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Specification for Pressure-Driven Airspeed Indicators
Air-speed indicators, Speedometers, Aircraft instruments, Aircraft components, Pressure measurement (fluids), Differential pressure, Indicating device components, Type testing, Performance testing
Flight Calibration of Four Airspeed Systems on a Swept-wing Airplane at Mach Numbers Up to 1.04 by the NACA Radar-phototheodolite Method
Of the systems investigated, a nose-boom installation was found to be most suitable for research use at transonic and low supersonic speeds because it provided the greatest sensitivity of the indicated Mach number to a unit change in true Mach number at very high subsonic speeds, and because it was least sensitive to changes in airplane normal-force coefficient. The static-pressure error of the nose-boom system was small and constant above a Mach number of 1.03 after passage of the fuselage bow shock wave over the airspeed head.
Standard Nomenclature for Airspeeds with Tables and Charts for Use in Calculation of Airspeed
Symbols and definitions of various airspeed terms that have been adopted as standard by the NACA Subcommittee on Aircraft Structural Design are presented. The equations, charts, and tables required in the evaluation of true airspeed, calibrated airspeed, equivalent airspeed, impact and dynamic pressures, and Mach and Reynolds numbers have been compiled. Tables of the standard atmosphere to an altitude of 65,000 feet and a tentative extension to an altitude of 100,000 feet are given along with the basic equations and constants on which both the standard atmosphere and the tentative extension are based.
Position Errors of the Service Airspeed Installations of 10 Airplanes
The "position" errors of the static systems of 10 service airspeed installations including static-pressure vents on the nose and rear section of the fuselage and pitot-static tubes mounted on the wing, the vertical tail, and the fuselage nose are presented. Tests were conducted at speeds between the stalling speed and 260 miles per hour for four flight conditions. Calibrations are analyzed to show variation of static-pressure error with position of static source, angle of attack, flap setting, and engine power.
Slow Flight Sense
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