Download or read book Experimental Investigation of the Pressure Distribution about a Yawed Circular Cylinder in the Critical Reynolds Number Range written by William J. Bursnall and published by . This book was released on 1951 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made of the pressure distribution about a circular cylinder at various angles of yaw. The results indicate that the flow and force characteristics in the range of Reynolds number based on the normal velocity component near and above critical cannot be determined only by the component of flow normal to the cylinder axis. Localized regions of laminar separation which were present in the 0 degrees yaw case in the supercritical Reynolds number range became less distinct as the yaw angle was increased and completely disappeared for yaw angles from 45 and 60 degrees.
Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 1026 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Note written by and published by . This book was released on 1951 with total page 460 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1970 with total page 610 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of Vehicle Bodies at Crosswind Conditions in Ground Proximity written by Kalman J. Grunwald and published by . This book was released on 1970 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of force tests was conducted on unpowered, high-speed ground-vehicle model configurations to provide information on shapes of this type very near the ground. Of particular interest were the crosswind effects on the aerodynamic forces and moments of the six models tested. These tests were conducted over the moving-belt ground plane in the 17-foot (5.18-m) test section of the Langley 300-MPH 7-by 10-foot tunnel at free-stream dynamic pressure values of 10 lb/ft2 (478.8 N/m2). The results indicate that the half-circle configuration is desirable because of the low rolling moments it experienced; however, it did have higher lift values than the other configurations and, from a utility standpoint, could be impractical. The half-circle configurations with extended sides may make good compromise configurations. All the ground-simulation techniques employed -moving ground belt, fixed ground belt, and image model -gave reasonable representations of the overall aerodynamic trends.
Download or read book List of Technical Notes 1947 1953 written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Method of Matching Components and Predicting Performance of a Turbine propeller Engine written by Alois T. Sutor and published by . This book was released on 1951 with total page 706 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical expressions are derived to show the geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle for a gas-turbine engine. For a known compressor performance map, a matching method is described to show some of the design compromises that must be made when the components are to be combined into a turbine-propeller engine. A method of predicting engine performance for a range of operating conditions from known component maps is presented. An illustrative example of the matching method and the performance analysis is presented, showing some of the practical limitations of engine operation.
Download or read book A Method for Calculating the Subsonic Steady state Loading on an Airplane with a Wing of Arbitrary Plan Form and Stiffness written by W. L. Gray and published by . This book was released on 1953 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1953 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Comparison of the Experimental and Theoretical Distributions of Lift on a Slender Inclined Body of Revolution at M written by Edward W. Perkins and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An investigation of the pressure distribution for a body of revolution, consisting of a 33-1/3-caliber (5.75 fineness ratio) tangent ogival nose and a cylindrical afterbody, has been made for an angle-of-attack range of 0° to 35.5° at a Mach number of 1.98 and a Reynolds number of approximately 0.5 x 106m based on body diameter. Comparisons of the theoretical and experimental pressure distributions are made to show the nature of the effects of both viscosity and cross-flow compressibility. The experimental load distributions are compared with those predicted by the method suggested in NACA RM A9I26 which includes an approximate method for taking into account the effects of viscosity on the lift distribution.
Download or read book An Experimental Investigation of Regions of Separated Laminar Flow written by Donald E. Gault and published by . This book was released on 1955 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from an investigation of regions of separated flow caused by separation of the laminar boundary layer (laminar-separation "bubbles"). The investigation was undertaken to obtain measurements which would define a large number of these bubbles for a wide range of Reynolds numbers and pressure gradients. In this manner, existing physical interpretations of the flow along a bubble could be studied in greater detail than in the past and, at the same time, it was hoped that the data would provide further insight into the conditions which control the occurrence and extent of a bubble.
Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Report written by and published by . This book was released on 1958 with total page 1138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 1200 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1951 with total page 1376 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Analysis of Total pressure Loss and Airflow Distribution for Tubular Turbojet Combustors with Constant Annulus and Liner Cross sectional Areas written by A. J. Eggers and published by . This book was released on 1958 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt:
