Constant altitude-constant Mach number cruise range of transport aircraft with compressibility effects

被引：0

作者：

Cavcar, Aydan ^{[1
,2
]}

机构：

[1] Anadolu University, 26470 Eskisehir, Turkey

[2] School of Civil Aviation, Turkey

来源：

Journal of Aircraft | 1600年 / 43卷 / 01期

关键词：

An approximate solution of the constant altitude-constant Mach number cruise range for high subsonic speed flight of the turbojet/fan aircraft is proposed. The solution considers cambered wing drag polar of modern transport aircraft; dependence of the specific fuel consumption on Mach number; and compressibility effects on aerodynamic characteristics of the aircraft. The method aims for a quick assessment of the cruise range during conceptual or preliminary design phase. An application of the method to a known type of aircraft is also presented. Copyright © 2005 by the American Institute of Aeronautics and Astronautics; Inc. All rights reserved;

D O I：

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学科分类号：

摘要：

Journal article (JA)

引用

页码：125 / 131

共 50 条

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