Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is inclined to the flow. Errors which result from variations in the configuration of static-pressure vents are also presented. Errors due to the position of a static-pressure tube in the flow field of the airplane are given for locations ahead of the fuselage nose, ahead of the wing tip, and ahead of the vertical tail fin. The errors of static-pressure vents on the fuselage of an airplane are also presented. A comparison of the calibrations of the four static-pressure-measuring installations indicates that, for an airplane designed to operate at supersonic speeds, a static-pressure tube located ahead of the fuselage nose will, in general, be the most desirable installation. If the operating range is confined to speeds below sonic, a static-pressure tube located ahead of the wing tip may, for some airplane configurations, prove more satisfactory than a fuselage-nose installation. For operation at Mach numbers below 0.8, a static-pressure tube ahead of the vertical tail fin or fuselage vents, properly located and installed, should prove satisfactory. Various methods of calibrating static-pressure installations in flight are briefly discussed.
An Adobe Acrobat (PDF) file of the entire report: