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
where Ce and c are the mean aerodynamic chords of the exposed wing and total
(theoretical) wing, respectively; (CLq)e and (CLq)B are the contributions of the
exposed wing and isolated body, respectively. The wing-body interference param
eters KB(W) and KW(B) can be obtained using the data given in Chapter 3. The
value of (CLq)WB given by Eq. (4.488) is per radian.
For subsonic speeds]
where
(CLq)e = (~ + 2g)(CLcr)e
g:x
c
(4.489)
(4.490)
x = (Xac)e - Xcg,le (4.491)
Here, (Xac)e iS the distance of the exposed wing aerodynamic center from the
leading edge of the root chord, and Xcg,te iS the distance of the center of gravity
from the leading edge of the exposed wing root chord. Both (Xac)e and Xc8Je are
measured parallel to the exposed wing root chord.
The parameter x will be positive if the aerodynamic center of the exposed wing
(Xac)e iS aft of the center of gravity as shown in the insert at the top of Fig. 4,20.
The lift: curve slope of the exposed wing (CLa)e and the aerodynamic center of the
exposed wing (Xac)e may be estimated using the procedure discussed in Chapter 3.
For supersonic Mach numbers, Datcoml gives
(CLq)e = (C2q)e + 28(CNa)e (4.492)
For low supersonic Mach numbers when the leading edge is subsonic or f3 cot ALE
< 1, the data7 is somewhat sparse and is not given here. The interested reader may
refer to Datcoml
For higher Mac irhen theleading edge becomes supersonic or p cot A
> 1. the p._'irt;~,j~f_u{:sented in Fig. 4.20 for typical wing sections. For
rder may refer to Datcoml
dataonotherwin ;bth~nriecadp -:)'
The body cont (:e2e )sB (j:e, (4.493)
(CZ,q)B = 2((
(C;a,)B=(Cla)B(S ) (4.494)
(CLcr)B = 2(k2 - k,)(SV:,, ) (4.495)
c
r:
lr
l:
l-
;.
.'J
394 PERFORMANCE, STABILITY, DYNAMICSr AND CONTROL
taper rat1o=o.2s
(CLq) e
(C2q)e
~-~ A = 30o
-~-~ A = 45o
--.--.- A = 600
taper rat1o=0.5
Aspect Rat1o=2.0
Aspect Rat1o=4.0
Mach Number
(CJ.q)
2
Z
-2
-4
┏━━━━━━━━━━━━━━━━━┓
┃O_-A ┃
┣━━━━━━━━━━━━━━━━━┫
┃ r- . ┃
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2(109)
