This study investigated the vortex dynamic of wing canard delta configurations of the Saab JAS Gripen C-like model which create different wing planform than other fighters. | Vortex dynamic investigation of wing slotted gap of SAAB JAS Gripen C-like fighter International Journal of Mechanical Engineering and Technology IJMET Volume 10 Issue 03 March 2019 pp. 567-575. Article ID IJMET_10_03_058 Available online at http ijmet JType IJMET amp VType 10 amp IType 3 ISSN Print 0976-6340 and ISSN Online 0976-6359 IAEME Publication Scopus Indexed VORTEX DYNAMIC INVESTIGATION OF WING SLOTTED GAP OF SAAB JAS GRIPEN C-LIKE FIGHTER Sutrisno Department of Mechanical and Industrial Engineering Faculty of Engineering Universitas Gadjah Mada Yogyakarta Indonesia 55281 Setyawan Bekti Wibowo Department of Mechanical and Industrial Engineering Faculty of Engineering Universitas Gadjah Mada Yogyakarta Indonesia 55281 Sigit Iswahyudi Department of Mechanical and Industrial Engineering Faculty of Engineering Universitas Gadjah Mada Yogyakarta Indonesia 55281 Department of Mechanical Engineering Faculty of Engineering Universitas Tidar Magelang Indonesia 56116 Tri Agung Rohmat Department of Mechanical and Industrial Engineering Faculty of Engineering Universitas Gadjah Mada Yogyakarta Indonesia 55281 ABSTRACT Canard fighters generally configured with wing canard-deltas and would generate an airflow phenomenon producing vortex cores and lifts. The lift distribution would stall at a high angle of attack AoA . This study investigated the vortex dynamic of wing canard delta configurations of the Saab JAS Gripen C-like model which create different wing planform than other fighters. The slotted leading edge of the Gripen would develop a strong vortex core on the outer wing on the same direction with the spin of wing vortex the outer core would drag the inner vortex core and strengthened. Consequently the vortex core streamlined in a leading edge of the wing would begin to detach resulting rolled-up vortices in the wing leading edge followed by a solid laminar stream which tends to curl out. The trailing edge of the wing tended to .
