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14.2: Lift Coefficient Cl

Click the folder button 'Design Computation' and click into input field 'Design Cl' to enter the desired value. All values are valid; values between -2 and +2 are practical.
Within the large airplane sector also higher values can be achieved, usually however only by special lift-increasing flaps. For model airplanes these values lie normally in the range of 0.8 to 1.5.
Near the input field are Up/Down-buttons located. They can be used to change the airplane's position with mouse clicks.
A click on the right mouse button pops up a menu to set the increment between 0.00001 and 1.



Below the input fields the button 'Start Computation' is located. If you click this button, the Vortex-Lattice computation will start. An iteration computation with several passes (approximate computation) starts. The program changes stepwise the angle of attack to approximate the desired lift coefficient. If the program exceeds 90° angle of attack, the computation will abort with an error message.

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