Lift slope for an infinite wing in a subsonic compressible flow Calculator

The lift slope for an infinite wing in a subsonic compressible flow, denoted as “a0,comp,” is a fundamental aerodynamic parameter that characterizes the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for an infinite wing in subsonic, compressible airflow. The lift slope a0,comp is significant in aerodynamics because it quantifies how the lift of a wing or airfoil changes as the angle of attack is adjusted. It is a measure of the wing’s ability to generate lift efficiently. 

  • Lift slope for an infinite wing in a subsonic compressible flow (a0,comp) in per rad
  • Lift slope for an infinite wing for incompressible flow (a0) in per rad
  • Freestream Mach number (M∞)

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