WING LEADING-EDGE DESIGN CONCEPTS FOR AIRBREATHING HYPERSONIC WAVERIDERS

被引：6

作者：

BLOSSER, ML

SCHWOERKE, S

BRUNSON, D

HAGSETH, OP

机构：

[1] Thermal Structures Branch, M/S 396, NASA Langley Research Center, Hampton, VA

[2] Hypersonics Research Division, NASA Headquarters, Washington, DC

[3] Flight Sciences, MZ 4207, Lockheed, Fort Worth Company, Fort Worth, TX

[4] Flight Sciences, MZ 2892, Lockheed, Fort Worth Company, Fort Worth, TX

来源：

JOURNAL OF AIRCRAFT | 1995年 / 32卷 / 02期

关键词：

D O I：

10.2514/3.46717

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Wing leading-edge structural concepts are considered in this article for a specific Mach 5 waverider cruise vehicle. Design tradeoffs, such as making the leading edges sharp enough for acceptable aerodynamic and propulsion efficiency, yet blunt enough for acceptable aerodynamic heating, are discussed. Aerodynamic heating distributions are calculated for two locations on the leading edge of the vehicle. Several structural concepts are discussed and a particular concept is studied. Temperature and thermal stress distributions are calculated for a simple wing leading-edge concept consisting of an uninsulated hot structure. Techniques for reducing thermal stresses are discussed.

引用

页码：307 / 322

页数：16

共 26 条

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