FIELD: evaluation of measurement errors of altitude-speed parameters. SUBSTANCE: present values of sensing of static pressure, altitude, air temperature, atmospheric pressure with change of geometric height are measured at altitude under 500 m. True pressure is determined from equation of statics of atmosphere, atmospheric conditions at airfield level and relative altitude of flight. Then parameters are measured while quasi-stationary conditions of flight at altitudes above 500 m and variations of flight speed and effective angle of attack are conducted. Errors are approximated during postflight processing of them and functions of relative aerodynamic error of air pressure tubes are found depending on Mach number, angle of attack at altitudes below 500 m, above 500 m, at various altitudes with accuracy up to constant value and under condition of continuity and differentiability within the entire range of Mach number and angle of attack. Present function of relative errors depending on various flight altitudes with reference to aerodynamic relative error for entire range of velocities, Mach number and angle of attack is determined by formulas given in description of invention. EFFECT: increased accuracy of determination of aerodynamic errors of air pressure tubes. 3 dwg
