A study of penetration of a liquid injectant into a supersonic flow /
by K.P. Horn, M.A. Kolpin, and R.E. Reichenbach.

Description

Main Author

Horn, Kenneth P., 1937-

Related Names

Reichenbach, Roy E., author.
Kolpin, Marc A., author.
United States. Air Force.
Space and Missile Systems Organization (U.S.)
Aerospace Corporation

Language(s)

English

Published

Los Angeles, California : Space and Missile Systems Organization, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967.

Subjects

Fluid dynamics.
Space vehicles > Space vehicles / Atmospheric entry.
Aerodynamics, Supersonic.

Summary

The paper reports a study of normal and lateral spray penetration for small diameter, high pressure, liquid jets issuing at an angle to a uniform supersonic stream. The experimental program described was carried out in a 4-in. by 4-in. blow down supersonic wind tunnel. The flow field is observed by means of a schlieren system, and the spray distribution is indicated by the light scattered by the liquid droplets. The data on normal penetration, in good agreement with data inferred from other investigations, indicate that a single-parameter correlation exists between the properly nondimensionalized penetration height and the injection pressure ratio. Injecting the coolant at a forward angle to the flow produces no substantial change in the penetration height. The data on lateral penetration show the spray width behind the jet to be proportional to the jet diameter with only a weak dependence on the injection pressure ratio. Analytical models proposed by previous investigators are critically examined in light of the results. No single model leads to a proper scaling law for both normal and lateral penetration. (Author).

Note

"October 1967."

Physical Description

33 pages : illustrations ; 28 cm.

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