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Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method

Description: Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existi… more
Date: March 1951
Creator: Wang, Chi-Teh
Partner: UNT Libraries Government Documents Department
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A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds

Description: One of the problems connected with the sweptback wing is the difficulty of controlling the location of the center of pressure and hence the pitching moment. A method is presented for designing a wing to be self-trimming at a given set of flight conditions. Concurrently, the spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag.
Date: May 11, 1951
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department
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A flight evaluation of the longitudinal stability characteristics associated with the pitch-up of a swept-wing airplane in maneuvering flight at transonic speeds

Description: This report presents the results of flight measurements of longitudinal stability and control characteristics made on a swept-wing jet aircraft to determine the origin of the pitch-up encountered in maneuvering flight at transonic speeds. For this purpose measurements were made of elevator angle, tail angle of attack, and wing-fuselage pitching moments (obtained from measurements of the balancing tail loads).
Date: September 12, 1951
Creator: Anderson, Seth B. & Bray, Richard S.
Partner: UNT Libraries Government Documents Department
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Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling

Description: "An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions"… more
Date: June 22, 1951
Creator: Eckert, E. R. G. & Livingood, J. N. B.
Partner: UNT Libraries Government Documents Department
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An Analysis of the Effects of Aeroelasticity on Static Longitudinal Stability and Control of a Swept-Wing Airplane

Description: From Introduction: "The results of the aforementioned study are presented in this report together with the method of analysis employed. The net stability change is shown together with the individual contributions due to flexibility of wing, tail, and fuselage, both including and neglecting the effect of inertial loads."
Date: March 19, 1951
Creator: Skoog, Richard B.
Partner: UNT Libraries Government Documents Department
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A correlation by means of transonic similarity rules of experimentally determined characteristics of a series of symmetrical and cambered wings of rectangular plan form

Description: Transonic similarity rules are applied to the correlation of experimental data for a series of related rectangular wings of varying aspect ratio, thickness, and camber. The data correlation is presented in two parts: the first part presents the correlation for a series of 22 wings having symmetrical NACA 63a-series sections; the second part is concerned with a study of one type of camber by correlation of the data for a series of 18 cambered wings having NACA 63a2xx and 63a4xx sections.
Date: December 17, 1951
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department
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Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
Date: December 31, 1951
Creator: Nielsen, Jack N. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department
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Investigation of turbines suitable for use in a turbojet engine with high compressor ratio and low compressor-tip speed 5: experimental performance of two-stage turbine with downstream stator

Description: An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.
Date: October 21, 1951
Creator: Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
Partner: UNT Libraries Government Documents Department
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Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine

Description: Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.
Date: March 5, 1951
Creator: Cook, William P. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department
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Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: Note presenting a method by which the total temperature of the gases at the combustion-chamber outlet of a ramjet engine may be determined from the loss in total pressure measured across the combustion chamber. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the altitude wind tunnel over a range of pressure altitudes.
Date: December 1951
Creator: Pinkel, I. Irving
Partner: UNT Libraries Government Documents Department
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Studies of high-temperature protection of a titanium-carbide ceramal by chromium-type ceramic-metal coatings

Description: Report presenting an investigation to gain information concerning the durability of metallic coatings as affected by frit content, firing temperature, firing time, and number of coats. Four coatings of various frit content were prepared and applied to ceramals containing 80 percent chromium and 20 percent cobalt and heated at four different temperatures.
Date: June 1951
Creator: Moore, Dwight G.; Benner, Stanley G. & Harrison, William N.
Partner: UNT Libraries Government Documents Department
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A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils

Description: 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 rat… more
Date: November 1951
Creator: Ivey, H. Reese & Harder, Keith C.
Partner: UNT Libraries Government Documents Department
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General plastic behavior and approximate solutions of rotating disk in strain-hardening range

Description: Report presenting a partly linearized solution of plastic deformation of a rotating disk based on the deformation theory of plasticity and considering finite strains. The method can be used to investigate the general plastic behavior of a rotating disk.
Date: May 1951
Creator: Wu, M. H. Lee
Partner: UNT Libraries Government Documents Department
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Possible Application of Blade Boundary-Layer Control to Improvement of Design and Off-Design Performance of Axial-Flow Turbomachines

Description: "A theoretical discussion of the application of blade boundary-layer control to increase the efficiency and the stage pressure ratio and to improve off-design performance of turbomachines is presented. A method based on the potential flow of a compressible fluid is developed for designing suction, or ejection, slotted blades having a prescribed velocity distribution along the blade and in the slot. The effect of the boundary layer on the design of the slot and the effect of ejecting gas at stag… more
Date: May 1951
Creator: Sinnette, John T., Jr. & Costello, George R.
Partner: UNT Libraries Government Documents Department
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Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61

Description: 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, a… more
Date: November 1951
Creator: Brewer, Jack D. & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Effects of Jet-Outlet Cut-Off Angle on Thrust Direction and Body Pitching Moment

Description: Note presenting a wind-tunnel investigation to determine the effects of jet-outlet cut-off angle on the directional and spreading characteristics of an unheated, subsonic air jet, and on the pitching moment of the body from which the jet issued. Results regarding the jet operating with the wind tunnel off, jet off with the wind tunnel operating, jet operating with the wind tunnel operating, and flow studies with the jet operating and the wind tunnel off are provided.
Date: June 1951
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department
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Effect of tail surfaces on the base drag of a body of revolution at Mach numbers of 1.5 and 2.0

Description: "Wind-tunnel tests were performed at Mach numbers of 1.5 and 2.0 to investigate the influence of tail surfaces on the base drag of a body of revolution without boattailing and having a turbulent boundary layer. The tail surfaces were of rectangular plan form of aspect ratio 2.33 and has symmetrical, circular-arc airfoil section. The results of the investigation showed that the addition of these tail surfaces with the trailing edges at or near the body base incurred a large increase in the base-… more
Date: April 1951
Creator: Spahr, J. Richard & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department
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Practical Methods of Calculation Involved in the Experimental Study of an Autopilot and the Autopilot-Aircraft Combination

Description: Report presenting practical methods for making the calculations required for the analysis of an autopilot and an autopilot-aircraft combination from frequency-response data. From Summary: "Equations are derived for determining the servo-system error voltage for both displacement input signal and displacement plus rate of displacement input signals, the autopilot frequency response for addition of rate of displacement input signal, the servo-system frequency response for a change of gain, and th… more
Date: June 1951
Creator: Smaus, Louis H. & Stewart, Elwood C.
Partner: UNT Libraries Government Documents Department
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Charts and tables for use in calculations of downwash of wings of arbitrary plan form

Description: From Summary: "Values of the downwash of a horseshoe vortex in compressible flow are presented in the form of charts and tables. The use of the charts and tables in the calculations of the downwash of wings of arbitrary plan form is discussed. The results of a few calculations are compared with experimental results."
Date: May 1951
Creator: Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department
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A numerical approach to the instability problem of monocoque cylinders

Description: Report presenting two closely related methods which employ operations tables that have been developed and used in the calculation of buckling load of a monocoque cylinder subjected to pure bending. The buckling loads of three cylinders with very different characteristics were calculated using the methods.
Date: April 1951
Creator: Boley, Bruno A.; Kempner, Joseph & Mayers, J.
Partner: UNT Libraries Government Documents Department
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Method for calculation of ram-jet performance

Description: Report presenting a method utilizing precalculated solutions graphically presented for calculating subsonic or supersonic ramjet performance parameters with the associated equations and graphs. By assuming constant values of specific-heat ratio and gas constant equal to those of standard air, the thrust-coefficient calculation has been reduced to a few simple operations.
Date: June 1951
Creator: Henry, John R. & Bennett, J. Buel
Partner: UNT Libraries Government Documents Department
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Floating characteristics of a plain and a horn-balanced rudder at spinning attitudes as determined from rotary tests on a model of a typical low-wing personal-owner airplane

Description: Report presenting an investigation to determine the floating characteristics of full-length plain and horn-balanced rudders during rotary tests at spinning attitudes on a scale model of a typical low-wing personal-owner airplane. The investigation included the determination of the effects of the horizontal tail and the wing on the rudder floating characteristics.
Date: May 1951
Creator: Bihrle, William, Jr.
Partner: UNT Libraries Government Documents Department
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