Flow-direction measurement with fixed-position probes in subsonic flow over a range of Reynolds numbers.
Fixed position pressure probe for measuring subsonic flow direction over range of Reynolds number, Mach number and flow angle
Dudzinski, T. J.↗
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Results for “FLOW - STABILITY”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Two-directional-flow, axial-motion-joint flow liner
Flow liner eliminates high-cycle fatigue in ducts carrying cryogenic fluids. It is capable of handling two-directional, high-velocity cryogenic liquid flow with a 3-inch axial motion without binding within a 25-inch length.
Bissing, L. L.↗
Calculations of the Flow of Natural Gas Through Critical Flow Nozzles
Calculation of natural gas flow through critical flow nozzles
Johnson, R. C.↗
Approximation for distribution of flow properties in the angle-of-attack plane of conical flows
Approximation for distribution of flow properties in angle of attack plane of conical flows
Cleary, J. W.↗
Calculations of the flow of natural gas through critical flow nozzles
Mass flow rate calculation of methane and natural gas mixtures through critical flow nozzles
Johnson, R. C.↗
Entrance flows of polymeric materials - Pressure drop and flow patterns
Polymeric materials flow at tube entrance, discussing pressure drop and flow birefringent patterns at tapered and sharp entrances
Bogue, D. C.↗
Effect of simulated downstream flow blockage doors on the performance of an axial-flow fan rotor
Simulating downstream flow blockage doors in bypass air duct of turbofan engine with axial flow fan rotor
Osborn, W. M.↗
Flow-induced vibration of bellows with internal cryogenic fluid flows Interim technical report
Flow-induced vibration of bellows with internal cryogenic fluid flows
Bass, R. L., III↗
Real gas effects in the flow of methane and natural gas through critical flow nozzles
Equations for mass flow of methane and natural gas mixtures through critical flow nozzles, including real gas effects
Johnson, R. C.↗
Computer program describing turbine aerodynamic requirements, approximate external blade geometries, and coolant flow requirements for a two stage axial flow turbine
Computer program to generate turbine aerodynamic requirements, approximate external blade geometries, and coolant flow requirements for two stage axial flow turbine
Evans, D. G.↗
Experimental study of the effect of inlet conditions on the flow and containment characteristics of coaxial flows
Effect of inlet conditions on flow and containment characteristics of coaxial flows for gas core nuclear rockets
Johnson, B. V.↗
Flow equation for porous plug and capillary tube flow restrictors
Development of flow measuring apparatus for determining low flow performance of resistojet thruster is discussed. Diagram of test equipment is presented. Operation of test equipment is described and numerical relationships are explained.
Davis, W. S.↗
Possible flow regimes of adiabatic one-dimensional compressible fluid flow with friction in convergent and divergent ducts.
An analytical solution for the compressible one-dimensional flow in convergent and divergent ducts with friction is obtained. It is found that a nondimensional parameter, N, can be formed using the friction factor, duct half-angle and the ratio of specific heats of the gas. Seven flow regimes are describable with the solution, based on certain bounds on the magnitude of N. The regimes are discussed and corollary data are presented graphically.
Shouman, A. R.↗
A source flow characteristic technique for the analysis of scramjet exhaust flow field
The factors which influence the design and selection of a nozzle for a hypersonic scramjet are described. A two dimensional second-order characteristic procedure capable of analyzing the aerodynamic performance of typical nozzle configurations is presented. Equations of motion governing the two dimensional, axisymmetric, or axially expanding inviscid flow of a gas mixture, with frozen chemistry, are provided. Diagrams of the flow conditions for various configurations are included.
Delguidice, P.↗
Flow processes in overexpanded chemical rocket nozzles. Part 1: Flow separation
An investigation was made of published nozzle flow separation data in order to determine the parameters which affect the separation condition. A comparison of experimental data with empirical and theoretical separation prediction methods leads to the selection of suitable equations for the separation criterion. The results were used to predict flow separation of the main space shuttle engine.
Schmucker, R. H.↗
An improved source flow characteristic technique for the analysis of scramjet exhaust flow fields
The process is discussed of designing a nozzle for a hypersonic airbreathing vehicle which involves a complex study of the inter-relationship among many parameters: internal-external expansion, vehicle lift, drag, pitching moments, and structural and weight limitations. The source flow characteristic approach to the design process was extended and improved, and streamline interpolation procedure was incorporated. All characteristic and boundary calculations were made compatible with frozen, equilibrium and ideal gas thermodynamic options, while slip surface calculations (cowl interaction) were extended to underexpanded flow conditions. Since viscous forces can significantly influence vehicle forces, pitching moments and structural/weight considerations, a local integration via flat plate boundary layer skin friction and heat transfer coefficients was included. These effects are calculated using the Spalding and Chi method, and all force and moment calculations are performed via integration of the local forces acting on the specified vehicle wetted areas.
Delguidice, P. D.↗
A new flow model for highly separated airfoil flows at low speeds
An analytical model for separated airfoil flows is presented which is based on experimentally observed physical phenomena. These include a free stagnation point aft of the airfoil and a standing vortex in the separated region. A computer program is described which iteratively matches the outer potential flow, the airfoil turbulent boundary layer, the separated jet entrainment, mass conservation in the separated bubble, and the rear stagnation pressure. Separation location and pressure are not specified a priori. Results are presented for surface pressure coefficient and compared with experiment for three angles of attack for a GA(W)-1, 17% thick airfoil.
Zumwalt, G. W.↗
Semidirect computation of three-dimensional viscous flows over suction holes in laminar flow control surfaces
A summary is given of the attempts made to apply semidirect methods to the calculation of three-dimensional viscous flows over suction holes in laminar flow control surfaces. The attempts were all unsuccessful, due to either (1) lack of resolution capability, (2) lack of computer efficiency, or (3) instability.
Roache, P. J.↗