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