Method for determining a position error correction on a static pressure measurement at an aircraft flying through a flow field, wherein p PEC = C p 1 2 ρV TAS 2 with: p PEC: position error correction C p: a non-dimensional pressure coefficient ρ: the density of the air V TAS: the true air speed and wherein C p is represented by the following Taylor series expansion C p = C 0 + C 1 M + C 2 α + C 3 β + C 4 M 2 + C 5 α 2 + C 6 β 2 + C 7 Mα + C 8 log R e + H. O. T. with: C 0, C 1,..: constants M: the Mach number α: the angle of attack β: the angle of sideslip R e: the Reynolds number H.O.T.: higher order terms of the Taylor series expansion characterized in that the constants of the Taylor series expansion are determined by the succession of the following steps: a) a step of an initial determination of the constants, using calculations based upon computational fluid dynamics and a detailed 3D scan of relevant parts of the aircraft; b) a step of a validation of the results of step a) by performing low altitude flyby's at a ground station while performing pressure measurements at the aircraft and comparing a static pressure measured at the ground station with the pressure measurements at the aircraft; c) a step of an extrapolation to altitude of the results from step b) by carrying out flight tests at a specific altitude accompanied by specific flight manoeuvres, during which step a first pressure measurement (p m1) is performed followed by performing a number of subsequent pressure measurements (p m2) at conditions of constant atmospheric static pressure (p) during said flight tests, wherein the difference between any pair of pressure measurements p m 1 − p m 2 = p + p PEC 1 − p + p PEC 2 with: p PEC1: position error correction of first pressure measurement p PEC2: position error correction of subsequent pressure measurements yields Δp m = ΔP PEC which through Δp PEC = Δ c p 1 2 ρV 2 then is used to further validate the extrapolation to altitude. p PEC: position error correction C p: a non-dimensional pressure coefficient ρ: the density of the air V TAS: the true air speed and wherein C p is represented by the following Taylor series expansion C p = C 0 + C 1 M + C 2 α + C 3 β + C 4 M 2 + C 5 α 2 + C 6 β 2 + C 7 Mα + C 8 log R e + H. O. T. with: C 0, C 1,..: constants M: the Mach number α: the angle of attack β: the angle of sideslip R e: the Reynolds number H.O.T.: higher order terms of the Taylor series expansion C 0, C 1,..: constants M: the Mach number α: the angle of attack β: the angle of sideslip R e: the Reynolds number H.O.T.: higher order terms of the Taylor series expansion characterized in that the constants of the Taylor series expansion are determined by the succession of the following steps: a) a step of an initial determination of the constants, using calculations based upon computational fluid dynamics and a detailed 3D scan of relevant parts of the aircraft; b) a step of a validation of the results of step a) by performing low altitude flyby's at a ground station while performing pressure measurements at the aircraft and comparing a static pressure measured at the ground station with the pressure measurements at the aircraft; c) a step of an extrapolation to altitude of the results from step b) by carrying out flight tests at a specific altitude accompanied by specific flight manoeuvres, during which step a first pressure measurement (p m1) is performed followed by performing a number of subsequent pressure measurements (p m2) at conditions of constant atmospheric static pressure (p) during said flight tests, wherein the difference between any pair of pressure measurements p m 1 − p m 2 = p + p PEC 1 − p + p PEC 2 with: p PEC1: position error correction of first pressure measurement p PEC2: position error correction of subsequent pressure measurements yields Δp m = ΔP PEC which through Δp PEC = Δ c p 1 2 ρV 2 then is used to further validate the extrapolation to altitude. a) a step of an initial determination of the constants, using calculations based upon computational fluid dynamics and a detailed 3D scan of relevant parts of the aircraft; b) a step of a validation of the results of step a) by performing low altitude flyby's at a ground station while performing pressure measurements at the aircraft and comparing a static pressure measured at the ground station with the pressure measurements at the aircraft; c) a step of an extrapolation to altitude of the results from step b) by carrying out flight tests at a specific altitude accompanied by specific flight manoeuvres, during which step a first pressure measurement (p m1) is performed followed by performing a number of subsequent pressure measurements (p m2) at conditions of constant atmospheric static pressure (p) during said flight tests, wherein the difference between any pair of pressure measurements p m 1 − p m 2 = p + p PEC 1 − p + p PEC 2 with: p PEC1: position error correction of first pressure measurement p PEC2: position error correction of subsequent pressure measurements yields Δp m = ΔP PEC which through Δp PEC = Δ c p 1 2 ρV 2 then is used to further validate the extrapolation to altitude. p PEC1: position error correction of first pressure measurement p PEC2: position error correction of subsequent pressure measurements yields Δp m = ΔP PEC which through Δp PEC = Δ c p 1 2 ρV 2 then is used to further validate the extrapolation to altitude.