Airplane-centered coordinate systems originate at a fixed point in the vehicle, called the reference point. The choice of the reference point is arbitrary, but it must be fixed point. In particular, the center of gravity (CG) cannot be the reference point because, over time, the CG does change in an airplane. Instead, a point such as the leading edge of the root chord, the tip of the nose, or the aerodynamic center of the wings serves as a reference point.

The orientation of the body axes with respect to the vehicle frame is
arbitrary. However, by convention, the *x*-axis points towards the
front of the airplane, the *y*-axis points to the right, and the
*z*-axis points to the bottom.

A special case of body axes is when they coincide with the vehicle's
principal axes. This simplifies the equations of motion, because the
airplane's products of inertia become zero. In most aircraft, the
*x*-*z*-plane is a plane of symmetry, and so the *y*-axis is
automatically a principal axis. While many simulators align the *x*-
and *z*-axes with principal axes, some do not due to practical
considerations. In many cases, it is simpler to make the *x*-axis
parallel the horizontal reference axis from the blueprints, or some
other line.

The *x*-*z*-plane in body axes is called the reference plane. This
plane is useful for defining other vehicle coordinate systems.

The transformation from body to wind axes consists of two rotations.
First the body axes are rotated about the *y*-axis through the angle
of attack ;
the axes are then rotated about the *z*-axis
through the angle of sideslip ,
yielding the wind axes. The
angle of attack and the angle of sideslip are defined respectively by

The main reason for the wind axis system is that it is more convenient for calculating aerodynamic forces. For instance, lift is, by definition, perpendicular to the relative wind, while drag is parallel. With wind axes, both lift and drag resolve into a force parallel to one of the axes.