SIMULASI AERODINAMIKA SAYAP DOUBLE DELTA 70/50 DENGAN PENGARUH MISIL PADA TIP

• Main Author: Nurrahman Besar, Muhammad
• Format: Final Project
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/39017
• Institution: Institut Teknologi Bandung

Fighter aircraft designed to fly at high speed until the supersonic regime. However to achieve the supersonic regime, the plane must pass through subsonic regime, then the transition to supersonic into transonic regime. In this transonic regime the plane doing cruise phase and combat phase especially at critical mach number. In the combat phase, a good ability to maneuver is necessary, and it all can be achieved where there is also good aerodynamic performance at high angles of attack. The wings are commonly used on the fighter aircraft is a delta-wing, because it can reach supersonic regime well, and delta wings are known to have good performance at high angles of attack because it can achieve a high stall angle. This ability was obtained due to the high angle of attack delta wings produce lift not because of camber on the wing chord, but the delta wing can produce a strong vortex flow over the wing surface, so that the delta wing's lift at high angles of attack. Of course when flying, combat aircraft will carry weapons such as missiles were placed under or beside the wings wing. And this will inevitably impact on the flow around the wings and missiles. So the major goal of this thesis is to capture the phenomenon of vortex flow on delta wings, and also see what effect if added the missile at the tip of the wings. This research was carried out by simulation using the CFD software FLUENT with the RANS method.