Serial/Series Title
Country
States
368 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
368
next
Application of statistical theory to beam-rider guidance in the presence of noise 2: modified Wiener filter theory
Report presenting a study of the application of Newton's modification of the Wiener filter theory to optimize a beam-rider guidance system operating in the presence of glint noise.
Date:
June 1958
Creator:
Stewart, Elwood C.
System:
The UNT Digital Library
Boundary-Induced Downwash Due to Lift in a Two-Dimensional Slotted Wind Tunnel
Note presenting a solution obtained for the complete tunnel-interference flow for a lifting vortex in a two-dimensional slotted tunnel. Curves are presented for the longitudinal distribution of tunnel-induced downwash angle for various values of boundary openness parameter and various heights of the vortex above the tunnel center line.
Date:
June 1958
Creator:
Katzoff, S. & Barger, Raymond L.
System:
The UNT Digital Library
Effect of the proximity of the wing first-bending frequency and the short-period frequency on the airplane dynamic-response factor
Report presenting a study of the effect of the frequency of the lowest wing structural mode on the airplane center-of-gravity dynamic-response factor was made my employing simplified transfer functions.
Date:
June 1958
Creator:
Huss, Carl R. & Donegan, James J.
System:
The UNT Digital Library
Experimental investigation of an impulse-type supersonic compressor rotor having a turning of 73 degrees at the mean radius
Report presenting testing of a 16-inch-diameter supersonic impulse rotor with guide vanes in Freon-12. Results regarding the overall performance and blade-element performance are provided.
Date:
June 1958
Creator:
Sterrett, James R.
System:
The UNT Digital Library
An experimental study of the turbulent boundary layer on a shock-tube wall
From Summary: "Interferometric measurements were made of the density profiles of an unsteady turbulent boundary layer on the flat wall of a shock tube. The investigation included both subsonic and supersonic flow (Mach numbers of 0.50 and 1.77) with no pressure gradient and with heat transfer to a cold wall. Velocity profiles and average skin-friction coefficients were calculated. Effects on the velocity profile of surface roughness and flow lengths are examined."
Date:
June 1958
Creator:
Gooderum, Paul B.
System:
The UNT Digital Library
Exploratory Wind-Tunnel Investigation to Determine the Lift Effects of Blowing over Flaps from Nacelles Mounted Above the Wing
"An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet momentum- coefficient range was from 0 to 3.0 and the model angle of attack was 0 degrees" (p. 1).
Date:
June 1958
Creator:
Riebe, John M. & Davenport, Edwin E.
System:
The UNT Digital Library
Exploratory wind-tunnel investigation to determine the lift effects of blowing over flaps from nacelles mounted above the wing
Report presenting an exploratory wind-tunnel investigation to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model with a delta wing of aspect ratio 3. The results indicate that the values of jet-circulation lift coefficient larger than the jet reaction were produced with blowing over flaps fro nacelles mounted above the wing. Results regarding lift coefficients, pitching-moment coefficients, and drag coefficients are provided.
Date:
June 1958
Creator:
Riebe, John M. & Davenport, Edwin E.
System:
The UNT Digital Library
Flight Measurements of the Vibratory Bending and Torsional Stresses on a Modified Supersonic Propeller for Forward Mach Numbers up to 0.95
Note presenting vibratory stress measurements obtained in flight on a modified supersonic propeller for forward mach numbers up to 0.95. The magnitude of the vibratory bending stress was low in relation to the strength of the material throughout the flight range of the airplane. Results of a propeller feathering operation at a Mach number of 0.95 indicated no excessive stresses.
Date:
June 1958
Creator:
O'Bryan, Thomas C.
System:
The UNT Digital Library
Flutter analysis of rectangular wings of very low aspect ratio
Report presenting a flutter analysis for rectangular wings of very low aspect ratio with a constant thickness, which used slender-body aerodynamic theory and thin-plate theory. The results show that the variation of flutter speed and mode shape with aspect ratio. Approximation of the chordwise deflection shape by use of parabolic or cubic curves yields flutter speeds in fair agreement with those of the "exact" theory for a ratio of chord to semispan less than 3 with the cubic approximation giving almost exact results.
Date:
June 1958
Creator:
Fralich, Robert W. & Hedgepeth, John M.
System:
The UNT Digital Library
Further Investigation of Fatigue-Crack Propagation in Aluminum-Alloy Box Beams
Report presenting testing of twenty-one box beams constructed according to nine designs that were subjected to fatigue tests at one load level to study fatigue-crack propagation and accompanying stress redistribution. Six designs had stiffeners riveted to the skin, two had integrally stiffened covers, and one had stiffeners bonded to the skin. Results regarding crack initiation, crack propagation, and stresses are provided.
Date:
June 1958
Creator:
Hardrath, Herbert F. & Leybold, Herbert A.
System:
The UNT Digital Library
A fuselage addition to increase drag-rise Mach number of subsonic airplanes at lifting conditions
Report presenting an investigation of the addition of fuselage volume on top of the forward portion of a fuselage for the purpose of increasing drag-rise Mach number of subsonic airplanes at lifting conditions. The addition increased the drag-rise Mach number by approximately 0.03 for a configuration with a wing of moderate thickness and 35 degrees of sweepback at a lift coefficient of 0.3. Results regarding drag characteristics and lift and pitching-moment characteristics are provided.
Date:
June 1958
Creator:
Whitcomb, Richard T.
System:
The UNT Digital Library
Heat Transfer in Isotropic Turbulence During the Final Period of Decay
Note presenting a consideration of the problem of heat transfer in isotropic turbulence with a constant mean temperature gradient during the final period of decay. The temperature field is ultimately found to become independent of the initial conditions on the temperature and have characteristics determined only by the mean temperature gradient, the physical properties of the fluid, and the characteristics of the turbulence.
Date:
June 1958
Creator:
Dunn, D. W. & Reid, W. H.
System:
The UNT Digital Library
High-Speed Hydrodynamic Characteristics of a Flat Plate and 20 Degrees Dead-Rise Surface in Unsymmetrical Planing Conditions
Note presenting the results of an investigation made to obtain the wetted areas, three components of planing forces, and the three components of moments acting on a 0 degree and a 20 degree dead-rise surface in high-speed, unsymmetrical planing conditions. The collected test data are presented in summary plots which are readily applicable for use in determining the lift, drag, side force, pitching moment, rolling moment, and yawing moment.
Date:
June 1958
Creator:
Savitsky, Daniel; Prowse, R. E. & Lueders, D. H.
System:
The UNT Digital Library
Internal characteristics and performance of several jet deflectors at primary-nozzle pressure ratios up to 3.0
Report presenting testing of several model jet deflectors to determine the effects of design variables on their performance and operating characteristics. The deflectors were designed to be adaptable to convergent-nozzle, plug-nozzle, and ejector turbojet exhaust systems. Results regarding the swiveled-nozzle jet deflectors, auxiliary-nozzle jet deflectors, mechanical jet deflectors, and miscellaneous jet deflectors are provided.
Date:
June 1958
Creator:
McArdle, Jack G.
System:
The UNT Digital Library
Normal component of induced velocity for entire field of a uniformly loaded lifting rotor with highly swept wake as determined by electromagnetic analog
Report presenting values of the nondimensional normal component of induced velocity throughout the flow field of a uniformly loaded lifting rotor operating in the upper half of the helicopter speed range in the form of graphs and tables. The results obtained should be useful for estimating the induced velocity distribution about lifting rotors in general and for synthesizing the distributions over the rotor disk for the case of any specified non-uniform loading.
Date:
June 1958
Creator:
Castles, Walter, Jr.; Durham, Howard L., Jr. & Kevorkian, Jirair
System:
The UNT Digital Library
A numerical method for evaluating wave drag
"A numerical method for evaluating the Von Karman wave-drag equation has been developed and applied to the calculation of wave drag for several bodies of revolution. Results indicated good agreement with the exact solution. Sufficient accuracy of wave drag was obtained by using a simple numerical method to determine the second derivatives of the area distributions" (p. 1).
Date:
June 1958
Creator:
Cahn, Maurice S. & Olstad, Walter B.
System:
The UNT Digital Library
On Pairs of Solutions of a Class of Internal Viscous Flow Problems With Body Forces
Note presenting a few examples of two distinct states of flow and heat transfer which were obtained for a given set of conditions if the frictional heating was taken into account. This report discusses these pairs of solutions in greater detail and shows how the solutions are affected by systematic variations of the basic physical parameters.
Date:
June 1958
Creator:
Ostrach, Simon & Albers, Lynn U.
System:
The UNT Digital Library
On Solutions for the Transient Response of Beams
Note presenting Williams type modal solutions of the elementary and Timoshenko beam equations for the transient response of several uniform beams to a general applied load. Example computations are shown for a free-free beam subject to various concentrated loads at its center. Results regarding modal solutions, the need for Timoshenko's theory, and numerical solutions are provided.
Date:
June 1958
Creator:
Leonard, Robert W.
System:
The UNT Digital Library
Prandtl Number Effects on Unsteady Forced-Convection Heat Transfer
"An analysis is made for laminar forced-convection heat transfer on a flat plate with unsteady surface temperature. The deviation of the instantaneous heat-transfer rate from the quasi-steady value is computed. Results are obtained for Prandtl numbers in the range 0.01 to 10" (p. 1).
Date:
June 1958
Creator:
Sparrow, E. M. & Gregg, J. L.
System:
The UNT Digital Library
Reflection and Transmission of Sound by a Slotted Wall Separating Two Moving Fluid Streams
"The reflection and transmission coefficients have been determined for a plane sound wave incident on a slotted wall separating two moving fluid streams. This acoustics problem is related to the aerodynamic problem of determining the tunnel-wall interference on an oscillating airfoil in a slotted-throat wind tunnel in that the same boundary condition is involved with one of the two streams at the boundary having zero velocity. In the analysis the wall with discrete slots is replaced by an equivalent homogeneous boundary" (p. 1).
Date:
June 1958
Creator:
Barger, Raymond L.
System:
The UNT Digital Library
Results of an experimental investigation of small viscous dampers
Report presenting the results of an experimental investigation of several small viscous dampers. The characteristics of the dampers are presented in the form of the magnitudes of the damping forces and spring forces as a function of the maximum velocity of the piston. The results indicated that the temperature has a large effect on the force produced by the dampers and demonstrated the necessity for consideration of the heat generated and dissipated as a result of work done by the dampers.
Date:
June 1958
Creator:
Silveira, Milton A.; Maglieri, Domenic J. & Brooks, George W.
System:
The UNT Digital Library
Some Effects of Vanes and of Turbulence in Two-Dimensional Wide-Angle Subsonic Diffusers
Note presenting tests on two aspects of the behavior of wide-angle, plane-walled, two-dimensional diffusers with essentially incompressible flow. First, a thorough study of the flow mechanism has been made during dye injection in a water table. Second, data are presented which demonstrate means for producing efficient diffusers for total included angles up to at least 45 degrees by use of simple, short, flat vanes.
Date:
June 1958
Creator:
Moore, Carl A., Jr. & Kline, Stephen J.
System:
The UNT Digital Library
Special bodies added on a wing to reduce shock induced boundary-layer separation at high subsonic speeds
Report presenting an investigation of the effects of special bodies added on the upper surface of a wing to reduce shock-induced boundary-layer separation for lifting conditions at high subsonic speeds. The basic test configuration had a relatively thick 35 degree sweptback wing of aspect ratio 7.05 mounted on a contoured fuselage. Results regarding the basic effects, variations of additions, effects of fuselage shape, and wing sweep are provided.
Date:
June 1958
Creator:
Whitcomb, Richard T.
System:
The UNT Digital Library
Stall Propagation in a Cascade of Airfoils
Note presenting an experimental investigation of stall propagation in a stationary circular cascade in which high-speed schileren and interferometer photography is used is described. Results regarding a circular cascade were provided, which indicated that the number of cells increased as the flow through the rotor was throttled.
Date:
June 1958
Creator:
Kriebel, Anthony R.; Seidel, Barry S. & Schwind, Richard G.
System:
The UNT Digital Library