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An Analysis of Ramjet Engines Using Supersonic Combustion
From Introduction: "The concept of supersonic combustion is by no means new, although little work appears to have been published on the subject. For example, an analysis of supersonic combustion to provide lift under a wing is given in reference 1. Reference 2 discusses applications to hypersonic ramjets being studied at the University of Michigan."
Date:
September 1958
Creator:
Weber, Richard J. & MacKay, John S.
System:
The UNT Digital Library
Analysis of the Creep Behavior of a Square Plate Loaded in Edge Compression
From Introduction: "In reference 1 results of creep tests and empirical method for predicting collapse times are presented for plates loaded in compression on two opposite edges and with the remaining edges unloaded and supported in V-groove fixtures. Other approximate methods for handling plates having types of edge support are suggested in reference 2; however, experimental verification for these methods is quite limited. In reference 3 an analysis based on small-deflection theory is made of the creep deflection of a simply supported plate composed of a linear viscoelastic material - that is, a material in which the stress and strain and their appropriate time derivatives are related in a linear fashion."
Date:
September 1958
Creator:
McComb, Harvey G., Jr.
System:
The UNT Digital Library
Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages
From Introduction: "In reference 1, wall temperature distributions for turbulent flow in rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients, together with assumed similarity of the wall heat-transfer and wall shear-stress variations; no attempt was made to calculate either the heat-transfer coefficients or the velocity and temperature distributions in the fluid field. Some calculations of velocity and shear-stress distributions in corners are reported in reference 2."
Date:
September 1958
Creator:
Deissler, Robert G. & Taylor, Maynard F.
System:
The UNT Digital Library
Analytical and Experimental Investigation of Temperature Recovery Factors for Fully Developed Flow of Air in a Tube
Note presenting an analysis made for predicting temperature recovery factors for fully developed flow in a tube. Most of the attention was confined to turbulent flow. Both analytical and experimental results are provided for the air flow.
Date:
September 1958
Creator:
Deissler, R. G.; Weiland, W. F. & Lowdermilk, W. H.
System:
The UNT Digital Library
An analytical study of turbulent and molecular mixing in rocket combustion
From Introduction: "The many physical processes which occur simultaneously in rocket combustion make the entire process extremely complex (ref. 1). The combustion chamber length required for evaporation of liquid-propellant sprays has already been studied (refs. 2, 3, and 4)."
Date:
September 1958
Creator:
Bittker, David A.
System:
The UNT Digital Library
An Approach to the Problem of Estimating Severe and Repeated Gust Loads for Missile Operations
Note presenting an analysis of available airplane measurements of vertical gust velocity in order to arrive at a simple description of the frequency and intensity of gust velocities experienced by airplanes in operations. For the purpose of application to missile operations, the results obtained are modified to eliminate the effects of storm-avoidance procedures normally followed in airplane operations.
Date:
September 1958
Creator:
Press, Harry & Steiner, Roy
System:
The UNT Digital Library
Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll
Report presenting an extension of a method for calculating motions in angles of attack and sideslip resulting from a trim angle of attack and steady rolling velocity to the condition of pitching- and yawing-moment inputs. The resulting formulas are intended primarily for rolling-velocity conditions in which rolling divergence is not encountered.
Date:
September 1958
Creator:
Moul, Martin T. & Brennan, Teresa R.
System:
The UNT Digital Library
Approximate Method for Calculation of Laminar Boundary Layer With Heat Transfer on a Cone at Large Angle of Attack in Supersonic Flow
Note presenting the use of an integral technique to reduce the laminar boundary-layer equations on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The method enables the skin friction coefficients and Stanton number to be calculated in a much shorter time than was needed to obtain exact numerical solutions from the boundary-layer equations.
Date:
September 1958
Creator:
Brunk, William E.
System:
The UNT Digital Library
Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows
Report presenting an analysis for obtaining approximate solutions of the similarity equations for three-dimensional laminar-boundary-layer flows over a flat surface under main-flow streamlines that are translates and representable as infinite series expansions.
Date:
September 1958
Creator:
Hansen, Arthur G. & Herzig, Howard Z.
System:
The UNT Digital Library
Comparison of shock-expansion theory with experiment for the lift, drag, and pitching-moment characteristics of two wing-body combinations at M=5.0
Report presenting lift, drag, and pitching-moment coefficients for two wing-body combinations as determined from tests at Mach number 5.0 and angles of attack up to 9 degrees. The test models consisted of small thin wings mounted on a body composed of a fineness-ratio-3 ogival nose and a fineness-ratio-2 cylindrical afterbody.
Date:
September 1958
Creator:
Savin, Raymond C.
System:
The UNT Digital Library
A Cooled-Gas Pyrometer for Use in High-Temperature Gas Streams
Report presenting a description of an immersion-type pyrometer that utilizes the controlled cooling of a continuously aspirated sample of the gas whose temperature is to be measured. Results regarding both the preliminary and final testing with this device are provided.
Date:
September 1958
Creator:
Krause, Lloyd N.; Johnson, Robert C. & Glawe, George E.
System:
The UNT Digital Library
Cumulative Fatigue Damage at Elevated Temperature
"A study of cumulative fatigue damage at elevated temperatures was conducted using heat-treated SAE 4130 alloy steel. The S-N curves at room temperature, 400 degrees Fahrenheit, and 800 degrees Fahrenheit were obtained from rotating-beam fatigue tests. Two-step, three-step, and five-step cumulative-damage fatigue tests were conducted on rotating-beam fatigue specimens at room temperature, 400 degrees Fahrenheit, and 800 degrees Fahrenheit. The results of the cumulative-damage tests are compared with those of a theoretical analysis" (p. 1).
Date:
September 1958
Creator:
Rey, William K.
System:
The UNT Digital Library
Effect of Advance Ratio on Flight Performance of a Modified Supersonic Propeller
Note presenting results of a flight investigation to determine the aerodynamic characteristics of a supersonic propeller modified by the incorporation of higher than optimum advance angles. The propeller was designed for a forward Mach number of 0.95, an advance ratio of 3.2, and a power coefficient of 0.42. The efficiency of the propeller is approximately 79 percent at a Mach number of 0.95.
Date:
September 1958
Creator:
Hammack, Jerome B. & O'Bryan, Thomas C.
System:
The UNT Digital Library
Effect of Precipitate Particles on Creep of Aluminum-Copper Alloys During Age Hardening
Note presenting an investigation of spherical or platelike precipitates prepared in aluminum alloys with 1 to 4 weight percent copper. The effects of controlled sizes and distributions of particles were determined by creep, tensile, and hardness measurements by quantitative metallographic evaluation of the particle characteristics, and by X-ray and electron-microscope examinations.
Date:
September 1958
Creator:
Underwood, E. E.; Marsh, L. L. & Manning, G. K.
System:
The UNT Digital Library
Effect of pressure and duct geometry on bluff-body flame stabilization
Report presenting blowoff velocities and recirculation-zone lengths of propane-air flames stabilized by cylindrical flameholders measured as a function of pressure, cylinder diameter, fuel-air ratio, and tunnel geometry for a range of Reynolds numbers. Results regarding blowoff velocities, recirculation-zone lengths, critical time, and heat losses from recirculation zone are provided.
Date:
September 1958
Creator:
Potter, Andrew E., Jr. & Wong, Edgar L.
System:
The UNT Digital Library
Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98
Note presenting an experimental investigation to determine the aerodynamic heat transfer and pressure distribution on flat-plate models with various arrangements of external stiffeners mounted normal to the direction of air flow. At all three Mach numbers tested, the addition of stiffeners to a flat plate caused large pressure variations and large pressure losses in the flow along the plate. Results regarding pressure distributions, equilibrium temperatures, and heat transfer are provided.
Date:
September 1958
Creator:
Carter, Howard S.
System:
The UNT Digital Library
Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections
Report presenting an investigation to determine the low tip Mach number blade maximum mean lift coefficients and the high tip Mach number effects of compressibility for rotor blades with NACA 0015 tip airfoil sections. The characteristics of this rotor was similar to those from other investigations, which is that at low Mach numbers, there is a stable pitching moment past rotor-blade drag divergence. Results regarding hovering performance, synthesized rotor-blade section characteristics, rotor-blade pitching moments, rotor-blade profile-drag torque, comparison of profile-drag torque ratios, and a comparison of experimental and two-dimensional drag-divergence characteristics are provided.
Date:
September 1958
Creator:
Shivers, James P. & Carpenter, Paul J.
System:
The UNT Digital Library
Effects of frequency and amplitude on the yawing derivatives of triangular, swept, and unswept wings and of a triangular-wing-fuselage combination with and without a triangular tail performing sinusoidal yawing oscillations
Report presenting an investigation to determine the effects of frequency and amplitude on the yawing derivatives of triangular, swept, and unswept wings. Results regarding the damping in yaw, rolling moment due to yawing, acceleration derivatives, and comparison of yawing and acceleration derivatives with combined derivatives for wings alone are provided for configurations of the wing alone and wing-body combinations.
Date:
September 1958
Creator:
Letko, William & Fletcher, Herman S.
System:
The UNT Digital Library
Effects of ground proximity on the thrust of a simple downward-directed jet beneath a flat surface
Report presenting an investigation to determine the effects of some of the basic parameters on the thrust of a simple downward-directed jet beneath a flat plate in a static-thrust facility. Some of the variables investigated included the size and shape of the flat plate, aspect ratio of the plate, distance of the flat plate and nozzle exit above the ground, and surface conditions of the ground.
Date:
September 1958
Creator:
Spreemann, Kenneth P. & Sherman, Irving R.
System:
The UNT Digital Library
Effects of nose angle and Mach number on transition on cones at supersonic speeds
"An investigation has been made to determine the transition characteristics of a group of smooth, sharp-nosed cones varying from 10 degrees to sixty degrees in included apex angle over a Mach number range from 1.61 to 2.20 and a range of Reynolds number per foot from about 1.5 x 10 to the 6th power to 8 x 10 to the 6th power. Increasing the cone angle is shown to decrease slightly the transition Reynolds number, whereas the effects of changes of Mach number and unit Reynolds number are negligible. When transition occurred within 15 to 20 percent of the model length from the base there was a dropoff in transition Reynolds number" (p. 1).
Date:
September 1958
Creator:
Czarnecki, K. R. & Jackson, Mary W.
System:
The UNT Digital Library
Effects of Propeller Position and Overlap on the Slipstream Deflection Characteristics of a Wing-Propeller Configuration Equipped With a Sliding and Fowler Flap
Report of an investigation in a static-test facility to determine some of the effects of propeller position and overlap on the slipstream deflection characteristics of a configuration equipped with a sliding and Fowler flap. An investigation of a leading-edge slat, nacelle size, flap segmentation, and number of propellers was also conducted. Results regarding the effect of number of propellers, effect of vertical position of propeller, effect of extending nacelles through flaps, effect of chordwise position of the propellers, effect of propeller overlap, effect of position and deflection of a leading-edge slat, propeller static-thrust efficiency in ground effect, and effect of nacelle size are provided.
Date:
September 1958
Creator:
Hayes, William C., Jr.; Kuhn, Richard E. & Sherman, Irving R.
System:
The UNT Digital Library
Experimental Evaluation of Low-Band-Pass Landing-Gear Shock Absorber for Pulse Loadings
Note presenting an experimental investigation to determine the practicality of constructing a low-band-pass landing-gear shock absorber and to evaluate its effectiveness in reducing rapidly applied loads. Results regarding the pulse-rate-response comparison, control-mechanism functions, recycling characteristics, landings on single bumps, and possible applications of design are provided.
Date:
September 1958
Creator:
Schnitzer, Emanuel
System:
The UNT Digital Library
Experimental investigation of axial and normal force characteristics of skewed nozzles
Report presenting an investigation of normal forces produced by several skewed nozzles and a series of ejectors with skewed shrouds discharging into quiescent air as conducted with cold air at jet total-pressure ratios up to 6.5. Nozzles were terminated at angles of 30 degrees, 45 degrees, 60 degrees, and 75 degrees relative to the normal plane. Results regarding basic data, effect of skew angle and indentation, and effect of a skewed shroud are provided.
Date:
September 1958
Creator:
Carter, David J., Jr. & Vick, Allen R.
System:
The UNT Digital Library
An experimental investigation of the effect of various parameters including tip Mach number on the flutter of some model helicopter rotor blades
Report presenting studies of some of the effects of parameters such as Mach number, blade angle, and structural damping on the flutter of model helicopter rotor blades in the hovering condition. Forward movement of the blade chordwise center-of-gravity location tended to raise the flutter speeds at low pitch angles, but had no effect at high pitch angles. The significant flutter data for the tests along with detailed descriptions of the models are included to facilitate more detailed analyses.
Date:
September 1958
Creator:
Brooks, George W. & Baker, John E.
System:
The UNT Digital Library