![]() Fighter aircraft with their wide variety of speeds and angles of attack will rarely profit from using them. Supercritical airfoils work best in a narrow Mach and angle of attack range and are used for transsonic designs (flight Mach number between 0.7 and 1.0). In case of the F15, thickness varies between 6.6% at the root and 3% at the tip. Typical sections use a relative thickness between 4% and 6%. ![]() Delta wing aircraft enhance this nose suction by cambering the outboard leading edge ( conical camber).Ĭommon to all supersonic wings is their minimization of wing thickness, because wave drag will grow with the square of thickness. This produces nose suction which is very helpful to keep drag down. Those airfoils are chosen because flow around them at supersonic flight speed is still heavily influenced by subsonic flow characteristics* as long as wing sweep allows for a subsonic leading edge. As you can see, the F-16 uses camber throughout, indicated by the 0.2 design lift coefficient of the airfoil, while the F-15 uses an uncambered root airfoil. This information is from The Incomplete Guide to Airfoil Usage by Dave Lednicer. General Dynamics F-16 NACA 64A204 NACA 64A204 McDonnell Douglas F-15 NACA 64A006.6 NACA 64A203 Normally, supersonic fighter wings for which airfoil information is published use a very thin NACA 6-series section with very little camber, such as Aircraft root airfoil tip airfoil
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