Abstract
When an imaging-guided vehicle is flying at hypersonic speed, its optical window faces severe aerodynamic heating. A Mach 3 supersonic nozzle was designed to produce a layer of cooling gas above the optical window. However, the introduction of cooling film will make the aero-optical effects more complicated, and ultimately affect the imaging quality of the aircraft. Optical properties of the supersonic cooling film were measured by background oriented schlieren (BOS) with 3 different total pressures and 3 different observation angles. Experimental results showed that the current design is incapable to provide uniform density distribution at the cooling film nozzle outlet. It was found that higher total pressure produced more severe aero-optical effects, and the aero-optical effects correspond to 81◦ observation angle were slightly stronger than those correspond to 90◦ and 99◦.
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.
