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T-45A/C TS, ADV & IUT Aero-02
High-Speed Flight
3.
Horizontal stabilizer configuration with a movable
leading edge
a.
Slab-type tail (stabilator), i.e., T-45, or
Sg 2, fr 9
trimmable horizontal stabilizer with elevators
Fig 8 & 9: Transonic/
Supersonic Flight
Controls (2 Overlays)
b.
Effective as counter to "tuck under," even when
aft portion is behind a compression wave;
Overlay 1
portion forward of compression wave remains
Overlay 2
effective
c.
Differential stabilizer, i.e., F-14 and F-18,
provide not only pitch moments, but also rolling
Sg 2, fr 10
Fully Powered
moments
Control System
4.
Fully powered, irreversible control systems
a.
Overcome large control forces encountered at
high speeds
b.
Prevent unwanted aerodynamic feedback often
described as control "buzz"
5.
Engine installation
Sg 2, fr 11
Convential Control
a.
No present operational turbojet/fan engines can
System
ingest supersonic flow
(1) All intake air must be decelerated to
subsonic through a series of compression
waves
(2) Exhaust gases must be accelerated above
supersonic if aircraft is to achieve
supersonic flight; generally achieved
Sg 2, fr 12
through the use of a convergent-divergent
Fig 10: Supersonic
duct
Flow in an Engine Inlet
B. T-45 aircraft design
1.
Swept wings (low thickness-to-chord ratio/small
radius leading edge)
2.
Stabilator
Page 2-16
(9-99) Original


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