UNT Libraries Government Documents Department - 221 Matching Results

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CRPL Exponential Reference Atmosphere

Description: From Introduction: "In this monograph, the background of the exponential reference atmosphere will be outlined and a set of radio ray tracings presented. These ray may be used for the solution of many problems involving refraction by means of the exponential reference atmosphere."
Date: October 29, 1959
Creator: Bean, B. R. & Thayer, G. D.
Item Type: Refine your search to only Report
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Strontium Program: Quarterly Summary Report, May 29, 1959

Description: From Abstract: "This report is one of a sequence of quarterly reports, each designed to up-date its predecessor beginning with HASL-42, "Environmental Contamination from Weapon Tests". Herein are presented data which have accrued since HASL-55. Levels of strontinum-90 in fallout, milk, air, water, vegetation, foods, and bone are given, based on data available from February 1, 1959 to May 20, 1959."
Date: May 29, 1959
Creator: Hardy, Edward P., Jr. & Klein, Stanley
Item Type: Refine your search to only Report
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Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design

Description: Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date: October 29, 1953
Creator: Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
Item Type: Refine your search to only Report
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Theoretical Performance of Mixtures of Liquid Ammonia and Hydrazine as Fuel With Liquid Fluorine as Oxidant for Rocket Engines

Description: Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal … more
Date: July 29, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Item Type: Refine your search to only Report
open access

Preliminary Transient Performance Data on the Fuel Control of the XRJ47-W-5 Ram-Jet Engine

Description: Report discussing the characteristics of the fuel control of the 48-inch diameter WRJ47-W-5 ramjet engine, including the time history of the fuel system pressures, fuel flow, and engine inlet total pressure. Oscillograph traces for the different variables are provided as well as the accuracy of the calibration factors.
Date: January 29, 1954
Creator: Welna, Henry J. & Smith, Ivan D.
Item Type: Refine your search to only Report
open access

Flight Investigation to Evaluate the Roll-Rate Stabilization System of the Naval Ordnance Test Station SIDEWINDER Missile at Mach Numbers From 0.9 to 2.3

Description: Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.
Date: April 29, 1954
Creator: Brown, Clarence A., Jr. & Nason, Martin L.
Item Type: Refine your search to only Report
open access

Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power

Description: Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Item Type: Refine your search to only Report
open access

Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield

Description: Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.
Date: September 29, 1958
Creator: Strass, H. K. & Goodman, V. M.
Item Type: Refine your search to only Report
open access

Thermal Stability of Decaborane and of a Commercial Ethyl Decaborane (HEF-3) in the Range 202 Degrees to 252 Degrees C

Description: Report discussing an investigation of the thermal stabilities of a commercial grade of ethyl decaborane and decaborane at two temperatures. Equations developed from the results of the experiment are also provided. Ethyl decaborane was found to be more stable to pyrolysis than pentaborane but less stable than decaborane.
Date: November 29, 1956
Creator: McDonald, G. E.
Item Type: Refine your search to only Report
open access

Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method

Description: "The rotating multicylinder method for in-flight determination of liquid-water content, droplet size, and droplet-size distribution in icing clouds is described. The theory of operation, the apparatus required, the technique of obtaining data in flight, and detailed methods of calculating the results, including necessary charts and tables, are presented" (p. 1).
Date: June 29, 1953
Creator: Lewis, William; Perkins, Porter J. & Brun, Rinaldo J.
Item Type: Refine your search to only Report
open access

Investigation of an on-off inlet shock-position control on a 16-inch ram-jet engine

Description: Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in the supersonic wind tunnel. The control operated at all conditions under which the engine could be manually operated. Prediction of the control-system dynamic behavior can be applied by treating the system as having pure dead time.
Date: November 29, 1954
Creator: Wilcox, Fred A.; Perchonok, Eugene & Hearth, Donald P.
Item Type: Refine your search to only Report
open access

Rocket-Model Investigation of the Longitudinal Stability, Drag, and Duct Performance of a 60 Degree Delta-Wing Canard Aircraft With Twin Side Inlets at Mach Numbers From 0.80 to 1.70

Description: Report discussing a flight test on a rocket-boosted canard aircraft with 60 degree delta lifting surfaces, twin normal-shock-type side inlets, and twin vertical tails. The drag, longitudinal stability, and duct performance data were obtained for a range of Mach and Reynolds numbers.
Date: March 29, 1954
Creator: Bond, Aleck C. & Swanson, Andrew G.
Item Type: Refine your search to only Report
open access

High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels

Description: Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individ… more
Date: May 29, 1957
Creator: Smith, Ivan D. & Saari, Martin J.
Item Type: Refine your search to only Report
open access

Calculation of External-Store Loads and Correlation With Experiment

Description: Memorandum presenting a theory for evaluating the mutual interference between a wing and tip tank as extended to apply to store-pylon configurations. By using the theory and the flow-field formulas of a previous report, theoretical store-pylon side-force estimates have been made for a number of store-pylon configurations. Results regarding the theory for store-pylon side force, scope of test configurations, contribution of store and pylon to combined load, effect of store spanwise location on t… more
Date: July 29, 1957
Creator: Bobbitt, Percy J.; Carlson, Harry W. & Pearson, Albin O.
Item Type: Refine your search to only Report
open access

Component and over-all performance evaluation of a J47-GE-25 turbojet engine over a range of engine-inlet Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds number indices. Secondary effects of exhaust-nozzle flow coefficient, air-flow leakage, and inlet temperature should be considered before analyzing the effect of variations in engine-inlet Reynolds number index. Several minor design modifications proposed by the manufacturer did not produce any measurable improvement in engine perform… more
Date: September 29, 1953
Creator: Walker, Curtis L.; Braithwaite, Willis M. & Fenn, David B.
Item Type: Refine your search to only Report
open access

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59

Description: Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.
Date: June 29, 1950
Creator: Spearman, M. Leroy & Hilton, John H., Jr.
Item Type: Refine your search to only Report
open access

Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925

Description: Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.
Date: June 29, 1950
Creator: Carmel, Melvin M.; Morgan, Francis G., Jr. & Coppolino, Domenic A.
Item Type: Refine your search to only Report
open access

Preliminary study of circulation in an apparatus suitable for determining corrosive effects of hot flowing liquids

Description: "A simple apparatus particularly applicable to the determination of the corrosive effects of flowing liquid metals on structural materials is described. In this apparatus, flow of the liquid medium at known velocities may be induced in toroidal shaped channels fabricated from the test structural material only, with no pump, valves, or flow meter required. A circulating velocity of 25 ft/sec has been obtained in preliminary tests and no basic limitation on increasing the speed was encountered" (… more
Date: June 29, 1951
Creator: Desmon, Leland G. & Mosher, Don R.
Item Type: Refine your search to only Report
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick rounded nose section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick rounded nose sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: August 29, 1951
Creator: Heitmeyer, John C. & Hightower, Ronald C.
Item Type: Refine your search to only Report
open access

The Rolling Effectiveness of Wing-Tip Ailerons as Determined by Rocket-Powered Test Vehicles and Linear Supersonic Theory

Description: Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.
Date: August 29, 1950
Creator: Sandahl, Carl A.; Strass, H. Kurt & Piland, Robert O.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered

Description: Report presenting the longitudinal and lateral characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at lift coefficient 0.25 and Mach number 1.5. The investigation occurred over a range of sideslip angles. The results indicated that the longitudinal characteristics were essentially unaffected by Reynolds number or the sideslip angles investigated.
Date: September 29, 1950
Creator: Lessing, Henry C.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane With Wings and Horizontal Tails of Aspect Ratios 4.2 and 2

Description: Report discussing an investigation of two transonic research airplane models at a range of Mach numbers and Reynolds numbers. The main difference between the models was the aspect ratio of the horizontal tail. Results regarding the stability, control, incremental horizontal-tail characteristics, downwash, horizontal-tail load, stability factors, and a tailless configuration are provided.
Date: September 29, 1950
Creator: Luoma, Arvo A. & Wright, John B.
Item Type: Refine your search to only Report
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