APPLICATION OF CIRCULATION CONTROL TO ADVANCED SUBSONIC TRANSPORT AIRCRAFT .1. AIRFOIL DEVELOPMENT

被引：37

作者：

ENGLAR, RJ

SMITH, MJ

KELLEY, SM

ROVER, RC

机构：

[1] Aerospace Sciences Laboratory, Georgia Tech Research Institute, Atlanta, GA

来源：

JOURNAL OF AIRCRAFT | 1994年 / 31卷 / 05期

关键词：

Control systems - Drag - Lift - Mass transfer - Performance - Pneumatic equipment - Subsonic aerodynamics - Transport aircraft - Wings;

D O I：

10.2514/3.56907

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An experimental/analytical research program was undertaken to develop advanced versions of circulation control wing (CCW) blown high-lift airfoils, and to address specific issues related to their application to subsonic transport aircraft. The primary goal was to determine the feasibility and potential of these pneumatic airfoils to increase high-lift system performance in the terminal area while reducing system complexity. A four-phase program was completed, including 1) experimental development and evaluation of advanced CCW high-lift configurations, 2) development of effective pneumatic leading-edge devices, 3) computational evaluation of CCW airfoil designs plus high-lift and cruise capabilities, and 4) investigation of the terminal-area performance of transport aircraft employing these airfoils. The first three phases of this program are described in Part I of this article. Applications to the high-lift and control systems of advanced subsonic transport aircraft and resulting performance are discussed in the continuation of this article, Part II. Experimental lift coefficient values approaching 8.0 at zero incidence and low blowing rates were demonstrated by two-dimensional CCW configurations that promised minimal degradation of the airfoil's performance during cruise. These results and experimental/CFD methods will be presented in greater detail in the following discussions.

引用

页码：1160 / 1168

页数：9

共 31 条

[1]

Englar R.J., Applegate C.A., Circulation control-a bibliography of dtnsrdc research and selected outside references (Jan. 1969 to dec. 1983), David Taylor Naval Ship R&D Center Rept, (1984)

[2]

Englar R.J., Experimental Investigation of the High Velocity Coanda Wall Jet Applied to Bluff Trailing Edge Circulation Control Airfoils, (1975)

[3]

Jones D.G., Measurements of Wall Jet Development on a Circulation Control Aerofoil, (1971)

[4]

Englar R.J., Two-Dimensional Subsonic Wind Tunnel Tests of Two 15-Percent-Thick Circulation Control Airfoils, (1971)

[5]

Englar R.J., Development of the A-6/Circulation Control Wing Flight Demonstrator Configuration, (1979)

[6]

Williams R.M., Howe H.J., Two-Dimensional Subsonic Wind Tunnel Tests of a 20-Percent Thick, 5-Percent Cambered Circulation Control Airfoil, (1970)

[7]

Englar R.J., Low-Speed Aerodynamic Characteristics of a Small Fixed-Trailing Edge-Circulation Control Wing Configuration Fitted to a Supercritical Airfoil, (1981)

[8]

Englar R.J., Huson C.G., Development of Advanced Circulation Control Wing High-Lift Airfoils, (1983)

[9]

Englar R.J., Huson C.G., Journal of Aircraft, 21, 7, pp. 476-483, (1984)

[10]

Wilson M.B., Von Kerczek C., An Inventory of Some Force Producers for Use in Marine Vehicle Control, (1979)

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