The lift slope for a swept wing in a compressible flow, denoted as “acomp,” is an aerodynamic parameter that characterizes the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for a swept wing operating in conditions where compressibility effects, such as changes in air density and the presence of shockwaves, are significant. Swept wings are commonly used in high-speed aircraft and are designed to delay the onset of transonic and supersonic flow regimes. In these conditions, understanding how lift varies with angle of attack is crucial for aircraft performance and stability.
- Lift slope for a swept wing in a compressible flow (acomp) in per rad
- Lift slope for an infinite wing in an incompressible flow (a0) in per rad
- Freestream Mach number (M∞)
- Swept angle (Λ) in rad
- Aspect Ratio (AR)