Abstract
An analysis for predicting the performance of side-exhausting scarfed propulsive nozzles is presented. Nozzles of this type consist of a conventional axisymmetric nozzle followed by a scarfed conical extension. They are employed in situations where the exhaust jet must exit through the side of a missile. The flowfield model assumes that the flow within the nozzle is axisymmetric, and that the overall nozzle pressure ratio is high enough to preclude shock waves or flow separation at the nozzle exit. The flowfield is calculated by the method of characteristics. The oblique shock wave that emanates from the junction of the nozzle and the nozzle extension is fitted discretely and tracked through the flowfield. The forces and moments acting on the scarfed nozzle and the missile are determined. The results of an extensive parametric study are presented. Comparisons with experimental measurements are presented to verify the analysis.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
