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翻訳と辞書　辞書検索 [ 開発暫定版 ] スポンサード リンク equivalent airspeed ： ウィキペディア英語版 equivalent airspeed Equivalent airspeed (EAS) is the airspeed at sea level in the International Standard Atmosphere at which the dynamic pressure is the same as the dynamic pressure at the true airspeed (TAS) and altitude at which the aircraft is flying.〔Clancy, L.J. (1975), ''Aerodynamics'', Section 3.8, Pitman Publishing Limited, London. ISBN 0-273-01120-0〕〔Anderson, John D. (2007), ''Fundamentals of Aerodynamics'', p.215 (4th edition), McGraw-Hill, New York USA. ISBN 978-0-07-295046-5〕 In low-speed flight, it is the speed which would be shown by an airspeed indicator with zero error.〔Houghton, E.L. and Carpenter, P.W. (1993), ''Aerodynamics for Engineering Students'', Section 2.3.3, Butterworth-Heinemann, Oxford UK. ISBN 0-340-54847-9〕 It is useful for predicting aircraft handling, aerodynamic loads, stalling etc. $EAS\; =\; TAS\; \backslash times\; \backslash sqrt\}$ Where: $\backslash rho\backslash ,$ is actual air density. $\backslash rho\_0\backslash ,$ is standard sea level density (1.225 kg/m³ -or- 0.00237 slugs/ft³). EAS is a function of dynamic pressure. $EAS\; =\; \backslash sqrt\}$ Where: $\backslash ,$ is dynamic pressure. $q\; =\; \backslash tfrac12\backslash ,\; \backslash rho\backslash ,\; v^,$ (this equation requires a consistent system of measurement) EAS can also be obtained from the aircraft mach number and static pressure. $EAS\; =\; M\; \backslash sqrt$ Where: $\backslash ,$ is the standard speed of sound at 15 °C (661.47 knots) $M\backslash ,$ is Mach number $P\backslash ,$ is static pressure $P\_0\backslash ,$ is standard sea level pressure (1013.25 hPa) Combining the above with the expression for Mach number gives EAS as a function of impact pressure and static pressure (valid for subsonic flow): $EAS=+1\backslash right)^\backslash frac-1\backslash right"\; TITLE="\backslash left(\backslash frac+1\backslash right)^\backslash frac-1\backslash right">)\}$ Where: $\backslash ,$ is impact pressure. At standard sea level EAS is the same as calibrated airspeed (CAS) and true airspeed (TAS). At high altitude, EAS may be obtained from CAS by correcting for compressibility error. A simplified formula can be used that allows calculation of CAS from EAS. $CAS=(1-\backslash delta)M^+\backslash frac(1-10\backslash delta+9\backslash delta^)M^\backslash right"\; TITLE="1+\backslash frac(1-\backslash delta)M^+\backslash frac(1-10\backslash delta+9\backslash delta^)M^\backslash right">)\}$ where: Pressure ratio: $\backslash delta=\backslash frac\{P\_\{0\}\}$ $CAS\backslash ,$ & $EAS\backslash ,$ the airspeeds in either knots, km/h, mph or any other appropriate unit Above formula is accurate within 1% up to Mach 1.2 and useful with acceptable error up to Mach 1.5. The 4th order Mach term can be neglected for speeds below Mach 0.85. == See also == * Position error * True airspeed * Indicated airspeed * Calibrated airspeed 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「equivalent airspeed」の詳細全文を読む スポンサード リンク 翻訳と辞書 : 翻訳のためのインターネットリソース Copyright(C) kotoba.ne.jp 1997-2016. All Rights Reserved.