Study of shock formation around various wing shapes in supersonic flow using colour schlieren method

Study of shock formation around various wing shapes in supersonic flow using colour schlieren method
Author(s):
Pavan Kumar Mekala, Naga Manikanta Kommanaboina, sai krishna Pabba, Akash Chanda, Adithya Reddy Ettireddy, Veeranjaneyulu Latchiboyina
ISSN:
2349-6002
Cite This Article:
Study of shock formation around various wing shapes in supersonic flow using colour schlieren method, International Journal of Innovative Research in Technology(www.ijirt.org) ,ISSN: 2349-6002 ,Volume 6 ,Issue 2 ,Page(s):224-227 ,July 2019 ,Available :IJIRT148503_PAPER.pdf
Keywords:
Shock wave, supersonic wind tunnel, computer aided design, schlieren method, BOS method, stainless steel, sweep angle, straight angle.
Abstract
Summary of the project is to be finding the effects of different wing shapes and size in supersonic flight. The wing shapes include delta, double delta and other some shapes. By using schlieren method and BOS method in softwares Ansys and designed in Catia. Using common fuselage size and shape according to blockage ratio of supersonic wind tunnel test section and various wing shapes.
Article Details
Unique Paper ID: 148503 Publication Volume & Issue: Volume 6, Issue 2 Page(s): 224 - 227
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International Journal of Innovative Research in Technology