Aerodynamic forces, such as lift and drag, on an object are directly proportional to the dynamic pressure of the surrounding fluid. The formulas are [latex]L = C_L \cdot q \cdot A[/latex] and [latex]D = C_D \cdot q \cdot A[/latex], where [latex]C_L[/latex] and [latex]C_D[/latex] are the dimensionless lift and drag coefficients, [latex]q[/latex] is the dynamic pressure, and [latex]A[/latex] is a reference area.
