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AERADE Reports Archive Search results for: axially 65 records found ... displaying 41 to 50 An analysis of base pressure at supersonic velocities and comparison with experiment Chapman, Dean R. In the first part of the investigation an analysis is made of base pressure in an inviscid fluid, both for two-dimensional and axially symmetric flow. It is shown that for two-dimensional flow, and also for the flow over a body of revolution with a cylindrical sting attached to the base, there are an infinite number of possible solutions satisfying all necessary boundary conditions at any given free-stream Mach number. For the particular case of a body having no sting attached only one solution is possible in an inviscid flow, but it corresponds to zero base drag. Accordingly, it is concluded that a strictly inviscid-fluid theory cannot be satisfactory for practical applications. An approximate semi-empirical analysis for base pressure in a viscous fluid is developed in a second part of the investigation. The semi-empirical analysis is based partly on inviscid-flow calculations. Analytical investigation of flow through high-speed mixed-flow turbine Stewart, Warner L. An analysis was made of the flow trough a high-speed mixed-flow turbine based on axially symmetric conditions. The calculated weight flow was lower than that used in the two-dimensional design. The rotor could be redesigned to increase the weight flow and a flow and alleviate undesirable pressure gradients at the expense of increased rotor blade stresses. Flow Separation Ahead of a Blunt Axially Symmetric Body at Mach Numbers 1.76 to 2.10 W. E. Moeckel (Lewis Flight Propulsion Laboratory, Cleveland, Ohio) No Abstract Available Theoretical wave drags and pressure distributions for axially symmetric open-nose bodies John R. Jack The variations of pressure distributions and coefficients of wave drag with fineness ratio, Mach number, and area ratio were calculated from linearized theory for a variety of open- nose bodies of revolution at zero angle of attack. Linearized supersonic axially symmetric flow about open-nosed bodies obtained by use of stream function Franklin Moore The use of Stokes' stream function for axially symmetric problems in linearized supersonic flow is discussed. The computation of streamlines away from the body is shown to be facilitated by solving the stream-function problem rather than the potential problem. An analysis of base pressure at supersonic velocities and comparison with experiment Dean R. Chapman In the first part of the investigation an analysis is made of the base pressure in an inviscid fluid, both for two-dimensional and axially-symmetric flow. It is shown that for two-dimensional flow, and also for the flow over a body of revolution with a cylindrical sting attached to the base, there are an infinite number of possible solutions satisfying all necessary boundary conditions at any given free-stream Mach number. For the particular case of a body having no sting attached only one solution is possible in an inviscid flow, but it corresponds to zero base drag. Accordingly, it is concluded that a strictly inviscid-fluid theory cannot be satisfactory for practical applications. Since the exact inviscid-fluid does not adequately describe the conditions of a real fluid flow, an approximate semi-empirical second part of the investigation. The semi-empirical theory is based partly on inviscid-flow calculations, and is restricted to airfoils and bodies without boattailing. In this theory an attempt is made to allow for the effects of Mach number, Reynolds number, profile shape, and type of boundary-layer flow. The results of some recent experimental measurements of base pressure in two-dimensional and axially-symmetric flow are presented for purposes of comparison. Some experimental results also are presented concerning the support interference effect of a cylindrical sting, and the interference effect of a reflected bow wave on measurements of base pressure in a supersonic wind tunnel. Application of radial-equilibrium condition to axial-flow compressor and turbine design Wu, Chung-Hua Wolfenstein, Lincoln Basic general equations governing the three-dimensional compressible flow of gas through a compressor or turbine are given in terms of total enthalpy, entropy, and velocity components of the gas. Two methods of solution are obtained for the simplified, steady axially symmetric flow; one involves the use of a number of successive planes normal to the axis of the machine and short distances apart, and the other involves only three stations for a stage in which an appropriate radial-flow path is used. Methods of calculation for the limiting cases of zero and infinite blade aspect ratios and an approximate method of calculation for finite blade aspect ratio are also given. In these methods, the blade loading and the shape of the annular passage wall may be arbitrarily specified. Application of radial-equilibrium condition to axial-flow compressor and turbine design Chung-Hua Wu, Lincoln Wolfenstein Basic general equations governing the three-dimensional compressible flow of gas through a compressor or a turbine are given in terms of velocity components, total enthalpy, and entropy. These equations are used to determine the radial motion of gas through an axial-flow compressor or a turbine and the corresponding effect on the radial variations of the state of gas between successive blade rows in the case of steady, axially symmetrical flow. Method for evaluating from shadow or Schlieren photographs the pressure drag in two-dimensional or axially symmetrical flow phenomena with detached shock Antonio Ferri A method has been developed for evaluating from shadow or schlieren photographs the pressure drag of axially symmetrical bodies at zero angle of attack or of two-dimensional bodies producing detached shock. Approximate method for predicting form and location of detached shock waves ahead of plane or axially symmetric bodies Moeckel, W E No Abstract Available |
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