National Advisory Committee for Aeronautics (NACA) - 190 Matching Results

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Additional Static and Fatigue Tests of High-Strength Aluminum-Alloy Bolted Joints

Description: From Introduction: "Early in 1951 the National Advisory Committee for Aeronautics published, as Technical Note 2276 (ref. 1), a report by the Aluminum Research Laboratories of the Aluminum Company of America on the results of static and fatigue tests of high-strength aluminum alloy monobloc specimens and bolted joints. In view of special interest shown by several aircraft companies, certain expansions of the test program were undertaken by the Aluminum Research Laboratories and are reported her… more
Date: July 1954
Creator: Hartmann, E. C.; Holt, Marshall & Eaton, I. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Description: From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."
Date: July 1955
Creator: Martin, John C. & Malvestuto, Frank S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of base pressure at supersonic velocities and comparison with experiment

Description: From Introduction: "The primary purpose of the investigation described in the present report is to formulate a method which is of value for quantitative calculations of base pressure on airfoils and bodies without boat-tailing. Part I consists of a detailed study of the base pressure in two-dimensional and axially-symmetric inviscid flow. In part II a semi-empirical theory is formulated since the results of part I indicate that an inviscid-flow theory cannot possibly be satisfactory for quantit… more
Date: July 1950
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory

Description: From Introduction: "The buzz or pulsation of axially symmetric supersonic inlets having central bodies has been the subject of investigations since Oswatitsch first observed the phenomenon in 1944 (ref.1). This buzzing is essentially an oscillation of the normal shock along the spike of certain diffusers operating at mass flows below design, and this buzz decreases the performance of the propulsion units appreciably (ref.2). This paper continues the analysis of the buzzing cycle by means of a m… more
Date: July 1956
Creator: Trimpi, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the normal accelerations and airspeeds of a two-engine type of transport airplane in commercial operations on routes in the central United States from 1948 to 1950

Description: Report presenting normal-acceleration and airspeed data obtained from V-G recorders installed in a two-engine type of transport airplane, employed in routine commercial operation in the United States for two years, which was analyzed to determine the gust and gust-load experiences of the airplane. Results regarding the acceleration experience, gust experience, average operating airspeed, maximum airspeed, comparison of predicted gust envelopes, and predicted gust-load envelopes are provided.
Date: July 1952
Creator: Walker, Walter G. & Schumacher, Paul W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of two-dimensional compressible-flow loss characteristics downstream of turbomachine blade rows in terms of basic boundary-layer characteristics

Description: Report presenting the effect of compressibility on the loss characteristics downstream of two-dimensional turbomachine blade rows. In this particular example, increasing the trailing-edge thickness increased the overall loss coefficients significantly, with an effect of compressibility only at exit flow angles close to axial.
Date: July 1955
Creator: Stewart, Warner L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical and Experimental Investigation of Adiabatic Turbulent Flow in Smooth Tubes

Description: Note presenting equations derived for the prediction of velocity distributions for fully developed adiabtic turbulent flow in smooth tubes; both the incompressible and compressible flow cases were treated. The analysis produced a single equation that represents flow in both the conventional buffer layer and the laminar layer. The results for fully developed flow were correlated by using conventional dimensionless velocity and distance parameters, and agreed closely with those of Nikuradse and o… more
Date: July 1950
Creator: Deissler, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Investigation of Fully Developed Laminar Flow in Tubes With Heat Transfer With Fluid Properties Variable Along the Radius

Description: "In the analytical investigation reported herein, which was conducted in the NACA Lewis laboratory, both velocity and temperature distribution are obtained for fully developed laminar flow in tubes of gases and of liquid metals with variable fluid properties" (p. 1).
Date: July 1951
Creator: Deissler, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of X-Ray Absorption to Measurement of Small Air-Density Gradients

Description: Report presenting an analysis of two x-ray absorption methods for determining small air-density gradients. One method uses a Geiger-Mueller counter for detection and the other uses photographic film for detection. Both of the methods are found to have some advantages and disadvantages.
Date: July 1951
Creator: Weltmann, Ruth N.; Fairweather, Steven & Papke, Daryl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate aerodynamic influence coefficients for wings of arbitrary plan form in subsonic flow

Description: From Summary: "Aerodynamic influence coefficients for symmetrically loaded wings of arbitrary plan form in subsonic flow are derived from a simple empirical method of estimating spanwise lift distributions. The application of the coefficients to an aeroelastic analysis is discussed."
Date: July 1950
Creator: Diederich, Franklin W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate design method for high-solidity blade elements in compressors and turbines

Description: Note presenting an approximate blade-element design method for compressible or incompressible nonviscous flow in high-solidity stators or rotors of axial-, radial-, or mixed-flow compressors, turbines, or two-dimensional cascades. The method is based upon channel-type flow between blade elements on a specified surface of revolution that lies between the hub and shroud and is concentric with the axis of the compressor turbine.
Date: July 1951
Creator: Stanitz, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate method for determining equilibrium operation of compressor component of turbojet engine

Description: Report presenting a method for estimating the equilibrium operating line for a compressor as a component part of a turbojet engine. Charts are presented for locating the equilibrium operating line on the performance map of the compressor component of a turbojet engine operating at sea-level static conditions. Results regarding design-point operation, off-design operation, effect of compressor-discharge bleed, effect of jet-nozzle adjustment, and an example are provided.
Date: July 1955
Creator: Huppert, Merle C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Axial-Momentum Theory for Propellers in Compressible Flow

Description: Note presenting the development of the axial-momentum theory for compressible flow as a step in the formulation of a rational propeller theory for compressible flow. The simple theory neglects some properties but predicts flow conditions through a propeller that are significantly different from the conditions predicted by the incompressible-flow theory.
Date: July 1951
Creator: Vogeley, Arthur William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Behavior of materials under conditions of thermal stress

Description: Report presenting a review of available information on the behavior of brittle and ductile materials under conditions of thermal stress and thermal shock. A number of practical methods that have been used to minimize the negative effects of thermal stress and shock are provided.
Date: July 1953
Creator: Manson, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bench-Test Investigation of the Transient-Response Characteristics of Several Simulated Airplanes Incorporating an Autopilot Sensitive to Yawing Accelerations

Description: Note presenting testing of an autopilot sensitive to yawing acceleration, which was used to control four simulated airplane (mass-spring) configurations, and a series of bench tests to determine the response characteristics of the combinations.
Date: July 1951
Creator: Howard, Donald A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending Tests of Ring-Stiffened Circular Cylinders

Description: Twenty-five ring-stiffened circular cylinders were loaded to failure in bending. The results are presented in the form of design curves which are applicable to cylinders with heavy rings that fail as a result of local buckling.
Date: July 1956
Creator: Peterson, James P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A blade-element analysis for lifting rotors that is applicable for large inflow and blade angles and any reasonable blade geometry

Description: Report presenting some simple approximate solutions that are derived for the relationships between rotor thrust and flight path velocity components and the rotor blade angle, torque, and in-plane forces.
Date: July 1952
Creator: Castles, Walter, Jr. & New, Noah C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

Description: From Summary: "Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possib… more
Date: July 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-layer development and skin friction at mach number 3.05

Description: Experimental and theoretical results are presented for boundary layer studies consisting of Schlieren observations and momentum surveys made on hollow cylinder models with their axes aligned parallel to the stream. Results were obtained for three model diameters and for natural and artificially induced turbulent boundary layer flows.
Date: July 1952
Creator: Brinich, Paul F. & Diaconis, Nick S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Transition on a Cooled 20 Degree Cone at Mach Numbers of 1.5 and 2.0

Description: Note presenting an investigation of the laminar boundary layer on a cooled 20 degree cone at Mach numbers of 1.5 and 2.0 to determine the variation of the position of transition with surface temperature for both constant surface temperatures and surface temperatures that increased toward the rear of the cone. The increase in the extent of the laminar boundary layer for uniform surface temperatures was found to be directly proportional to the difference between the surface and recovery temperatu… more
Date: July 1950
Creator: Scherrer, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Effect of Some Airplane Handling Techniques on the Ground-Run Distance in Landing on Slippery Runways

Description: Note presenting some calculations made on the basis of simplifying assumptions to determine the effect on the ground-run distance of maintaining a nose-high attitude instead of a three-point attitude in landings of several types of jet airplanes on slippery runways. The airplanes considered were a swept-wing transport and unswept-, swept-, and delta-wing fighters. Results regarding the effect of airplane attitude and effect of flap retraction are provided.
Date: July 1957
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The calculation of downwash behind wings of arbitrary plan form at supersonic speeds

Description: Report presenting exact and approximate methods based on linearized supersonic flow theory for the calculation of the velocity potential and the downwash from thin wings of arbitrary plan form. The applicability of the method inherently depends on a knowledge of the load distribution over the plan form of the wing.
Date: July 1950
Creator: Martin, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The calculation of modes and frequencies of a modified structure from those of the unmodified structure

Description: Report presenting a method that has been developed for the calculation of the natural coupled or uncoupled frequencies and modes of a structure with modifications directly from the known modes and frequencies of the unmodified structure. The method is advantageous when the modes and frequencies of the unmodified structure either are known or are required along with the modes and frequencies of the structure with various modifications.
Date: July 1950
Creator: Kruszewski, Edwin T. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Transonic Flows Past Thin Airfoils by Integral Method

Description: Note presenting a method of calculating two-dimensional compressible flows past thin airfoils with particular reference to the transonic speed range. The method is based on the integral form of the equation of continuity and on the intrinsic form, in terms of the streamline curvature, of the irrotationality condition.
Date: July 1950
Creator: Perl, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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