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

被引：6

作者：

Cavcar, A ^{[1
]}

机构：

[1] Anadolu Univ, Sch Civil Aviat, TR-26470 Eskisehir, Turkey

来源：

JOURNAL OF AIRCRAFT | 2006年 / 43卷 / 01期

关键词：

D O I：

10.2514/1.14252

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

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.

引用

页码：125 / 131

页数：7

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