The invention provides an aerodynamic parameter measurement method for an aircraft, which is used for measuring key data in three aspects of an airflow angle, dynamic pressure and an aerodynamic force. The method comprises the following steps: the airflow angle is calculated, the airflow angle is acquired through an embedded atmospheric data sensing system or a trajectory reconstruction mode, andthe above two modes are in mutual backup; the dynamic pressure is calculated, data are outputted according to pressure sensors configured by the embedded atmospheric data sensing system on the aircraft, the dynamic pressure is calculated and input is provided for calculating an aerodynamic coefficient; and the aerodynamic coefficient is calculated, the output is measured by using accelerometers, the aerodynamic force, that is, the lift force and the drag force, is calculated, and in combination of the dynamic pressure data, an aerodynamic calculation formula is used to directly determine the lift force coefficient and the drag force coefficient of the aircraft. The embedded atmospheric data sensing system is equipped with two sets of pressure sensors and multiple sets of accelerometers andgyroscopes. A hardware redundancy design and an algorithm redundancy design are adopted, and the aerodynamic parameter measurement reliability is improved.