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Published October 1964 | Published
Journal Article Open

Secondary Injection of Gases into a Supersonic Flow


The flow field around the injection port for secondary injection of a gas normal to a supersonic stream has been studied in a series of wind-tunnel experiments. The experiments were conducted at freestream Mach numbers of 1.38 to 4.54. Gaseous nitrogen, argon, and helium were used as injectants. New information concerning pressure fields, concentration fields, and shock shapes was obtained. A scale parameter has been calculated, based on a simple, inviscid model of the flow field. This scale parameter gives a good general correlation of the data. Use of this scale parameter allows prediction of a simple scaling law for the side forces generated by secondary injection. This side-force scaling law is in approximate agreement with existing rocket motor test results.

Additional Information

© 1964, by the American Institute of Aeronautics and Astronautics. Presented as Preprint 64-110 at the AIAA Solid Propellant Rocket Conference, Palo Alto, Calif., January 29-31, 1964; revision received July 10, 1964. This research work was supported by the Daniel and Florence Guggenhiem Jet Propulsion Center of the California Institute of Technology and by NASA Contract No. NAS 7-100, through the Solid Rockets Section of the Jet Propulsion Laboratory, California Institute of Technology.

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