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Atmosphere and Flight Conditions

1 tool in the Aerodynamics area.

Standard Atmosphere and Airspeeds

Temperature, pressure, density, speed of sound and viscosity of the U.S. Standard Atmosphere, 1976 at any geometric altitude to 86 km, with an optional ISA temperature offset giving the pressure and density altitudes, and the airspeed chain of NACA Report 837: indicated, calibrated, equivalent and true airspeed, Mach number, impact and dynamic pressure from any one of them (instrument and position corrections for IAS, the compressibility correction from CAS to EAS, the Rayleigh pitot formula above Mach 1), Reynolds number per unit length and at a reference length, the layer equations printed with the 1976 constants, a table of the atmosphere at the standard altitudes and charts of the ratios and of the airspeeds against altitude. The default is 35,000 ft at 250 knots calibrated airspeed, for which the page gives T = 218.92 K, p = 499.3 lb/ft^2, rho/rho_0 = 0.3106, M = 0.740, 426.8 KTAS and 237.9 KEAS, checked against the printed rows of Tables I, III and IV of the standard.

1 worked example reproduced, listed on the tool page.

Other Aerodynamics sections

Airfoils and Wings · Rotors and Propellers · Aircraft Performance · Stability and Control · Propulsion