L/D max: —
Total Lift
—
kN
Total Lift [kN]
L = q·S·CL.
q=½ρV² dinamik basınç.
Total Drag
—
kN
Total Drag [kN]
D = q·S·CD.
Profile + Friction + Induced + Wave.
L/D Ratio
—
L/D — Efficiency
CL/CD ratio.
CD_friction
—
Schlichting
CD_friction
Schlichting mixed BL. Michel x_tr criterion.
Stall α
—
Stall Angle
CLmax corresponds to this α.
Mach / Re_mac
—
Mach · Re_mac
M = V/a, Re = ρVc/μ at MAC.
Stall Type
—
Stall Type
LE: abrupt. TE: gentle.
Flap ΔCL
0.000
Flap ΔCL
ΔCL = Cl_δ·δ_rad (NACA).
Cm_α [/rad]
—
Pitching Moment Deriv.
Cm_α < 0 → stable.
Static Margin
—
NP: —
Static Margin [% MAC]
SM = (x_NP − x_CG)/MAC.
Bending Mom.
—
kN·m
Root Bending Moment
Integrated spanwise lift × moment arm.
Wing Area
—
m²
Wing Area S
Total planform area both sides.
Aspect Ratio
—
Aspect Ratio AR
AR = b²/S.