Study on γ-Reθ transition model for high speed flow
With the expansion of the airspace and velocity domain of high-speed(supersonic and hypersonic)aircraft,the accurate prediction of boundary layer transition is becoming more and more important for the aerodynamic performance design of high-speed aircraft.In the original γ-Reθ transition model,the empirical relation based on low-speed plate boundary layer transition is not suitable for high-speed boundary layer transition prediction.In order to solve this problem,the empirical relation of momentum thickness Reynolds number is improved based on DNS calculation data and wind tunnel test data.Examples of high-speed plate and sharp cone flow are selected to verify the empirical relationship.The results show that the original transition model will predict the transition onset position too early when predicting transition in high-speed boundary layer,while the improved transition model can give onset and extent of transition accurately,and is more suitable for high-speed boundary layer transition prediction.
boundarylayertransitionhigh speedtransition modelcompressibility correctionγ-Reθtransition modeltransition momentum thickness reynolds number
NETL
NSTL
万方数据
