Zero point error processing method for wind tunnel test data of symmetrical aircraft

The invention provides a zero point error processing method for the wind tunnel test data of a symmetrical aircraft. The method comprises a step of selecting a basic flight attitude with symmetry as astandard state of a zero point of the wind tunnel test data, a step of determining aerodynamic force resultant force in a cross section of the aircraft and a direction and a size of a resultant moment when a synthetic attack angle is zero, a step of decomposing the resultant force in the cross section of the aircraft and the resultant moment under a rotating body shaft system to obtain new valuesof corresponding force and moment, a step of obtaining new values of axial force and rolling moment zero point through algebraic averaging, a step of obtaining a difference between old and new values, a step of adding the above difference to old data changing with the synthetic attack angle to obtain new data and realizing the overall translation of a curve for matching use. According to the method, starting from the phys