Rolled-up vortex dynamic numerical studies of bird's-body-type fighter

This paper elucidates the study of the vortex dynamics of a fighter with a birds body type fuselage (BBTF), at constant canard deflection angle, using computational fluid dynamics (CFD).
Nội dung trích xuất từ tài liệu:
Rolled-up vortex dynamic numerical studies of birds-body-type fighterInternational Journal of Mechanical Engineering and Technology (IJMET)Volume 10, Issue 03, March 2019, pp. 304-316. Article ID: IJMET_10_03_032Available online at http://www.iaeme.com/ijmet/issues.asp?JType=IJMET&VType=10&IType=3ISSN Print: 0976-6340 and ISSN Online: 0976-6359© IAEME Publication Scopus Indexed ROLLED-UP VORTEX DYNAMIC NUMERICAL STUDIES OF BIRDS-BODY-TYPE 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. Department of Mechanical Engineering, Vocational College, Universitas Gadjah Mada, Yogyakarta, Indonesia 55281. Sigit Iswahyudi Department of Mechanical and Industrial Engineering, Faculty of Engineering, Universitas Gadjah Mada, Yogyakarta, Indonesia 55281Department 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 The fuselage type of a fighter greatly influences the aerodynamic characteristic especially in vortex generating which determines the agility and maneuverability. This paper elucidates the study of the vortex dynamics of a fighter with a birds body type fuselage (BBTF), at constant canard deflection angle, using computational fluid dynamics (CFD). The CFD study employs Q-criterion to probe vortices and structured logarithmic grid to maintain the micro-gridding effectiveness of the turbulent boundary layer. The flow visualizations are coupled with shear-wall streamline to produce complete vortex dynamic pattern. The results show that the configurations of the bulky-head aerodynamic, the body, canard and main wing of the BBTF affect vortex core trajectories on the blended-body-main wing and the canard that very close to the surface, which gives higher coefficients of lift, of order 1.40 at a high angle of attacks causing its high agility and maneuverability. The numerical calculations show that there is no negative surface pressure distribution (SPD) on vertical walls near the canard and wings of BBTF fighters. On other design, negative SPD on vertical walls waste a lot of fuel energy, including weakening the lift coefficient. http://www.iaeme.com/IJMET/index.asp 304 editor@iaeme.com Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung Rohmat Keywords: Fighter aircraft, CFD, vortex dynamic mechanism; fuselage effect; Q- criterion. Cite this Article Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung Rohmat, Rolled-Up Vortex Dynamic Numerical Studies of Birds-Body-Type Fighter, International Journal of Mechanical Engineering and Technology, 10(3), 2019, pp. . 304-316. http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=10&IType=31. INTRODUCTIONThe difference between a passenger plane and a fighter is the assumption of its flight speedoperation. Passenger aircraft are characterized by subsonic to transonic flying speeds, whilefighter aircraft preferably work reliably at supersonic speeds. So, the configuration of thoseplanes is different. The passenger plane has a low swept wing, so that the airflow around theplane is of a straight flow with little mixed with the rolling vortices, whereas on fighteraircraft with medium to the high swept wing, so the airflow around the fighter is more mixedand mostly dominated by rolled-up vortices. On passenger aircraft, the wind velocity energy is converted into the high-velocity flow toform a low-pressure zone above the wing airfoil surface to create lift force on the wing, tail,and control surfaces as the role of vortex swirls, in passenger aircraft, is lesser. Compared tocombat aircraft, the force developments are more dominated by the role of vortices, yetstraight flow is still significant. The role of the vortices start above the wing brought up by therolled-up-vortex effect, which also then plays a lot on the canard or leading edge extension(LEX) of the fighters. At present, the widely known fighter flow energy transmission is the rolled-up vortex(RuV) effect, such as above the wings, LEX, and canard. The fuselage effects are still notwell known, mainly due to the effects of the blended wing-body, the ...