144 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
p. = ,os-l 6 S~881
- 81.2694 deg
V = \/2VR
; 298.2950 m/s
CL :
- 0.3162
g.~2-=1
to : - N
V
-. 0.2142 rad/s
- 12.2709deg/s
27r
t-
w
- 29.3333 s
R = Lv
co
- 1392.60 m
Ct;rse 4, Corner Velocity Turn: For this case,we have
CL -. CL,max
~ 1.2
CD - CDO+ CZ.max
= 0.012 + 0.120 * l,22
- 0.1848
Tl, - Tllim
- 82.8192 deg
AIRCRAFT PERFORMANCE
V -.
- 168.7408 m/s
D - ~p V2SCD
= 2l1.225 * 168.74082 * 30 * 0.1848
- 96,687.3201
y = s:-, (-. )
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