Abstract
The influence of underexpanded jets on a supersonic afterbody flowfield is investigated using computational techniques. The thin-shear-layer formulation of the compressible, Reynolds-averaged, Navier-Stokes equations is solved using a time-dependent, implicit numerical algorithm. Solutions are obtained for supersonic flow over an axisymmetric conical afterbody containing a centered propulsive jet where the freestream Mach number is 2.0 and the jet exit Mach number is 2.5. Exhaust-jet static pressures are considered in the range of 2 to 9 times the freestream static pressure and with nozzle-exit half-angles from 15 to 43 deg. Comparisons are made with experimental results for base pressure, separation distance, afterbody pressure distribution, and flowfield structure. Although good quantitative agreement with experimental separation distance and base pressure level is not observed, the parametric trends induced by exhaust-jet pressure level and nozzle-exit angle are well predicted, as well as the flowfield details in the vicinity of the afterbody and in the exhaust plume.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: 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.