Title: Scheme and Inlet Performance of Supersonic Business Aircraft
Abstract: Developed and chosen is a configuration of high efficient inlet prototype including supersonic inlet and subsonic large curvature diffuser for supersonic business aircraft with M∞=2 cruise flight. Preliminary deceleration of incoming airflow and boundary layer control are provided by means of a swept wedge placed in front of inlet due to forming pressure transverse gradient. Further compression is realized in a system of 3D shocks with terminal normal one. Numerical modeling based on solution of 3-D Navier-Stokes equations allowed obtaining the results of inlet flow at throttle modes under M∞=2 and confirmed flow stability at 5..7fold increased pressure in subsonic diffuser outlet section in comparison with external free stream pressure. Parametric flow calculations are organized and inlet throttle performance is determined with subsonic diffuser at M∞=2 and boundary layer suction in a throat. It is received that using the boundary layer control with air suction rate Gsuct/Ginlet = 2…5% total pressure recovery coefficient σ grows up to σ = 0.89…0.91. Throttle performance and drag of 3-D inlet have more advantages in comparison with ones of traditional 2-D inlet.
Publication Year: 2008
Publication Date: 2008-07-21
Language: en
Type: article
Indexed In: ['crossref']
Access and Citation
Cited By Count: 4
AI Researcher Chatbot
Get quick answers to your questions about the article from our AI researcher chatbot