UNT Libraries Government Documents Department - 131 Matching Results

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Variation of Local Liquid-Water Concentration About and Ellipsoid of Fineness Ratio 5 Moving in a Droplet Field

Description: From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."
Date: July 1954
Creator: Dorsch, Robert G. & Brun, Rinaldo J.
Item Type: Refine your search to only Report
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Impingement of Water Droplets on NACA 65A004 Airfoil at 8 Degree Angle of Attack

Description: The trajectories of droplets in the air flowing past an NACA 65AO04 airfoil at an angle of attack of 8 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the … more
Date: July 1954
Creator: Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
Item Type: Refine your search to only Report
open access

Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models

Description: Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.
Date: July 15, 1954
Creator: Church, James D.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket

Description: Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the armi… more
Date: July 6, 1954
Creator: Bird, John D. & Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
open access

Experimental stress analysis of stiffened cylinders with cutouts: Shear load

Description: A cylindrical semimonocoque shell of circular cross section was mounted as a cantilever and loaded by a direct shear at the tip. The cylinder was tested with no cutout, with a rectangular cutout on the tension side, and with the cutout centered on the neutral axis on one side of the cylinder. The cutout was successively enlarged through six sizes varying from 30 degrees to 130 degrees in circumference and from 1 and 2 bays in length. Strain measurements were made with resistance-type wire strai… more
Date: July 1954
Creator: Schlechte, Floyd R. & Rosecrans, Richard
Item Type: Refine your search to only Report
open access

Oscillating pressures near a static pusher propeller at tip Mach numbers up to 1.20 with special reference to the effects of the presence of the wing

Description: Report presenting measurements of free-space oscillating pressures near a static propeller in the region where a wing might be located are presented for a range of tip Mach numbers and the results are compared with available theory. The radial pressure distributions vary as a function of axial distance and order of the harmonic. Results regarding free-space pressures and wing pressures are provided.
Date: July 1954
Creator: Hubbard, Harvey H. & Lassiter, Leslie W.
Item Type: Refine your search to only Report
open access

Shock-turbulence interaction and the generation of noise

Description: Report presenting the interaction of a convected field of turbulence with a shock wave, which has been analyzed to yield the modified turbulence, entropy spottiness, and noise generated downstream of the shock. The results in this report are applicable quantitatively to flow in ducts or channels containing normal shocks.
Date: July 1954
Creator: Ribner, H. S.
Item Type: Refine your search to only Report
open access

Experimental investigation of temperature recovery factors on a 10 degree cone at angle of attack at a Mach number of 3.12

Description: Report presenting temperature recovery factors on a thin-walled, metal, 10 degree included angle cone at a Mach number of 3.12 over a range of angles of attack and Reynolds numbers per foot. An increase in angle of attack was found to increase the equilibrium surface temperatures in the laminar and turbulent boundary-layer regions.
Date: July 1954
Creator: Jack, John R. & Moskowitz, Barry
Item Type: Refine your search to only Report
open access

Theoretical investigation of longitudinal response characteristics of a swept-wing fighter airplane having a normal acceleration control system and a comparison with other types of systems

Description: Report presenting an investigation of the longitudinal response characteristics of a swept-wing fighter airplane using normal-acceleration control system. Results regarding the frequency and transient responses, acceleration systems, pitching-velocity command system, and the pitch-attitude system are provided.
Date: July 1954
Creator: Stokes, Fred H. & Mathews, Charles W.
Item Type: Refine your search to only Report
open access

Heat, Mass, and Momentum Transfer for Flow Over a Flat Plate With Blowing or Suction

Description: Note presenting testing of a woven fiberglass-nichrome wire heater cloth attached directly to the back side of the porous test wall in order to insure exact and known temperature profiles for the injected air. Suction was found to decrease the boundary-layer thickness, increase the magnitude of the friction and heat transfer coefficients, and delay the transition from laminar to turbulent flow.
Date: July 1954
Creator: Mickley, H. S.; Ross, R. C.; Squyers, A. L. & Stewart, W. E.
Item Type: Refine your search to only Report
open access

Additional Static and Fatigue Tests of High-Strength Aluminum-Alloy Bolted Joints

Description: From Introduction: "Early in 1951 the National Advisory Committee for Aeronautics published, as Technical Note 2276 (ref. 1), a report by the Aluminum Research Laboratories of the Aluminum Company of America on the results of static and fatigue tests of high-strength aluminum alloy monobloc specimens and bolted joints. In view of special interest shown by several aircraft companies, certain expansions of the test program were undertaken by the Aluminum Research Laboratories and are reported her… more
Date: July 1954
Creator: Hartmann, E. C.; Holt, Marshall & Eaton, I. D.
Item Type: Refine your search to only Report
open access

Considerations on a large hydraulic jet catapult

Description: Report presenting a survey of various types of catapults in connection with the problem of accelerating a large car along a track to a speed of 150 miles per hour. A hydraulic jet catapult was found to be the best suited and various design problems of that type are treated. The expected propulsive efficiency of the catapult is given and the effect of a side wind on the jet trajectory is calculated.
Date: July 1954
Creator: Joyner, Upshur T. & Horne, Walter B.
Item Type: Refine your search to only Report
open access

An Investigation of the Creep Lifetime of 75S-T6 Aluminum-Alloy Columns

Description: Report presenting the results of short-time elevated-temperature creep tests of 75S-T6 aluminum-alloy columns and evaluated with the objective of obtaining procedures for predicting column lifetime. Distortions resulting from creep in objects such as supersonic aircraft and missiles can cause the aerodynamic characteristics to change.
Date: July 1954
Creator: Mathauser, Eldon E. & Brooks, William A., Jr.
Item Type: Refine your search to only Report
open access

Lift and Pitching Moment at Supersonic Speeds Due to Constant Vertical Acceleration for Thin Sweptback Tapered Wings With Streamwise Tips: Supersonic Leading and Trailing Edges

Description: Note presenting the nondimensional lift derivative and the corresponding pitching-moment derivative resulting from constant vertical acceleration as evaluated for a family of thin sweptback tapered wings with streamwise tips traveling at supersonic speeds. The analysis is applicable at those speeds for which the wing leading and trailing edges are both supersonic, provided that the Mach lines from the wing apex intersect the trailing edge and that the Mach line from the leading edge of one tip … more
Date: July 1954
Creator: Cole, Isabella J. & Margolis, Kenneth
Item Type: Refine your search to only Report
open access

Theoretical Investigation at Subsonic Speeds of the Flow Ahead of a Slender Inclined Parabolic-Arc Body of Revolution and Correlation With Experimental Data Obtained at Low Speeds

Description: Report presenting charts which permit the rapid estimation of deviations from free-stream values of static pressure, angle of attack, and angle of sideslip so that ideal positions for orifices and vanes for measuring these qualities can be selected. The effects of thickness and angle of attack are considered in greater detail.
Date: July 1954
Creator: Letko, William & Danforth, Edward C. B., III
Item Type: Refine your search to only Report
open access

An experimental study of the lift and pressure distribution on a double-wedge profile at Mach numbers near shock attachment

Description: Report presenting an account of wind-tunnel measurements at low supersonic speeds of the pressure distribution on a doubly symmetrical double-wedge profile of approximately 8-percent thickness. The results cover a range of Mach numbers, angles of attack, and a specified Reynolds number. Results regarding the characteristics at zero angle of attack, characteristics at angle of attack, comparison with subsonic results, and some general remarks are provided.
Date: July 1954
Creator: Vincenti, Walter G.; Dugan, Duane W. & Phelps, E. Ray
Item Type: Refine your search to only Report
open access

Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature

Description: From Summary: "Exact solution of the laminar-boundary-layer equations for wedge-type flow with constant property values are presented for transpiration-cooled surfaces with variable wall temperatures. The difference between wall and stream temperature is assumed proportional to a power of the distance from the leading edge. Solutions are given for a Prandtl number of 0.7 and ranges of pressure-gradient, cooling-air-flow, and wall-temperature-gradient parameters. Boundary-layer profiles, dimensi… more
Date: July 15, 1954
Creator: Donoughe, Patrick L. & Livingood, John N. B.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64₂-015, and 64₃-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Description: An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as vari… more
Date: July 23, 1954
Creator: Critzos, Chris C.
Item Type: Refine your search to only Report
open access

Effect on Drag of Longitudinal Positioning of Half-Submerged and Pylon-Mounted Douglas Aircraft Stores on a Fuselage with and without Cavities between Mach Numbers 0.9 and 1.8

Description: From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. T… more
Date: July 15, 1954
Creator: Hoffman, Sherwood & Wolff, Austin L.
Item Type: Refine your search to only Report
open access

Drop Hammer Tests With Three Oleo Strut Models and Three Different Shock Strut Oils at Low Temperatures

Description: "Drop hammer tests with different shock strut models and shock strut oils were performed at temperatures ranging to -40 C. The various shock strut models do not differ essentially regarding their springing and damping properties at low temperatures; however, the influence of the different shock strut oils on the springing properties at low temperatures varies greatly" (p. 1).
Date: July 1954
Creator: Kranz
Item Type: Refine your search to only Report
open access

Free-Flight Tests of 0.11-Scale North American F-100 Airplane Wings to Investigate the Possibility of Flutter in Transonic Speed Range at Varying Angles of Attack

Description: "Free-flight tests in the transonic speed range utilizing rocketpropelled models have been made on three pairs of 0.11-scale North American F-100 airplane wings having an aspect ratio of 3.47, a taper ratio of 0.308, 45 degree sweepback at the quarter-chord line, and thickness ratios of 31 and 5 percent to investigate the possibility of flutter. Data from tests of two other rocket-propelled models which accidentally fluttered during a drag investigation of the North American F-100 airplane are … more
Date: July 29, 1954
Creator: O'Kelly, Burke R.
Item Type: Refine your search to only Report
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