NACA Technical Notes

Note presenting the effect of inclination of the airstream on the static pressure measured by two essentially similar service pitot-static tubes and by one of those tubes with three modified orifice arrangements as determined in flight. Results regarding initial calibrations at Mach numbers from 0.20 to 0.24 and the final orifice configuration are provided

NACA Technical Notes

Note presenting a flight investigation made on three nonrotating full-scale propeller spinners at free-stream Mach numbers of 0.70 to 0.96 to determine the surface-pressure distribution and the magnitude and radial extent of the influence of each spinner on the local flow field. Results regarding surface static-pressure distributions and radial variation of local Mach number along the blade center line are provided

Flight investigation of the variation of static-pressure error of a static-pressure tube with distance ahead of a wing and a fuselage /

Flight calibrations of the static-pressure error of a static-pressure tube located 1/4 to 2 chords ahead of the wing tip of a trainer airplane and 1/2 to 1 1/2 body diameters ahead of the fuselage and 1 chord ahead of the wing tip of a fighter airplane are presented. Calibrations were obtained over an indicated speed range from stall to speeds not exceeding 265 miles per hour.NACA TN No. 2311."March 1951."Flight calibrations of the static-pressure error of a static-pressure tube located 1/4 to 2 chords ahead of the wing tip of a trainer airplane and 1/2 to 1 1/2 body diameters ahead of the fuselage and 1 chord ahead of the wing tip of a fighter airplane are presented. Calibrations were obtained over an indicated speed range from stall to speeds not exceeding 265 miles per hour.Mode of access: Internet