A vehicle guidance system, comprising: a plurality of surface-mounted pressure sensors configured to be mounted on a vehicle, wherein a surface pressure distribution is represented by surface pressure data detected by several surface-mounted pressure sensors constituting a set of surface-mounted pressure sensors; an air data estimation controller configured to be connected to each of the plurality of surface-mounted pressure sensors, the air data estimation controller being configured to: receive an initial value for a Mach number of the vehicle, calculate a converged value for an angle of attack (α c) of the vehicle based on a first set of surface pressure data from a first set of the surface-mounted pressure sensors, and a converged sideslip angle value (β c) of the vehicle based on a second set of surface pressure data from a second set of the surface-mounted pressure sensors, calculate a freestream dynamic pressure q ̅ ∞ n + 1 based on the initial value for Mach number M ∞ n, the calculated converged value for angle of attack (α c), and the calculated converged sideslip angle value (β c), calculate a freestream pressure (p ∞), and calculate a converged value for Mach number (M ∞) based on the calculated freestream pressure (p ∞) and the calculated freestream dynamic pressure q ̅ ∞ n + 1; and a flight control processor configured to receive the calculated converged value for Mach number (M ∞) and the calculated freestream pressure (p ∞) from the air data estimation controller, and to provide an output command for adjusting an orientation of the vehicle based on the converged value for Mach number (M ∞) and the freestream pressure (p ∞). a plurality of surface-mounted pressure sensors configured to be mounted on a vehicle, wherein a surface pressure distribution is represented by surface pressure data detected by several surface-mounted pressure sensors constituting a set of surface-mounted pressure sensors; an air data estimation controller configured to be connected to each of the plurality of surface-mounted pressure sensors, the air data estimation controller being configured to: receive an initial value for a Mach number of the vehicle, calculate a converged value for an angle of attack (α c) of the vehicle based on a first set of surface pressure data from a first set of the surface-mounted pressure sensors, and a converged sideslip angle value (β c) of the vehicle based on a second set of surface pressure data from a second set of the surface-mounted pressure sensors, calculate a freestream dynamic pressure q ̅ ∞ n + 1 based on the initial value for Mach number M ∞ n, the calculated converged value for angle of attack (α c), and the calculated converged sideslip angle value (β c), calculate a freestream pressure (p ∞), and calculate a converged value for Mach number (M ∞) based on the calculated freestream pressure (p ∞) and the calculated freestream dynamic pressure q ̅ ∞ n + 1; and a flight control processor configured to receive the calculated converged value for Mach number (M ∞) and the calculated freestream pressure (p ∞) from the air data estimation controller, and to provide an output command for adjusting an orientation of the vehicle based on the converged value for Mach number (M ∞) and the freestream pressure (p ∞). receive an initial value for a Mach number of the vehicle, calculate a converged value for an angle of attack (α c) of the vehicle based on a first set of surface pressure data from a first set of the surface-mounted pressure sensors, and a converged sideslip angle value (β c) of the vehicle based on a second set of surface pressure data from a second set of the surface-mounted pressure sensors, calculate a freestream dynamic pressure q ̅ ∞ n + 1 based on the initial value for Mach number M ∞ n, the calculated converged value for angle of attack (α c), and the calculated converged sideslip angle value (β c), calculate a freestream pressure (p ∞), and calculate a converged value for Mach number (M ∞) based on the calculated freestream pressure (p ∞) and the calculated freestream dynamic pressure q ̅ ∞ n + 1; and a flight control processor configured to receive the calculated converged value for Mach number (M ∞) and the calculated freestream pressure (p ∞) from the air data estimation controller, and to provide an output command for adjusting an orientation of the vehicle based on the converged value for Mach number (M ∞) and the freestream pressure (p ∞).