Abstract
Experimental wind tunnel tests, conducted to reproduce the base flow past a space launcher during early ascent fight conditions, were numerically simulated by solving the steady Reynolds-averaged Navier–Stokes equations using two different versions of the Spalart–Allmaras model. The launcher model consisted of a cylinder with a circular cross section, an ogival nose, and a centered nozzle that issued a supersonic cold jet embedded in the external subsonic stream. A comparative analysis of the data obtained from the steady-state simulations and from the experimental tests indicated that the launcher base pressure was closely related to the turbulent shear stresses within the jet mixing layer; therefore, accurate modeling of the compressibility effects in the turbulent mixing layer plays an important role in improving the base drag estimates provided by the numerical simulations.
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.