swept-wing-aerodynamicslisted

# Swept Wing Aerodynamics (aerodynamics/high-speed/swept-wing-aerodynamics) Use when the task is wing sweep effects for high-speed flight: simple sweep theory, the cosine corrections on lift curve slope and section Mach, and the critical Mach number increase that sweep provides. ## Domain quick reference - Simple sweep theory: a yawed infinite wing behaves like an unswept wing at the velocity component normal to the leading edge. The sweep angle Lambda is the angle between the leading edge and the plane perpendicular to the freestream; all corrections below use cos(Lambda). - Effective (section) Mach: M_eff = M * cos(Lambda). The section sees a reduced Mach number, which is the mechanism behind the critical Mach increase. - Velocity components about the leading edge: normal M_n = M * cos(Lambda), tangential M_t = M * sin(Lambda). - Lift curve slope (simple sweep theory): a_swept = a0 * cos(Lambda), a0 the unswept section slope (2 * pi for thin sections). The lift-curve-slope leaf applies this as one step of its correction chain; this leaf owns the sweep-specific analysis and design forms. - Critical Mach: M_crit,swept = M_crit,0 / cos(Lambda), from the condition that the section reaches its critical Mach at the reduced effective Mach. A 35 degree sweep (cos = 0.819) raises a 0.7 section critical Mach to about 0.85. - Design form: Lambda = acos(M_crit,0 / M_crit,target) gives the sweep angle needed to reach a target critical Mach. - Range: the co