Application #21. Supersonic Retro-Propulsion
Simulation of a late 1960s Jarvinen and Adams wind tunnel entry in support of the Entry Technology Development Program.
Mach 2 flow from the right forms a bow shock around the wind tunnel model (in white), which is firing an air jet into the oncoming flow as a means to decelerate during atmospheric entry. Jet entrainment causes a large, annular recirculation region to engulf the entire forebody and, combined with the plume, creates a large effective body size—see the dividing streamline between the jet flow and the post-bowshock flow. The balance between the jet terminal shock, the intermediate stagnation point, and the bow shock is very sensitive to grid resolution. Additionally, the overall shear-layer/barrel-shock/plume structure is highly dependent on the turbulence model (SST in this case).
Simulations performed by Bil Kleb and Jan Renee-Carlson of NASA Langley and Ashley Korzun and Chris Cordell of Georgia Tech.
This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.