C

Figure 3.7 Detailed view of the sting-mounted wing.

and so

Two static aeroelastic equilibrium equations can now be written for the determination of Op and 6m- Using Eqs. (3.3) and (3.4) for the lift and pitching moment, the force equilibrium equation can be written as qSCLa(ar+0F + 0M)- W-F0 = 0, (3.15)

and the sum of moments about the trailing edge yields qScCMac + qSCLa(ar + 0F + 0M)(c - xac) - W(C - xcg) - M0 = 0. (3.16)

Substitution of Eqs. (3.14) into Eqs. (3.15) and (3.16), simultaneous solution for 0F and 0M, and use of Eq. (3.12) yields

0 0

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