Expressions for measuring the accuracy of approximate solutions to compressible flow through cascades of blades with examples of use
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Sinnette, John T↗
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Studies on von Karman's similarity theory and its extension to compressible flows : a critical examination of similarity theory for incompressible flows
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Lin, C C↗
Linearized Potential Theory of Propeller Induction in a Compressible Flow
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Davidson, Robert E↗
Prediction of losses induced by angle of attack in cascades of sharp-nosed blades for incompressible and subsonic compressible flow
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Kramer, James J↗
A Compressible-flow Plotting Device and Its Application to Cascade Flows
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Wesphal, Willard R↗
Theoretical and Experimental Analysis of One-dimensional Compressible Flow in a Rotating Radial-inlet Impeller Channel
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Lieblein, Seymour↗
On the form of the turbulent skin-friction law and its extension to compressible flows
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Donaldson, Coleman Dup↗
Theoretical and experimental investigation of the effect of tunnel walls on the forces on an oscillating airfoil in two-dimensional subsonic compressible flow
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Runyan, Harry L↗
Analysis of two-dimensional compressible-flow loss characteristics downstream of turbomachine blade rows in terms of basic boundary-layer characteristics
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Stewart, Warner L↗
Laminar separation over a transpiration-cooled surface in compressible flow
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Morduchow, Morris↗
General Treatment of Compressible Flow in Ejectors and Example of Its Application to Problem of Effect of Ejector Addition on Thrust of Jet-propulsion Units
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Ellerbrock, Herman H , Jr↗
A theoretical and experimental study of wind-tunnel-wall effects on oscillating air forces for two-dimensional subsonic compressible flow
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Runyan, Harry L↗
Investigation of Compressible Flow Mixing Losses Obtained Downstream of a Blade Row
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Stewart, Warner L↗
Compressible-flow solutions for the actuator disk
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Delano, James B↗
Linearized compressible-flow theory for sonic flight speeds
The partial differential equation for the perturbation velocity potential is examined for free-stream Mach numbers close to and equal to one. It is found that, under the assumptions of linearized theory, solutions can be found consistent with the theory for lifting-surface problems both in stationary three-dimensional flow and in unsteady two-dimensional flow. Several examples are solved including a three dimensional swept-back wing and two dimensional harmonically-oscillating wing, both for a free stream Mach number equal to one. Momentum relations for the evaluation of wave and vortex drag are also discussed. (author)
Heaslet, Max A↗
Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows
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Tetervin, Neal↗
Finite Span Wings in Compressible Flow
Equations are developed using the source distribution method for the velocity potential function and pressure on thin wings in steady and unsteady motion. Closed form solutions are given for harmonically oscillating wings of general plan form including the effect of the wing wake. Some useful examples are presented in an appendix for arrow, semielliptical, and hexagonal plan form wings.
WINGS, ELLIPTICAL↗
Behavior of fast moving flow of compressible gas in cylindrical pipe in presence of cooling
For compressible flow with friction in a cylindrical pipe the momentum, continuity, and heat-transfer equations are examined to determine whether an increase in Mach number ("thermal" Laval nozzle) is obtainable through heat conduction from the gas through the pipe walls. The analysis is based on the assumption that the wall temperature is negligibly small in comparison with the stagnation temperature of the gas. The analysis leads to a negative result. When the gas cooling is increased by also considering radiation to the wall, a limited region at high temperatures is obtained where Mach number increases were theoretically possible. Obtaining this condition practically is considered impossible.
FLOW, SUPERSONIC↗