National Advisory Committee for Aeronautics (NACA) - 2,223 Matching Results

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Velocity Distribution on Wing Sections of Arbitrary Shape in Compressible Potential Flow 3: Circulatory Flows Obeying the Simplified Density-Speed Relation

Description: "The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determining the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerically by an iteration meth… more
Date: March 1950
Creator: Bers, Lipman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method of computing subsonic flows around given airfoils

Description: From Summary: "An extremely simple computational method is established for obtaining circulatory flows around given bodies to a high degree of accuracy for flows satisfying the linear pressure and specific-volume equation of state. The method depends not on an integral equation but on the transformation from the holograph to the physical plane involving the determination of an arbitrary analytic function. The determination of the arbitrary analytic function by elementary means results in a clos… more
Date: March 1950
Creator: Gelbart, Abe & Resch, Daniel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Continuation of a Potential Gas Flow Across the Sonic Line

Description: "Simple, sufficient conditions are given under which a two-dimensional steady compressible flow can be continued across the line of Mach number 1 as a continuous supersonic flow. Methods for the actual computation of the flow are described. The problem is of importance in the theory of transonic flows past airfoils" (p. 1).
Date: April 1950
Creator: Bers, Lipman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Method of Experimentally Determining Radial Distributions of Velocity Through Axial-Flow Compressor

Description: Note presenting a method by which the energy and continuity relations are simultaneously solved to express the velocity distributions downstream of any compressor blade row in terms of outlet total temperature, total pressure, and relative flow angle. The method is intended for use in units in which only a limited amount of experimental data can be obtained.
Date: April 1950
Creator: Finger, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of rate of change of angle of attack on the maximum lift of a small model

Description: Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.
Date: March 1950
Creator: Harper, Paul W. & Flanigan, Roy E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number

Description: Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
Date: March 1950
Creator: Neihouse, Anshal I. & Pepoon, Philip W.
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbulence-Intensity Measurements in a Jet of Air Issuing From a Long Tube

Description: Report presenting data for turbulent-velocity-fluctuation components and mean-velocity distributions measured in the subsonic jet issuing from a pipe in which a fully developed turbulent flow was established. Axial and radial components of the fluctuation velocities were examined as functions of Reynolds number and position in the jet.
Date: May 1951
Creator: Little, Barney H., Jr. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Torsional Strength of Stiffened D-Tubes

Description: "The present report covers a series of torsional tests on stiffened D-tubes of alclad 24S-T3 aluminum alloy having a cross section similar to the NACA 0012 airfoil section and a closing web at 30 percent of the chord. The stiffeners consisted of ribs and stringers. An average-strength chart has been developed for this type of structure that takes into account the skin thickness, rib spacing, and stringer spacing. This chart may also be used for unstiffened D-tubes" (p. 1).
Date: May 1951
Creator: Kavanaugh, E. S. & Drinkwater, W. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Particular Integrals of the Prandtl-Busemann Iteration Equations for the Flow of a Compressible Fluid

Description: Note presenting the particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid that have been obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The forms of the particular integrals, derived for subsonic flow, are readily adapted to supersonic flows with only a change in sign of one of the parameters of the problem.
Date: August 1950
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Relation Between Inflammables and Ignition Sources in Aircraft Environments

Description: From Summary: "A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presen… more
Date: December 1950
Creator: Scull, Wilfred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Application of Mathieu Functions in the Theory of Subsonic Compressible Flow Past Oscillating Airfoils

Description: Note presenting an account of explicit solutions in terms of Mathieu functions of the problem of two-dimensional subsonic compressible flow past oscillating airfoils. The results are applied to the calculation of three-dimensional corrections for the two-dimensional theory and the effect of the incorporation of the three-dimensional effects on the Mathieu function solution of the two-dimensional problem is shown.
Date: May 1951
Creator: Reissner, Eric
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On Two-Dimensional Flow After a Curved Stationary Shock (With Special Reference to the Problem of Detached Shock Waves)

Description: Note presenting an analysis of the problem of two-dimensional flow behind a curved stationary shock wave. The method assumes a given shock-wave shape, which automatically determines certain initial conditions on flow variables, and flow-pattern, including any body shape, follows from initial conditions.
Date: May 1951
Creator: Shu, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A General Integral Form of the Boundary-Layer Equation for Incompressible Flow With an Application to the Calculation of the Separation Point of Turbulent Boundary Layers

Description: Note presenting a general integral form of the boundary-layer equation that is derived from the Prandtl partial-differential boundary-layer equation. The general integral equation, valid for either laminar or turbulent incompressible boundary-layer flow, contains the Von Karman momentum equation, the kinetic-energy equation, and the Loitsianskii equation as special cases.
Date: August 1950
Creator: Tetervin, Neal & Lin, Chia Chiao
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations on the forces and moments for an oscillating wing-aileron combination in two-dimensional potential flow at sonic speed

Description: Report presenting the use of linearized theory for compressible unsteady flow to obtain the velocity potential and lift and moment for a thin, harmonically oscillating, two-dimensional wing-aileron combination moving at sonic speed.
Date: January 1952
Creator: Nelson, Herbert C. & Berman, Julian H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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