| 1. | For most airfoils, lift slope decreases at high lift coefficients.
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| 2. | Maximum Lift Coefficient of the aircraft and therefore reduce its stalling speed.
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| 3. | This corresponds to a lift coefficient of 1.17.
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| 4. | When slats are extended they increase wing camber and increase maximum lift coefficient.
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| 5. | Finally, constant k _ 1 is determined to give the desired lift coefficient.
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| 6. | For example, the phenomenon of lift coefficient, leading to a still greater displacement.
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| 7. | At higher angles a maximum point is reached, after which the lift coefficient reduces.
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| 8. | Boundary layer separation is generally undesirable in aircraft high lift coefficient systems and jet engine intakes.
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| 9. | For example, using Lifting-Line Theory for a flat elliptical wing, the lift coefficient is
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| 10. | While climbing, the flaps were extended, producing a high lift coefficient of 2.2.
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