Technical Report Archive & Image Library (TRAIL) - 32 Matching Results

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Theoretical lift and drag of thin triangular wings at supersonic speeds

Description: "A method is derived for calculating the lift and the drag due to lift of point-forward triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary or "supersonic sources" solution of the linearized equation of motion is used to find the potential function of a line of doublets. The flow about the triangular flat plate is then obtained by a surface distribution of these doublet lines. The lift-curve slope of triangular wings is found to be a function of the … more
Date: November 29, 1946
Creator: Brown, Clinton E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds

Description: An approximate method is presented for the calculation of the external lift, moment, and pressure drag of slender open-nose bodies of revolution of supersonic speeds. The lift, moment, and pressure drag of a typical ram-jet body shape are calculated at Mach numbers 1.45, 1.60, 1.75, and 3.00; and the lift and moment results are compared with available experimental data. The agreement of the calculated lift and moment data with the experimental data is excellent. The pressure-drag comparison was… more
Date: December 29, 1945
Creator: Brown, Clinton E. & Parker, Hermon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition

Description: Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation. Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil-film studies. The maximum scope of measurement encompassed Mach numbers between 0.4 and 3.6, and length Reynolds nu… more
Date: November 29, 1956
Creator: Chapman, Dean R.; Kuehn, Donald M. & Larson, Howard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities

Description: From Summary: "Measurements of base pressure are presented for 29 blunt-trailing-edge wings having an aspect ratio of 3.0 and various airfoil profiles. The different profiles comprised thickness ratios between 0.05 and 0.10, boattail angles between -2.9 degrees and 20 degrees, and ratios of trailing-edge thickness to airfoil thickness between 0.2 and 1.0. The tests were conducted at Mach numbers of 1.25, 1.5, 2.0, and 3.1. For each Mach number, the Reynolds number and angle of attack were varie… more
Date: October 29, 1951
Creator: Chapman, Dean R.; Wimbrow, William R. & Kester, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control

Description: Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude … more
Date: December 29, 1950
Creator: Curfman, Howard J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of hecter fuel with export aviation gasoline

Description: Among the fuels which will operate at compression ratios up to at least 8.0 without preignition or "pinking" is hecter fuel, whence a careful determination of its performance is of importance. For the test data presented in this report the hecter fuel used was a mixture of 30 per cent benzol and 70 per cent cyclohexane, having a low freezing point, and distilling from first drop to 90 per cent at nearly a constant temperature, about 20 degrees c. below the average distillation temperature ("mea… more
Date: January 29, 1920
Creator: Dickinson, H. C.; Gage, V. R. & Sparrow, S. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of the Method of Characteristics to Supersonic Rotational Flow

Description: "A system for calculating the physical properties of supersonic rotational flow with axial symmetry and supersonic rotational flow in a two-dimensional field was determined by use of the characteristics method. The system was applied to the study of external and internal flow for supersonic inlets with axial symmetry. For a circular conical inlet the shock that occurred at the lip of the inlet became stronger as it approached the axis of the inlet and became a normal shock at the axis" (p. 111). more
Date: April 29, 1946
Creator: Ferri, Antonio
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary flight tests of the N.A.C.A. Roots type aircraft engine supercharger

Description: "An investigation of the suitability of the N.A.C.A. Roots type aircraft engine supercharger to flight-operating conditions, as determined the effects of the use of the supercharger upon engine operation and airplane performance, is described in this report. Attention was concentrated on the operation of the engine-supercharger unit and on the improvement of climbing ability; some information concerning high speeds at altitude was obtained. The supercharger was found to be satisfactory under fl… more
Date: December 29, 1926
Creator: Gardiner, Arthur W. & Reid, Elliott G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the flow of a compressible fluid by the hodograph method 2: fundamental set of particular flow solutions of the Chaplygin differential equation

Description: From Summary: "The differential equation of Chaplygin's jet problem is utilized to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The particular solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows. It is shown that the geometric-mean type of velocity… more
Date: September 29, 1944
Creator: Garrick, I. E. & Kaplan, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Flow of a Compressible Fluid by the Hodograph Method. II - Fundamental Set of Particular Flow Solutions of the Chaplygin Differential Equation

Description: From Summary: "The differential equation of Chaplygin's jet problem is utilized to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The particular solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows. It is shown that the geometric-mean type of velocity… more
Date: September 29, 1944
Creator: Garrick, I. E. & Kaplan, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flutter and oscillating air-force calculations for an airfoil in two-dimensional supersonic flow

Description: A connected account is given of the Possio theory of non-stationary flow for small disturbances in a two-dimensional supersonic flow and of its application to the determination of the aerodynamic forces on an oscillating airfoil. Further application is made to the problem of wing flutter in the degrees of freedom - torsion, bending, and aileron rotations. Numerical tables for flutter calculations are provided for various values of the Mach number greater than unity. Results for bending-torsion … more
Date: May 29, 1946
Creator: Garrick, I. E. & Rubinow, S. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Minimization for Wings and Bodies in Supersonic Flow

Description: "The minimization of inviscid fluid drag is studied for aerodynamic shapes satisfying the conditions of linearized theory, and subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one of determining two-dimensional potential flows satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions. A general method for determining integral relations between perturbation velocity components is developed. … more
Date: November 29, 1957
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of temperature distribution and elastic properties of materials on gas-turbine-disk stresses

Description: From Summary: "Calculations were made to determine the influence of changes in temperature distribution and in elastic material properties on calculated elastic stresses for a typical gas-turbine disk. Severe temperature gradients caused thermal stresses of sufficient magnitude to reduce the operating safety of the disk. Small temperature gradients were found to be desirable because they produced thermal stresses that subtracted from the centrifugal stresses in the region of the rim."
Date: March 29, 1947
Creator: Holms, Arthur G. & Faldetta, Richard D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Sound from a two-blade propeller at supersonic tip speeds

Description: Report presents the results of sound measurements at static conditions made for a two-blade 47-inch-diameter propeller in the tip Mach number range 0.75 to 1.30. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. In addition, the measured data are compared with calculations by the theory of Gutin which has previously been found adequate for predicting the sound at subsonic tip speeds. Curves are presented from which the maximum over-all noise levels in free… more
Date: March 29, 1951
Creator: Hubbard, Harvey H. & Lassiter, Leslie W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Plastic Deformation of Aluminum Single Crystals at Elevated Temperatures

Description: "This report describes the results of a comprehensive study of plastic deformation of aluminum single crystals over a wide range of temperatures. The results of constant-stress creep tests have been reported for the temperature range from 400 degrees to 900 degrees F. For these tests, a new capacitance-type extensometer was designed. This unit has a range of 0.30 inch over which the sensitivity is very nearly linear and can be varied from as low a sensitivity as is desired to a maximum of 20 mi… more
Date: December 29, 1953
Creator: Johnson, R. D.; Young, A. P. & Schwope, A. 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: "The particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid are obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The assumption is made that the Prandtl-Glauert solution of the linearized or first-order iteration equation for the two-dimensional flow of a compressible fluid is known. The forms of the particular integrals, derived for subs… more
Date: May 29, 1950
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Supersonic Aerodynamic Heating With Continuous Fluid Injection

Description: From Introduction: "The aerodynamic heating problem assumes considerable importance at high-supersonic speeds. Sanger and Bredt (reference 1) have calculated the high-speed aerodynamic forces and equilibrium surface temperature at extremely high altitudes where the molecular mean free path is large (free-molecule-flow region) compared with a characteristic body dimension. The theoretical investigation of Lees (reference 2) on the stability of the laminar boundary layer in compressible flow ind… more
Date: September 29, 1949
Creator: Klunker, E. B. & Ivey, H. Reese
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Method for calculating the rolling and yawing moments due to rolling for unswept wings with or without flaps or ailerons by use of nonlinear section lift data

Description: From Summary: "The methods of NACA reports 865 and 1090 have been applied to the calculation of the rolling-moment and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods are based on lifting-line theory and allow the use of nonlinear section lift data. The method presented in this report permits calculations to be made somewhat beyond maximum lift for wings having no twist or continuous twist and employing airfoil sections which do not dis… more
Date: January 29, 1953
Creator: Martina, Albert P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Line-Vortex Theory for Calculation of Supersonic Downwash

Description: "The perturbation field induced by a line vortex in a supersonic stream and the downwash behind a supersonic lifting surface are examined to establish approximate methods for determining the downwash behind supersonic wings. Lifting-lines methods are presented for calculating supersonic downwash. A bent lifting-line method is proposed for computing the downwash field behind swept wings. When applied to triangular wings with subsonic leading edges, this method gives results that, in general, are… more
Date: April 29, 1949
Creator: Mirels, Harold & Haefeli, Rudolph C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Calculated Effect of Various Hydrodynamic and Aerodynamic Factors on the Take-Off of a Large Flying Boat

Description: Report presents the results of an investigation made to determine the influence of various factors on the take-off performance of a hypothetical large flying boat by means of take-off calculations. The factors varied in the calculations were size of hull (load coefficient), wing setting, trim, deflection of flap, wing loading, aspect ratio, and parasite drag. The take-off times and distances were calculated to the stalling speeds and the performance above these speeds was separately studied to … more
Date: April 29, 1940
Creator: Olson, R. E. & Allison, J. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Investigation of a Powered Dynamic Model of a Large Long-Range Flying Boat

Description: "Principles for designing the optimum hull for a large long-range flying boat to meet the requirements of seaworthiness, minimum drag, and ability to take off and land at all operational gross loads were incorporated in a 1/12-size powered dynamic model of a four-engine transport flying boat having a design gross load of 165,000 pounds. These design principles included the selection of a moderate beam loading, ample forebody length, sufficient depth of step, and close adherence to the form of a… more
Date: November 29, 1946
Creator: Parkinson, John B.; Olson, Roland E. & Haar, Marvin I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Study of the Application of Power-Spectral Methods of Generalized Harmonic Analysis to Gust Loads on Airplanes

Description: "The applicability of some results from the theory of generalized harmonic analysis (or power-spectral analysis) to the analysis of gust loads on airplanes in continuous rough air is examined. The general relations for linear systems between power spectrums of a random input disturbance and an output response are used to relate the spectrum of airplane load in rough air to the spectrum of atmospheric gust velocity. The power spectrum of loads is shown to provide a measure of the load intensity … more
Date: September 29, 1952
Creator: Press, Harry & Mazelsky, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Development of Turbulent Wakes From Vortex Streets

Description: "Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hot-wire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges" (p. 1).
Date: May 29, 1952
Creator: Roshko, Anatol
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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