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Reaction of Fluorine With Carbon as a Means of Fluorine Disposal

Description: Report discussing an investigation into the binding of amorphous carbon with flourine to render it inert and easy to vent into the atmosphere.The ease and safety of the procedure are described.
Date: July 18, 1957
Creator: Schmidt, Harold W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06

Description: Memorandum presenting an investigation to determine the drag, longitudinal stability, and lateral stability characteristics of a model of a fighter-type airplane. Several modifications were made to the model in an attempt to eliminate pitch-up.
Date: January 18, 1957
Creator: Carmel, Melvin M. & Turner, Kenneth L.
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers base… more
Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor

Description: Memorandum presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Performance of the stator was determined with static-pressure measurements and detailed surveys of total pressure and flow angle made with the turbine operating at design speed near design work.
Date: July 18, 1957
Creator: Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
Partner: UNT Libraries Government Documents Department
open access

Origin and Prevention of Crash Fires in Turbojet Aircraft

Description: "The tendency for the jet engine rotor to continue to rotate after crash presents the probability that crash-spilled combustibles suspended in the air or puddled on the ground at the engine inlet may be sucked into the engine. Studies with jet engines operating on a test stand and full-scale crashes of turbojet-powered airplanes showed that combustibles drawn into the engine in this way ignite explosively within the engine. Experiment showed that the gas flow through the engine is too rapid to … more
Date: January 18, 1957
Creator: Pinkel, I. Irving; Weiss, Solomon; Preston, G. Merritt & Pesman, Gerard J.
Partner: UNT Libraries Government Documents Department
open access

Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88

Description: "Measurements of aerodynamic heat transfer have been made along the hemisphere and cylinder of a hemisphere-cylinder rocket-propelled model in free flight up to a Mach number of 3.88. The test Reynolds number based on free-stream condition and diameter of model covered a range from 2.69 x l0(exp 6) to 11.70 x 10(exp 6). Laminar, transitional, and turbulent heat-transfer coefficients were obtained" (p. 1).
Date: April 18, 1957
Creator: Garland, Benjamine J. & Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310 and 3,500 Degrees R on a Magnesium Fin With Several Leading-Edge Modifications

Description: Report presenting testing of four models of a thin magnesium fin, with the leading edge swept back 35 degrees, of a type used to stabilize the first stages of rocket-propelled multistage hypersonic models. The investigation was carried out to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective methods. The fins tested included a basic fin, a fin with a blunt lead… more
Date: April 18, 1957
Creator: Bland, William M., Jr. & Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
open access

Component performance investigation of J71 experimental turbine 8: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 70-percent-design stator area

Description: Results of a survey investigation of the J71-97 experimental three-stage turbine equipped with a first-stator area 70 percent pf design are presented and compared with the turbine with a first-stator area 97 percent of design.
Date: January 18, 1957
Creator: Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Description: Report presenting an experimental determination of the flow fields near swept- and unswept-wing-fuselage combinations at zero sideslip as determined experimentally at low speed for various spanwise and vertical locations and angles of attack as variations with chordwise distance. Results regarding the swept-wing-fuselage flow fields, unswept-wing-fuselage flow fields, and a comparison of wing-fuselage and fuselage-alone flow fields are provided.
Date: January 18, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Description: From Introduction: "This report presents net thrusts computed for hydrogen, diborance, and hydrazine with fuel-air ratios form stoichiometric values to 0.5. Net thrusts for fuel-rich afterburning are compared with those for stoichiometric combustion of the turbojet fuel and air augmented with a 220-second specific-impulse rocket."
Date: June 18, 1957
Creator: Morris, James F.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 2: design and experimental performance of turbine with low-velocity-turning stator and standard rotor

Description: Report presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Turbine performance was measured to determine the effect of low-velocity turning in the stator on the overall turbine performance. Results regarding the stator performance, overall turbine performance, and rotor exit surveys are provided.
Date: July 18, 1957
Creator: Rohlik, Harold E.; Wintucky, William T. & Scribbe, Herbert W.
Partner: UNT Libraries Government Documents Department
open access

Injection Principles for Liquid Oxygen and Heptane Using Nine-Element Injectors in an 1800-Pound-Thrust Rocket Engine

Description: Memorandum presenting a study of six nine-element injectors for the liquid-oxygen-heptane propellant system in an 1800-pound-thrust rocket engine. The characteristic velocities for comparable injector types were about the same as those obtained from the two-element study. The level of performance was generally higher for the nine-element injectors.
Date: July 18, 1957
Creator: Neu, Richard F.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8

Description: Memorandum presenting an analysis of one-spool ducted-fan engines in order to determine the primarily limitations on ducted-fan-engine design and to compare this type with the turboprop and turbojet engines for the same application. Designs were studied at flight Mach numbers of 0 and 0.6 at sea level and Mach numbers of 0.6 and 0.8 at the tropopause. Results regarding the discussion of charts, effect of design parameters on turbine stress, effect of design parameters, effect of design paramete… more
Date: July 18, 1957
Creator: Cavicchi, Richard H.
Partner: UNT Libraries Government Documents Department
open access

Heat-Transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2

Description: Report presenting testing on six blunt-nose models at angles of attack ranging from 0 to 5 degrees in order to evaluate the heat transfer and pressure on their surfaces. Information about transition, proper design, and locations of greatest and least heat transfer is provided.
Date: April 18, 1957
Creator: Carter, Howard S. & Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
open access

Reaction of Fluorine With Carbon as a Means of Fluorine Disposal

Description: Memorandum presenting an experimental investigation showing that amorphous carbon, such as wood charcoal, is readily applicable to fluorine disposal by a specified chemical reaction. Fluorine and fluorine-oxygen and fluorine-nitrogen mixtures containing as little as 6.5 percent fluorine reacted spontaneously with fresh dry charcoal.
Date: July 18, 1957
Creator: Schmidt, Harold W.
Partner: UNT Libraries Government Documents Department
open access

Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0

Description: Internal performance of normal-shock rectangular, circular, and scoop inlets and of external-compression inlets experimentally obtained with varying immersion in a turbulent boundary layer. Recoveries varied from about 95 percent of theoretical in the free stream to 80 percent with complete immersion, while the corresponding mass flows were usually above 95 percent of theoretical. Turning of the flow through 10 degrees caused losses in pressure recovery of 0.03 to 0.07. External compression did… more
Date: January 18, 1957
Creator: Huff, Ronald G. & Anderson, Arthur R.
Partner: UNT Libraries Government Documents Department
open access

Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0

Description: An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.
Date: January 18, 1957
Creator: Wasserbauer, Joseph F. & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)

Description: "A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).
Date: April 18, 1957
Creator: Buglia, James J.
Partner: UNT Libraries Government Documents Department
open access

Effect of burner design variables on performance of 16-inch diameter ram-jet combustor using gaseous-hydrogen fuel

Description: An evaluation of the effect of geometric design variables on the performance of a 16-inch-diameter ram-jet combustor total pressures from 7 to 44 inches of mercury absolute. Equivalent ratio was varied from 0.1 to 1.0 at a combustor inlet temperature of 1100 degrees R.
Date: January 18, 1957
Creator: Krull, H. George & Burley, Richard R.
Partner: UNT Libraries Government Documents Department
open access

A phenomenological relation between stress, strain rate, and temperature for metals at elevated temperatures

Description: Report presenting a phenomenological relation between stress, strain rate, and temperature to account for the behavior of polycrystalline metals above the equicohesive temperature. This is because the behavior of metals at elevated temperatures is constantly becoming a more important problem. The validity of the relation suggested in the equation appears to be accurate for 7075-T6 aluminum alloy.
Date: February 18, 1957
Creator: Stowell, Elbridge Z.
Partner: UNT Libraries Government Documents Department
open access

A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient

Description: "A method of calculating the temperature of thick walls has been developed in which the time series and the response to a unit triangle variation of surface temperature concepts are used, together with essentially standard formulas for transient temperature and heat flow into thick walls. The method can be used without knowledge of the mathematical tools of its development. The method is particularly suitable for determining the wall temperature in one-dimensional thermal problems in aeronautic… more
Date: June 18, 1957
Creator: Hill, P. R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a nonlinear control system

Description: A discontinuous variation of coefficients of the differential equation describing the linear control system before nonlinear elements are added is studied in detail. The nonlinear feedback is applied to a second-order system. Simulation techniques are used to study performance of the nonlinear control system and to compare it with the linear system for a wide variety of inputs. A detailed quantitative study of the influence of relay delays and of a transport delay is presented.
Date: October 18, 1957
Creator: Flügge-Lotz, I.; Taylor, C. F. & Lindberg, H. E.
Partner: UNT Libraries Government Documents Department
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