Morphing MAC sections introduce asymmetric drag if not coordinated. The control system enforces symmetric morphing within 0.5% of mean radius to avoid yaw moments.
At Mach 1.2 (transonic), the fixed baseline (non-morphing) fuselage produces a wave drag coefficient (C_D_w = 0.045). The MAC fuselage, morphing to a Sears-Haack-like distribution tailored for Mach 1.2, reduces (C_D_w) to (40% reduction). At Mach 6.0, wave drag is reduced by 18% compared to a fixed hypersonic body. hypersonic vst mac
Lift coefficient in hypersonic regime (Newtonian theory): Morphing MAC sections introduce asymmetric drag if not
Supported by the AFOSR Hypersonic Vehicles Program (grant FA9550-XX-XXXX). You don't need the original plugin to sound like you have it
You don't need the original plugin to sound like you have it. Here is a cheat sheet to replicate Hypersonic patches using modern .
Variable sweep and tilt alter the aerodynamic center (AC). At low speed (Λ=20°, anhedral), AC is at 45% MAC. At hypersonic (Λ=75°, dihedral), AC shifts to 38% MAC. The flight computer uses a gain-scheduled LQR controller, adjusting elevator, canards (deployed only subsonically), and differential wing tilt for roll control.