National Advisory Committee for Aeronautics (NACA) - 259 Matching Results

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Accuracy of Approximate Methods for Predicting Pressures on Pointed Nonlifting Bodies of Revolution in Supersonic Flow

Description: Note presenting an investigation of the accuracy and range of applicability of the linearized theory, second-order theory, tangent-cone method, conical-shock-expansion theory, and Newtonian theory for predicting pressure distributions on pointed bodies of revolution at zero angle of attack. Three shapes, cone, ogive, and a modified optimum body, are investigated over a wide range of fineness ratios and Mach numbers. The results indicated that for most combinations of fineness ratio and Mach num… more
Date: August 1952
Creator: Ehret, Dorris M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Achievement of Continuous Wall Curvature in Design of Two-Dimensional Symmetrical Supersonic Nozzles

Description: "Auxiliary boundary conditions are derived to assure continuity of wall curvature in applying the method of characteristics to the design of two-dimensional symmetrical supersonic nozzles. An illustrative example is included" (p. 1).
Date: January 1952
Creator: Evvard, J. C. & Marcus, Lawrence R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes

Description: From Introduction: "The results of one phase of this investigation, presented in reference 1, have indicated that hull drag can be reduced without causing large changes in aerodynamic stability and hydrodynamic performance by the use of high length-beam ratios. Another phase of the investigation, reference 2, indicated that hulls of the deep-step planning-tail type have much lower air drag than the conventional type of hull and about the same aerodynamic stability; tank tests, reference 3, have… more
Date: June 1952
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody

Description: From Summary: "An investigation was made to determine the aerodynamic characteristics in the presence of a wing of three-step planning-tail flying-boat hulls which differed only in the amount of step fairing. The purpose of comparison, tests were also made of a transverse-step hull with an extended afterbody."
Date: August 1952
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E.; Ridyard, Herbert W. & Cromer, Nancy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Design of Supersonic Propellers from Structural Considerations

Description: From Summary: "The aerodynamic design of propellers from considerations of centrifugal force is presented. By applying a constant minimum value of thickness ratio from root to tip and allowing the distribution of required area to appear in the blade plan form, propellers with good efficiency are realized at high Mach numbers by the method of this paper."
Date: December 1952
Creator: Hammack, Jerome B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics

Description: From Introduction: "The servo system considered in this report is in the latter category, due mainly to the fact its amplifier tends to saturate. An investigation of the longitudinal dynamic response of the stabilized airplane was made and the results were reported in reference 1. In this investigation it was found that when restricted to linear methods of analysis the performance of the autopilot-aircraft combination could be predicted for only the small range of operation where the elements o… more
Date: June 1952
Creator: Jones, Arthur L. & White, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of flow in a subsonic mixed-flow impeller

Description: From Introduction: "A brief description of the method of analysis is presented herein considering the mean stream surface approach advanced in references 2 and 3, and both the incompressible and compressible solutions are given in detail."
Date: August 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Costilow, Eleanor L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Laminar Free-Convection Flow and Heat Transfer About a Flat Plate Parallel to the Direction of the Generating Body Force

Description: From Introduction: "The problem of free-convection flow as produced by a body force about a flat plate in the direction of the body force was studied at the NACA Lewis laboratory and is treated in a formal and more general manner herein. The method used is somewhat similar to that used in reference 4 wherein consideration was given to the free-convection flow at high Grashof numbers in a horizontal cylinder which had a variable surface-temperature distribution. In addition, the numerical soluti… more
Date: February 1952
Creator: Ostrach, Simon
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Landing-Gear Behavior

Description: Note presenting an analytical study of the behavior of the conventional type of oleo-pneumatic landing gear during the process of landing impact. The basic analysis is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection.
Date: August 1952
Creator: Milwitzky, Benjamin & Cook, Francis E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Normal Accelerations and Airspeeds of One Type of Twin-Engine Transport Airplane in Commercial Operations Over a Northern Transcontinental Route

Description: Note presenting normal-acceleration and airspeed data obtained for one type of twin-engine transport airplane in commercial operations in order to determine the gust and gust-load experiences of the airplane. Results regarding acceleration experience, gust experience, seasonal effects, and effect of special operating restriction are provided.
Date: November 1952
Creator: Steiner, Roy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Supersonic Flow in the Region of the Leading Edge of Curved Airfoils, Including Charts for Determining Surface-Pressure Gradient and Shock-Wave Curvature

Description: Note presenting an investigation of the inviscid flow in the region of the leading edge of curved airfoils with attached shock waves. Tables and charts are presented for determining the surface-pressure gradient and the shock-wave curvature in supersonic flow of an ideal diatomic gas. An approximate procedure for determining the flow field a short distance downstream of the leading edge is also presented.
Date: June 1952
Creator: Kraus, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the errors in curve-fitting problems with an application to the calculation of stability parameters from flight data

Description: From Introduction: "It is shown in the body of this report that the solution to the error problem depends upon a more or less arbitrary definition, the only criterion as to the choice of the definition being the usefulness of the solution to which it leads. In this respect, it may be said of the method derived herein that it is not difficult to apply and appears to lead reasonable values of the errors."
Date: November 1952
Creator: Shinbrot, Marvin
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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Analytical and Experimental Investigation of Fully Developed Turbulent Flow of Air in a Smooth Tube With Heat Transfer With Variable Fluid Properties

Description: Note presenting tests to determine local heat-transfer coefficients and friction factors for fully developed turbulent flow of air in a smooth electrically heated tube with an inside diameter of 0.87 inch and a length of 87 inches. Testing occurred at high ratios of wall to fluid bulk temperatures. Results regarding the predicted temperature and velocity distributions, Nusslet numbers, friction factors, velocity distributions, and temperature distributions are provided.
Date: February 1952
Creator: Deissler, R. G. & Eian, C. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Application of Planing Characteristics to the Calculation of the Water-Landing Loads and Motions of Seaplanes of Arbitrary Constant Cross Section

Description: Note presenting the general equations governing the fixed-trim water landing of a straight-keel seaplane with a hull of arbitrary constant cross section in such a form that the landing motions and loads are expressed in terms of the steady planing characteristics of the seaplane.
Date: November 1952
Creator: Smiley, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of Transonic Similarity

Description: "From a review of the different similarity approaches to compressible potential flow, the meaning and limitations of transonic similarity are traced back to their origin. Although the main text deals with the quasi two-dimensional flow, special suggestions for the case of axisymmetric bodies are added in an appendix" (p. 1).
Date: April 1952
Creator: Busemann, Adolf
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Approach to the Prediction of the Frequency Distribution of Gust Loads on Airplanes in Normal Operations

Description: Note presenting the statistical concepts of random variables and probability distributions as applied to the sharp edge gust formula as a basis for the prediction of the gust-load history of airplanes in service operations. The results are applied in an example and the predicted load experience is compared with the available flight loads data for the case.
Date: April 1952
Creator: Press, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An approximate method for determining the displacement effects and viscous drag of laminar boundary layers in two-dimensional hypersonic flow

Description: From Summary: "A simplified approximate theory is presented by means of which the laminar boundary layer over an insulated two-dimensional surface may be calculated, a linear velocity profile being assumed, and an estimate made of its effect in changing the pressure distribution over the profile upon which the boundary layer is formed. Skin friction is also determined. Comparisons of results from this theory are made with experimental results at a Mach number of 6.86 and a Reynolds number of 98… more
Date: September 1952
Creator: Bertram, Mitchel H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An approximate method of determining the subsonic flow in an arbitrary stream filament of revolution cut by arbitrary turbomachine blades

Description: Report presenting a method to obtain a relatively quick approximate determination of the detailed subsonic flow of a nonviscous fluid past arbitrary turbomachine blades. The method is illustrated with examples of compressible flow in a turbine cascade and in a centrifugal compressor.
Date: June 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Prian, Vasily D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate Theory for Calculation of Lift of Bodies, Afterbodies, and Combinations of Bodies

Description: Note presenting an expression developed for the lift of a slender afterbody in terms of the "slender-body" approximate potential at the after end in conjunction with a suitably calculated value of the potential at the forward end. The same expression is used to compute the part of the interference lift generated by the presence of a neighboring body, due to the interference upwash. The lift is determined for a cone-cylinder body, a cylindrical afterbody of a slender wing-body combination, and t… more
Date: April 1952
Creator: Moskowitz, Barry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Auxiliary equipment and techniques for adapting the constant-temperature hot-wire anemometer to specific problems in air-flow measurements

Description: Report presenting the constant-temperature hot-wire anemometer amplifier and accessories have been developed to provide an instrument with wide frequency response, good stability, and ease of operation. Techniques are described using the equipment to study periodic phenomena such as surge, rotating stall, and wake surveys in centrifugal- and axial-flow compressors.
Date: November 1952
Creator: Laurence, James C. & Landes, L. Gene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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