PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1(83)

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

                           - 6.9789
 Ccrse 2, SST:   Thelift-to-drag ratiois given by
                                                        2zn Em
                       E = ~+~222
        2 * 6.5881*1.406 *  13.1762
= ~+6 588~2:* ~4062
- 2.8122
We have
AIRCRAFT PERFORMANCE
             z
         = 1.406
p = ,os-, (l~06)
    = 44.6643 deg
V=~
        -. 45.2778 m/s
            2n W
    CL -. pS /-2
         - 2.9292
R - Rnun
    V~
143
        ~-
                               g ~2-7
                                                     - 211.4288 m
                                V
                    w: R
                                                                    -. 0.2142 rad/s
                                                        = 12.2709 deg/s
              27r
                               t ~ --
                        co
                                                       - 29.3333 s
Because CL > CL,max, the aircraft cannot perform a steady SST at constant altitude
at sealevel. The reader may verify that V  < Vstall
Case 3, Turn wrlh nmu:   We have
                                 E = Em
                                               = 13.1762
                    N
                                       tl - rzmax
                   ~
                                                          -. z
　
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