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.
Turbulence Modeling of Base Drag on Launcher in Subsonic Flight
Journal of Spacecraft and Rockets ; 51 , 5 ; 1673-1680
2014-09-12
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Base-Pressure Experimental Investigation on a Space Launcher in Subsonic Regime
Online Contents | 2013
|AIAA | 1965
|