Airspeed
Body Axes
Inertial Axes
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Deflect Elevator
Steady State Condition
Steady State 1
Steady State 2
Steady State 3
Altitude:
m
True Airspeed (\( V_{\text{TAS}_{1}} \)):
m/s
Angle of Attack (\( \alpha_1 \)):
°
Pitch Rate (\( q_{1} \)):
0.00
°/s
Pitch Angle (\( \theta_{1} \)):
°
Lift Coefficient (\( C_{L_{1}} \)):
Drag Coefficient (\( C_{D_{1}} \)):
Elevator Deflection (\( \delta_{e_{1}} \)):
°
Stability Derivatives
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\(C_{D_{\alpha}}\):
\(C_{L_{\alpha}}\):
\(C_{L_{q}}\):
\(C_{m_{\alpha}}\):
\(C_{m_{\dot{\alpha}}}\):
\(C_{m_{q}}\):
\( \Delta u\) (m/s)
\( \Delta \alpha \) (deg)
\( \Delta q \) (deg/s)
\( \Delta \theta \) (deg)