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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