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Can you solve this question about aircraft flight dynamics?
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What is the significance of the term $C_{m_{w}}$ in aircraft flight dynamics and how does it relate to the aircraft's stability and control?
How does the lift coefficient $C_{L}$ affect the drag coefficient $C_{D_{w}}$ in the given approximation equations for $C_{m_{w}}$?
Explain the impact of the parameter $a_{w}$ on the calculation of the moment coefficient $C_{m_{w}}$ in the context of aircraft dynamics.
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