曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

      of 0,3 above and below the design lift coefficient.
      4: The design lift coefficient is 0.4.
      18: The maximum thickness is 0.18c.
   The concept of design lift coefficient is illustrated in Fig. 1.16. It is the mean
value of the range of lift coefficients for which the sectional drag coefficient is
minimum.
For additional information on airfoil data, refer to Refs. 2 and 3.
                  Cl
Fig*1.16    Concept of desigrt lift coeffiaenL
16               PERFORMANCE, STABfLfTY, DYNAMICS, AND CONTROL
I-4.2  Wing Planform Parameters
      General planform parameters that are usefulin estimating aerodynamic data are
the planform area S, aspect ratio A, mean aerodynamic chord c, and the spanwise
location of the mean aerodynamic chord Ymac  These parameters are given by the
following expressions:
                                                      S = 2 [,' c(y) dy                                        (1.19)
                                   A = bS                            (1.20)
                                   - = ~[,'C2(y)dy  .                        (1.21)
                             2
                                              ymac = i= [' -(Y)Y dy                                 (1.22)
where c(y) is thelocal chord, y is the spanwise coordinate, and b is the wing span.
    For a corrventional straight wing (Fig. 1.17), Eqs. (1.19-1.22) reduce to
                                                             S = ~i;Cr (1 +A)                                             (1.23)
           A=- 2b          (1.24)
                     :c,( + )
                               - = ~Cr(:A//   )                       (1.25)
                                         l:
                                                         ymac = : (L++2AA)                                         (1.26)
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：動力機械和機身手冊1(15)