Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date:
May 25, 1953
Creator:
Ruggeri, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Data on Rain Deflection from Aircraft Windshields by Means of High-Velocity Jet-Air Blast
From Summary: "A preliminary experimental investigation is being conducted to determine the feasibility of preventing rain from impinging on aircraft windshields by means of high-velocity jet-air blast. The results indicate that rain deflection by jet blast appears feasible for flight speeds comparable with landing and take-off speeds of interceptor-type jet aircraft; however, attainment of good visibility through the mist generated by raindrop breakup presents a problem. For the simulated windshield and the lower windshield angles used in the investigation, air-flow rates of the order of 3.3 pounds per minute of unheated air per inch of windshield span were required for adequate rain deflection at a free-stream velocity of 135 miles per hour."
Date:
July 25, 1955
Creator:
Ruggeri, Robert S.
Object Type:
Report
System:
The UNT Digital Library
A Photographic Study of Freezing of Water Droplets Falling Freely in Air
From Summary: "A photographic technique for investigating water droplets of diameter less than 200 microns falling freely in air at temperatures between 0 C and -50 C has been devised and used to determine: (1) The shape of frozen droplets, (2) The occurrence of collisions of partly frozen or of frozen and liquid droplets, and (3) The statistics on the freezing temperatures of individual free-falling droplets."
Date:
February 25, 1952
Creator:
Dorsch, Robert G. & Levine, Joseph
Object Type:
Report
System:
The UNT Digital Library
Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01
Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.
Date:
March 25, 1955
Creator:
Robinson, Ross B.
Object Type:
Report
System:
The UNT Digital Library
The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin
"Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).
Date:
October 25, 1956
Creator:
Buell, Donald A. & Tinling, Bruce E.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail
Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.
Date:
April 25, 1955
Creator:
Beam, Benjamin H.; Reed, Verlin D. & Lopez, Armando E.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of a Series of Practice Bombs
Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.
Date:
October 25, 1957
Creator:
Ward, Donald H.
Object Type:
Report
System:
The UNT Digital Library
Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis
"Model investigations were made to determine the ditching characteristics of three typical multiengine airplanes equipped with possible arrangements of hydro-ski ditching gear. The behavior of the models was determined from visual observations, acceleration records, and motion pictures of the landings. Data are presented in tabular form and sequence photographs" (p. 1).
Date:
April 25, 1950
Creator:
Fisher, Lloyd J.
Object Type:
Report
System:
The UNT Digital Library
Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6
Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.
Date:
January 25, 1955
Creator:
Henning, Allen B. & Brown, Clarence A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight Test of an End-Burning Solid-Fuel Ramjet
Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.
Date:
March 25, 1954
Creator:
Bartlett, Walter A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System
Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date:
June 25, 1958
Creator:
Smith, Arthur L. & Grobman, Jack S.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds
Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.
Date:
April 25, 1950
Creator:
Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Effect of combustion-chamber pressure and nozzle expansion ratio on theoretical performance of several rocket propellant systems
Theoretical calculations of specific impulse to determine the separate effects of increasing the combustion-chamber pressure and the nozzle expansion ratio on the performance of the propellants, hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine and AN-F-58 fuel - white fuming nitric acid (95 percent). The results indicate that an increase in specific impulse obtainable with an increase in combustion-chamber pressure is almost entirely caused by the increased expansion ratio through the nozzle.
Date:
May 25, 1956
Creator:
Morrell, Virginia E.
Object Type:
Report
System:
The UNT Digital Library
Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds
Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.
Date:
August 25, 1950
Creator:
Kraft, Christopher C., Jr. & Mathews, Charles W.
Object Type:
Report
System:
The UNT Digital Library
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions
A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Date:
May 25, 1950
Creator:
Acker, Loren W. & Kleinknecht, Kenneth S.
Object Type:
Report
System:
The UNT Digital Library
Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.
Date:
January 25, 1950
Creator:
Czarnecki, K. R. & Mueller, James N.
Object Type:
Report
System:
The UNT Digital Library
Wing-flow measurements of longitudinal stability and control characteristics of a canard airplane configuration with a 45 degree sweptback wing and a triangular all-movable control surface
Report presenting measurements of the longitudinal stability and control characteristics of a canard airplane configuration using the wing-flow method. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model with control settings between several different degrees. The experimental data are presented in summarized or abridged form and calculated trim curves are presented for various flight loading conditions.
Date:
August 25, 1950
Creator:
Crane, Harold L. & Adams, James J.
Object Type:
Report
System:
The UNT Digital Library
Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight
Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date:
June 25, 1951
Creator:
Carman, L. Robert & Carden, John R.
Object Type:
Report
System:
The UNT Digital Library