曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
REVIEW OF BASIC AERODYNAMIC PRINCIPLES 45
Fig.1.46 Schematic variation ofcrit.icaIMach number with tluckness ratio.
is formed at the leading edge and the flow everywhere is supersonic on the airfoil
. -
surface as we have discussed earlier. .
i.n. Methods of Postponing Adverse Effects of Co
There are a number of ways of delaying the adverse effects of compressibil-
ity to higher Mach numbers. This js of considerable importance to the airline
industry because"'even a modest rise in the cruise Mach number in the high sub-
sonic/transonic regime helps to cut down operating costs considerably. Some of
the most commonly used methods are discussed in the following sections.
Thin airfo17s. The thinner the airfoil, the smaller the peak local velocitjt on its
surface will be and the higher the critical Mach number wi,ll be as schematically
shown in Fig. 1.46. The use of thin airfoils pushes the critical-Mach number
and the drag divergence number further towards unity. However, a disadvantage
of using very thin airfoils is that their low-speed characteristics, especially the
stalling characteristics, are poor. As we have discussed earlier, thin airfoils exhibit
an abrupt loss oflift at stall, which leads to stability and control problems as we
shall study later in the text.
Low-aspect ratio wings. As we know, the lower the aspect ratio, the more
pronounced the indtrced flow effects will be and the lower the peak velocities
on the wing surface will be. As a result, the critical Mach number will increase
with a decrease in aspect ratio as shown schematically in Fig, 1.47. However, the
disadvantage oflow-aspect ratio wings is that they have higher induced drag and
lower lift curve slopes.
Supercritica/ a/rfo17s. For a conventiortal airfoil at Mach numbers above the
critical Mach number, the local region of supersonic flow terminates in a strong
shock wave (Figs. 1.42c and 1.42d) that induces significant flow separation and a
steep rise in the drag coefficient. For a supercritical airfoil12.13 shownrin Fig. 1.48a,
the curvature ofthe middle region of the upper surface is substantially reduced with
46 PERFORMANCE, STABILITY DYNAMICS, AND CONTROL
A
Fig.1.47 Schematic variation ofcrihcaIMach number with aspect ratio.
+
┏━━━━━━━━━━━━━━━━━━━━━┓
┃ ) i7sU ┃
┃ ┃
┣━━━━━━━━━━━━━━━━━━━━━┫
┃ ┃
┣━━━━━━━━━━━━━━━━━━━━━┫
┃//7: ~- :: ltte . - '\ ┃
┣━━━━━━━━━━━━━━━━━━━━━┫
┃ ┃
┗━━━━━━━━━━━━━━━━━━━━━┛
b) Schematic pressure clistribution
Fig. 1.48 SchematiciHustration offtow o'ver supercriticait airfoil.
REVIEW OF BASIC AERODYNAMIC PRINCIPLES
47
a resulting decrease in the strength and extent of the shock wave. As a result, the
drag associated with the shock wave is reduced and, more importantly, the onset
of separation is substantially delayed. The lif.t lost by reducing the upper surface
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
动力机械和机身手册1(29)
