National Advisory Committee for Aeronautics (NACA) - 275 Matching Results

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Accelerations in Transport-Airplane Crashes

Description: From Introduction: "A study of crash-impact survival in light airplanes is reported in references 1 and 2. A similar study for fighter airplanes is reported in reference 3. This report discusses crash-impact survival in transport airplanes."
Date: February 1958
Creator: Preston, G. Merritt & Pesman, Gerard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Description: From Introduction: " Considerable analytical and experimental research has been done to find means of reducing the noise levels of the turbojet transports. Noise levels can be decreased by engine redesign to reduce the jet-exit velocity (ref. 1), proper flight-climb techniques (ref. 2), and the use of noise-suppression exhaust nozzles (refs. 3 to 5). The present report is concerned with the last method."
Date: April 1958
Creator: Ciepluch, Carl C.; North, Warren J.; Coles, Willard D. & Antl, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Description: From Summary: "The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions."
Date: February 1958
Creator: Gray, Vernon H. & von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of harmonic forces produced at hub by imbalances in helicopter rotor blades

Description: From Introduction: "First, an analysis of loads transmitted to the hub by balanced blades will be given. In the second section, the additional loads transmitted to the hub in a direction normal to the plane of rotation of the blades by imbalances in a rotor are derived. In the entire analysis, the results are given in terms of the forces transmitted to the hub by a single rotating helicopter blade in flight, and these are regarded as known or given."
Date: April 1958
Creator: Morduchow, M. & Muzyka, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Ramjet Engines Using Supersonic Combustion

Description: From Introduction: "The concept of supersonic combustion is by no means new, although little work appears to have been published on the subject. For example, an analysis of supersonic combustion to provide lift under a wing is given in reference 1. Reference 2 discusses applications to hypersonic ramjets being studied at the University of Michigan."
Date: September 1958
Creator: Weber, Richard J. & MacKay, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of the Creep Behavior of a Square Plate Loaded in Edge Compression

Description: From Introduction: "In reference 1 results of creep tests and empirical method for predicting collapse times are presented for plates loaded in compression on two opposite edges and with the remaining edges unloaded and supported in V-groove fixtures. Other approximate methods for handling plates having types of edge support are suggested in reference 2; however, experimental verification for these methods is quite limited. In reference 3 an analysis based on small-deflection theory is made of … more
Date: September 1958
Creator: McComb, Harvey G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the turbulent boundary-layer characteristics on a flat plate with distributed light-gas injection

Description: From Introduction: "The present paper is concerned with a transpiration cooling system in which the coolant passes through the surface it is protecting before entering the surrounding boundary layer. Analyses and experiments have been performed to determine the effect of distributed air transportation through flat surfaces over which air flows in turbulent boundary layer (refs. 2, 3, and 4)."
Date: February 1958
Creator: Rubesin, Morris W. & Pappas, Constantine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages

Description: From Introduction: "In reference 1, wall temperature distributions for turbulent flow in rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients, together with assumed similarity of the wall heat-transfer and wall shear-stress variations; no attempt was made to calculate either the heat-transfer coefficients or the velocity and temperature distributions in the fluid field. Some calculations of velocity and shear-stress… more
Date: September 1958
Creator: Deissler, Robert G. & Taylor, Maynard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers With Variable Fluid Properties

Description: From Introduction: "In the turbulent case, however, the results of the various analyses disagree markedly because of the different assumptions made by various authors. These analyses are reviewed in references 1 to 3. The analysis is extended to flow and heat transfer in a boundary layer at high Mach numbers in this paper. (Some preliminary results were presented in ref. 11.)"
Date: April 1958
Creator: Deissler, R. G. & Loeffler, A. L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical and Experimental Investigation of Aerodynamic Forces and Moments on Low-Aspect-Ratio Wings Undergoing Flapping Oscillations

Description: "Aerodynamic forces and moments associated with flapping oscillations of finite wings at low speeds are considered. A comparison of theoretical and experimental results is made for a rectangular wing of aspect ratio 2. Calculated results are also given for three tapered wings of aspect ratio 3 with varying amounts of sweepback" (p. 1).
Date: August 1958
Creator: Woolston, Donald S.; Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical and Experimental Investigation of Temperature Recovery Factors for Fully Developed Flow of Air in a Tube

Description: Note presenting an analysis made for predicting temperature recovery factors for fully developed flow in a tube. Most of the attention was confined to turbulent flow. Both analytical and experimental results are provided for the air flow.
Date: September 1958
Creator: Deissler, R. G.; Weiland, W. F. & Lowdermilk, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical relation for wake momentum thickness and diffusion ratio for low-speed compressor

Description: From Introduction: "The present report presents the derivation of a simple equation for blade-wake mometum thickness as a function of suction-surface diffusion ratio based on the one-dimensional boundary-layer mometum equation in conjunction with simplifying approximations."
Date: August 1958
Creator: Lieblein, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analytical study of turbulent and molecular mixing in rocket combustion

Description: From Introduction: "The many physical processes which occur simultaneously in rocket combustion make the entire process extremely complex (ref. 1). The combustion chamber length required for evaporation of liquid-propellant sprays has already been studied (refs. 2, 3, and 4)."
Date: September 1958
Creator: Bittker, David A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of a high-temperature static strain gage to the measurement of thermal stresses in a turbine stator vane

Description: From Introduction: "This report describes the high-temperature static strain gage and presents the results obtained in a determination of the thermal stresses in a turbine stator vane resulting from the temperature distribution obtained under steady-state conditions at rated speed and temperature of the engine."
Date: March 1958
Creator: Kemp, R. H.; Morse, C. R. & Hirschberg, M. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Approach to the Problem of Estimating Severe and Repeated Gust Loads for Missile Operations

Description: Note presenting an analysis of available airplane measurements of vertical gust velocity in order to arrive at a simple description of the frequency and intensity of gust velocities experienced by airplanes in operations. For the purpose of application to missile operations, the results obtained are modified to eliminate the effects of storm-avoidance procedures normally followed in airplane operations.
Date: September 1958
Creator: Press, Harry & Steiner, Roy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An approximate analytical method for studying entry into planetary atmospheres

Description: Report presenting a single, ordinary, nonlinear differential equation of second order that can be used for determining entry into an exponential planetary atmosphere. The reduced equation includes various terms, some of which represent the gravity force, the centrifugal acceleration, and the lift force. A number of solutions for lifting and nonlifting vehicles entering at various initial angles are obtained from the complete nonlinear equation.
Date: May 1958
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Description: Report presenting an extension of a method for calculating motions in angles of attack and sideslip resulting from a trim angle of attack and steady rolling velocity to the condition of pitching- and yawing-moment inputs. The resulting formulas are intended primarily for rolling-velocity conditions in which rolling divergence is not encountered.
Date: September 1958
Creator: Moul, Martin T. & Brennan, Teresa R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate Method for Calculation of Laminar Boundary Layer With Heat Transfer on a Cone at Large Angle of Attack in Supersonic Flow

Description: Note presenting the use of an integral technique to reduce the laminar boundary-layer equations on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The method enables the skin friction coefficients and Stanton number to be calculated in a much shorter time than was needed to obtain exact numerical solutions from the boundary-layer equations.
Date: September 1958
Creator: Brunk, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Approximate Method for Design or Analysis of Two-Dimensional Subsonic-Flow Passages

Description: Note presenting a method for the design and analysis of two-dimensional subsonic-flow passages with isentropic nonviscous flow. The method is based on the relation between the pressure change across a stream tube and the centrifugal force resulting from the curvature of the flow. In an example, the method was applied to the design of an expanding elbow at each of two Mach numbers.
Date: April 1958
Creator: Valentine, E. Floyd
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Description: Report presenting an analysis for obtaining approximate solutions of the similarity equations for three-dimensional laminar-boundary-layer flows over a flat surface under main-flow streamlines that are translates and representable as infinite series expansions.
Date: September 1958
Creator: Hansen, Arthur G. & Herzig, Howard Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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