Measuring and testing – Wind tunnel: aerodynamic wing and propeller study
Patent
1982-05-14
1984-02-14
Woodiel, Donald O.
Measuring and testing
Wind tunnel: aerodynamic wing and propeller study
73432SD, G01M 900
Patent
active
044308906
ABSTRACT:
A method of studying steady and unsteady supersonic gas flow using a two layer hydraulic analogy technique. The method simulates the specific heat ratio of the gas. Two layers of immiscible liquids having different densities and thicknesses are held in a shallow container. The densities are chosen and the layer thicknesses are adjusted to simulate the specific heat ratio of the gas. A model of a device to be studied is submerged in the liquid. Relative flow is caused to occur between the model and liquid simulating steady flow. The depth of the lower layer during the period of relative flow is measured and is analogous to steady state gas flow characteristics. For studying unsteady flow two bodies of liquids each having two layers of liquids of densities chosen, and lower layer thicknesses adjusted to simulate the specific heat ratio of the gas and to simulate a high and low pressure across a gas system, are held in a container separated by a removable gate. Flow is caused to occur from the high to low pressure liquid body simulating unsteady flow. The depth of the lower layers during the period of flow is analogous to unsteady gas flow characteristics.
REFERENCES:
Hoyt, Applied Mechanics Review, vol. 15, No. 6, pp. 419-423, Jun. 1962.
Shapiro, Physical Measurement in Gas Dynamics and Combustion, Princeton Uersity Press, pp. 309-321, 1954.
Beers R. F.
Breh D. J.
The United States of America as represented by the Secretary of
Walden K. E.
Woodiel Donald O.
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