Abstract
This work presents computational studies of turbulent flow in a hypersonic wind-tunnel nozzle. The objective is t o validate several explicit compressibility and pressure-gradient corrections on prediction of the fiow properties. The computations were performed by solving the Reynolds-averaged NavierStokes equations with the turbulent viscous terms closed by four alternative eddy-viscosity models. The numerical algorithm is based on a finite volumc method using a space centered multistage RungeKutta scheme. It is found that there exist some considerable compressibility and pressure-gradient effects in the computed boundary layer. Compared with the models without such corrections, the modified models give an improved experimental agrecment. 2
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 call
