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985 Matching Results
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Wind-Tunnel Measurements of the Dynamic Cross Derivative (Rolling Moment Due to Yawing Velocity and to Acceleration in Sideslip) of the Douglas D-558-II Airplane and Its Components at Supersonic Speeds Including Description of the Technique
Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.
Date:
November 3, 1955
Creator:
Boatright, William B.
System:
The UNT Digital Library
Effect of Reduced Stator-Blade Trailing-Edge Thickness on Over-All Performance of a Transonic Turbine
"A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement was largely due to a reduced amount of low-velocity fluids entering the rotor and the interference effect of these fluids with the mainstream flow" (p. 1).
Date:
November 1, 1955
Creator:
Whitney, Warren J.; Stewart, Warner L. & Wong, Robert Y.
System:
The UNT Digital Library
Investigation of performance of 9-cylinder engine using large valve overlap and eclipse fuel-injection system
Report presenting single-cylinder tests were made with several different engines over a period of time, which have shown that a large overlap between the time of inlet valve opening and exhaust valve closing results in a considerable increase in the maximum power obtainable from a supercharged engine and reduces cylinder temperatures.
Date:
November 1941
Creator:
Young, Alfred W.
System:
The UNT Digital Library
Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel
Report presenting an investigation conducted in the full-scale tunnel to determine methods of improving the cooling of the B-24D engine installation. The B-24D is a four-engine high-wing monoplane having a span of 110 feet, a wing area of 1048 square feet, and a gross weight of 56,000 pounds.
Date:
November 1942
Creator:
Lehr, Robert R.; Kinghorn, George F. & Guryansky, Eugene R.
System:
The UNT Digital Library
Cascade investigation of buckets for a modern aircraft turbosupercharger
Report presenting a cascade investigation in two-dimensional flow in the 5-inch cascade tunnel and the 1-inch turbine-element testing apparatus to obtain a satisfactory bucket design for use in a modern aircraft turbosupercharger. Results regarding the root sections, pitch sections, and tip sections are provided.
Date:
November 1944
Creator:
Kantrowitz, Arthur & Erwin, John R.
System:
The UNT Digital Library
Model ditching investigation of the Boeing 707 jet transport
Report presenting an investigation of the ditching characteristics of the Boeing 707 jet transport in tank no. 2. Various conditions of damage, landing attitude, and speed were investigated. Data were obtained from visual observations, acceleration records, and motion pictures.
Date:
November 21, 1955
Creator:
Thompson, William C.
System:
The UNT Digital Library
Preliminary Investigation of Deep Inducers as Separate Supercharger Components
Report presenting a study of a family of three single-stage deep inducers designed to impart solid-body, or wheel, rotation in the entering air at constant rates along the axial depth of the inducers. The cast inducers tested were 4-inch axial depth with 24 blades, 4-inch depth with 12 blades, and 2-inch depth with 24 blades. Results regarding the cast inducers of the constant-angular-acceleration family, inducer section from the conventional impeller, and estimate of the inducer effect are provided.
Date:
November 1945
Creator:
Ritter, William K. & Johnsen, Irving A.
System:
The UNT Digital Library
A Study of Piston and Ring Friction
Report discusses an investigation into piston and ring friction as compared to total engine friction under natural operating conditions. Several test conditions were explored, including the effect of scuffing and excess cylinder-wall lubrication on friction. A device for measuring ring tensions and an apparatus for transforming pressure-crank angle indicator diagrams into pressure-volume indicator diagrams are also described.
Date:
November 1944
Creator:
Leary, W. A. & Jovellanos, J. U.
System:
The UNT Digital Library
On possible similarity solutions for three-dimensional incompressible laminar boundary layers 2: similarity with respect to stationary polar coordinates
From Summary: "Solutions of mainstream flow patterns for three-dimensional, laminar, incompressible thin-boundary-layer flows (over flat or slightly curved surfaces) having similarity with respect to stationary polar coordinates in the plane of the surface are derived. The solutions are summarized in a table."
Date:
November 1956
Creator:
Herzig, Howard Z. & Hansen, Arthur G.
System:
The UNT Digital Library
Stability Limits and Burning Velocities of Laminar Hydrogen-Air Flames at Reduced Pressure
Note presenting laminar burning velocity measured at pressures of 1 atmosphere and below and critical boundary velocity gradient for flashback at pressures below 1 atmosphere over a range of compositions for hydrogen-air burner flames. Pressure exponents of 0.23 for burning velocity and 1.35 for flashback velocity gradient was found. Results regarding blowoff and general stability loop, burning velocity, relations among various combustion properties, and reaction order from pressure exponents are provided.
Date:
November 1956
Creator:
Fine, Burton
System:
The UNT Digital Library
A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils
Report presenting a velocity-correction formula for the purpose of calculating, from the known Mach number distribution for a diamond-shaped airfoil at a stream Mach number of 1.0, Mach number distributions on the same airfoil at speeds from a Mach number of about 0.8 to shock-attachment Mach number. An expression for the rate of change of local Mach number with stream Mach number is derived and an explicit equation for the drag coefficient as a function of stream Mach number and thickness ratio is given.
Date:
November 1951
Creator:
Ivey, H. Reese & Harder, Keith C.
System:
The UNT Digital Library
Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61
Results of tests conducted in the 6-foot-diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper ratio on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 degrees and 45 degrees were investigated.
Date:
November 1951
Creator:
Brewer, Jack D. & Fisher, Lewis R.
System:
The UNT Digital Library
Heat Capacity Lag in Gases
Note presenting a review of the literature on the sonic studies of the problem of the excitation of molecular vibrations by collision. The theory on which the interpretation of almost all the sonic work has been based is discussed rather qualitatively in some detail. Results concerning techniques, principal experimental programs, and an interpretation of the results are provided.
Date:
November 1951
Creator:
Walker, Richard
System:
The UNT Digital Library
Experimental Investigation at Low Speed of the Effects of Wing Position on the Static Stability of Models Having Fuselages of Various Cross Section and Unswept and 45 Degrees Sweptback Surfaces
Note presenting an investigation to determine the effects of wing position on the low-speed static longitudinal and static lateral stability of airplane models with fuselages of square and rectangular cross sections and unswept and 45 degree sweptback surfaces. The results of the investigation indicated that at low angles of attack, the complete unswept models with the wing in the high position were more stable or least longitudinally unstable. The results also showed that wing-fuselage interference causes an increase in effective dihedral angle when the wing is moved to the high position.
Date:
November 1956
Creator:
Letko, William
System:
The UNT Digital Library
Langley full-scale-tunnel investigations of the maximum-lift and stalling characteristics of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections
Report presenting an investigation of the results at high Reynolds numbers and low Mach numbers to determine the maximum-lift and stalling characteristics of an aspect-ratio-4 trapezoidal wing with 10-percent-thick, circular-arc airfoil sections. Testing occurred measurements of lift, drag, and pitching-moment coefficients of the basic wing and of the wing with 0.20-chord droop-nose and rear flaps deflected alone and in combination with one another.
Date:
November 1952
Creator:
Lange, Roy H.
System:
The UNT Digital Library
Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections
Report presenting an investigation in the low-turbulence pressure tunnel to determine the effects of Mach and Reynolds number on the maximum lift characteristics of the NACA 65-006, 64-009, 64-210, and 64(sub 2)-215 airfoil sections in smooth and leading-edge roughness conditions. A range of Mach and Reynolds numbers were explored.
Date:
November 1952
Creator:
Racisz, Stanley F.
System:
The UNT Digital Library
Studies on Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Critical Examination of Similarity Theory for Incompressible Flows
Note presenting an investigation of three theories: the momentum transfer theory of Prandtl, the vorticity transfer theory of Taylor, and the similarity theory of Von Kármán. The primary focus is to examine Von Kármán's theory using modern concepts.
Date:
November 1951
Creator:
Lin, C. C. & Shen, S. F.
System:
The UNT Digital Library
Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Similarity Theory for Turbulent Boundary Layer Over a Flat Plate in Compressible Flow
Note presenting a treatment of the problem of turbulent boundary layer over a flat plate in compressible flow. The dissipation term in the energy equation, often neglected, is first carefully studied and found to be of importance. The four main approximations include the turbulence pattern, the boundary-layer growth, the two choices of the length scale, and the effect of pressure gradient.
Date:
November 1951
Creator:
Lin, C. C. & Shen, S. F.
System:
The UNT Digital Library
Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flow: Investigation of Turbulent Boundary Layer Over a Flat Plate in Compressible Flow by the Similarity Theory
Note presenting an investigation of the turbulent-boundary-layer flow over a flat plate in compressible flow. The report shows how the influence of the Mach number can be predicted from the theory after the constant coefficients in the theory are determined by one set of experimental measurements. By averaging the Navier-Stokes equations, differential equations for the mean flow are obtained.
Date:
November 1951
Creator:
Shen, S. F.
System:
The UNT Digital Library
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds
Report discussing a flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Date:
November 1956
Creator:
Mitcham, Grady L.; Stevens, Joseph E. & Norris, Harry P.
System:
The UNT Digital Library
Application of Variational Methods to Transonic Flows With Shock Waves
Note presenting a modification of certain variational methods for the approximate solution of subsonic and transonic flows to compensate for the fact that those methods fail as soon as shock waves occur. By applying a variational principle to the regions of flow behind shock waves and Bateman's original principle to the other regions in the fluid, shock equations can be directly obtained.
Date:
November 1951
Creator:
Wang, Chi-Teh & Chou, Pei-Chi
System:
The UNT Digital Library
Hydrodynamic Investigation of a Series of Hull Models Suitable for Small Flying Boats and Amphibians
Note presenting the results of an investigation to obtain hydrodynamic information on a series of hull models suitable for small flying boats or amphibians of from 2000 to 5000 pounds gross weight. The series of hulls consisted of a basic hull with simple lines, and of plus and minus variations to the design in which the beam, stern-post angle, and afterbody length were altered. The results show that it is possible to design a hull with simple lines that will be suitable for small flying boats or amphibians.
Date:
November 1951
Creator:
Hugli, W. C., Jr. & Axt, W. C.
System:
The UNT Digital Library
Application of Response Function to Calculation of Flutter Characteristics of a Wing Carrying Concentrated Masses
Note presenting concepts involved in the harmonic-response-function method, such as the direct or conjugate characteristic modes, by application of the method to the calculation of the change in flutter characteristics of a wing due to adding concentrated masses.
Date:
November 1951
Creator:
Serbin, H. & Costilow, E. L.
System:
The UNT Digital Library
Investigation of deflectors as gust alleviators on a 0.09-scale model of the Bell X-5 airplane with various wing sweep angles from 20 degrees to 60 degrees at Mach numbers from 0.40 to 0.90
Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a given deflector arrangement as a gust alleviator on a model of the Bell X-5 airplane with various wing sweep angles, Mach numbers, and angles of attack. Results regarding lift, drag, and pitching moment are provided.
Date:
November 1957
Creator:
Croom, Delwin R. & Huffman, Jarrett K.
System:
The UNT Digital Library