Abstract
Two high efficient intakes – 3D and traditional 2D consisted of supersonic inlet and subsonic large curvature diffuser were developed for supersonic business aircraft with M =1.6 cruise flight. Preliminary deceleration of incoming airflow and boundary layer control (BLC) in case of 3D inlet are provided by swept wedge placed in front of inlet due to the forming transverse pressure gradient. In case of 2D inlet bypass of BL is provided by installation of the inlet on bleed wedge of some height. Further compression is realized in a system of 3-D shocks with terminal normal one. Numerical modeling based on solution of 3-D Navier-Stokes equations allowed obtaining the results of inlet and subsonic diffuser flowing under the boundary layer suction in a throat at throttle modes under M=0.8-1.8. Results of calculation confirmed flow stability at 1.5-4 fold increased pressure in subsonic diffuser outlet section in comparison with external free stream pressure. It was received that using the BLC the total pressure recovery coefficient grows up to = 0.89...0.97 for considered M range. Drag evaluations of considered inlets with taking into account of additive and wave drag components and also wave drag of bleed wedge of 2D inlet resulted in approximately the same compression efficiency, but summary drag of 3D inlet is less by a factor of 1,5-3.5 times in comparison with 2D inlet drag at M =0.8-1.8 range.
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 callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
