| ElementName |
A name for this element |
| areai |
The planform semi-area of this element (right side only) |
| spani |
The semi-span (not projected) of this element. |
| taper |
Ratio of tip chord to root chord |
| sweep |
Sweep (deg) of c/4 line |
| dihed |
Dihedral angle for this element (deg) |
| xroot |
X-location of root c/4 |
| yroot |
Y-location of root c/4 |
| zroot |
Z-location of root c/4 |
| rooti |
Root incidence (deg) |
| tipi |
Tip incidence (deg) |
| cdp0 |
Section zero lift drag coefficient |
| cdp1 |
Section drag parameter: Cd_section = cdp0 + cdp1*cl + cdp2*cl^2 |
| cdp2 |
Quadratic section drag parameter |
| cl0 |
Cl at alpha=0 for this section |
| cm0 |
Cm at zero lift for this section |
| clmax |
Maximum Cl for this section |
| npan |
Number of spanwise panels (< 40). See note below. |
X is measured positive downstream, Y to the right looking forward, and Z upward as is customary in aerodynamics
calculations. Accurate drag calculation requires at least 20 spanwise panels over the configuration, so choose
the number of panels on each element appropriately. Try to make the width of each panel about the same for each
element (i.e. npan = k * spani).