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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)
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