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Stability
T-45A/C TS, E2C2, ADV & IUT Aero-04
B.
T-45 has conventional rudder
Sg 1, fr 4
Conventional Control
System
1.
Aerodynamic forces may feed back to rudder pedals
2.
Rudder pedals will be displaced due to side loads
during post stall gyration or spin
3.
Up to 300 pounds of pressure may be required to
counter air loads on rudder during post stall gyration
or spin
II.
Stability (General)
Sg 2, fr 2
Lesson Organization
A.
Stall
STABILITY
1.
Condition when any increase in angle of attack
* T-45 Flight Controls
(AOA) results in decrease in coefficient of lift (CL)
* Stability (Generic)
* T-45 Stability (General)
* Factors Affecting T-45
2.
Stalling AOA is AOA that stall commences or
Stability
coefficient of lift max (CL)max
3.
Swept wing aircraft generate less CL
Sg 2, fr 3
Fig 2: Coefficient of
a.
stall at higher AOA than straight wing aircraft
Lift Curve: Straight vs
Swept Wing
b.
stall less dramatic, flatter CL curve
Figure 2: COEFFICIENT OF LIFT CURVE: STRAIGHT VS SWEPT WING
Page 4-4
(9-99) Original


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