01 / Flight Lab
AeroLabThe physics of flight.
Explore lift, drag and aircraft performance. Change the conditions and see the physics respond.
Open the calculatorAeroLab / Flight analysis
Flight calculator.
Calculated
- Lift
- 18.12kN
- Drag
- 1,054N
- Air density
- 1.058kg/m³
- Lift-to-drag
- 17.19L/D
- Stall speed
- 28.2m/s
- Thrust-to-weight
- 0.285T/W
Force balance
Vertical
Lift18,120 N
Weight10,885 N
Horizontal
Thrust3,100 N
Drag1,054 N
Linear scale within each pair. Independent forces, not a trimmed-flight solution.
Compare a configuration
No saved comparison.
Method & limitations
Lift = ½ρV²SCL. Drag = ½ρV²SCD. Coefficients stay constant; the speed curve does not model changes in induced or compressibility drag. L/D = CL/CD. Stall speed uses CL max and assumes level flight. The standard atmosphere covers 0–20,000 m. The forces are independent, not a trimmed-flight solution. Presets are illustrative; these estimates are not certified flight data.
SI units · Fixed-coefficient model · Educational use