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.