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T-45A/C TS, ADV & IUT Aero-02
High-Speed Flight
II.
Methods used to overcome effects and permit high-speed
Sg 2, fr 2
flight 1.7.1.4.3.1
Lesson Organization
A.
High-speed aircraft design
HIGH-SPEED FLIGHT
* Effects of high-speed
NOTE: Aircraft designed to fly at near transonic or
flight on aircraft
supersonic speeds all have features incorporated in their
* Methods used to overcome
design to delay onset of critical Mach number, reduce
effects and permit high-
wave drag, reduce or eliminate "tuck under", reduce flow
speed flight
separation, and maintain engine performance.
Sg 2, fr 3
Thickness-to-Chord
1.
Thin airfoil sections of low thickness-to-chord ratio
Ratio
a.
Do not accelerate the air to the extent that a
thick airfoil does
b.
Compression wave is not as strong, once
formed
Sg 2, fr 4
c.
Lack structural strength and volume for landing
Effect of Low
gear and fuel
Thickness-to-Chord
Ratio Airfoil on Shock
Wave Formation
d.
Sweepback (thin wing with thick section) "fools"
air into thinking wing is a thin airfoil section
(1) Airflow broken into vector components
(a) A component perpendicular to the
leading edge contributes to lift; this
component is less than the free stream
component
Sg 2, fr 5
(b) A spanwise component does not
Fig 6: Effect of Wing
Sweep on High-Speed
contribute to lift; this component at
Airflow
high AOAs/low IAS's causes tip stalling
(c) Airflow "sees" an airfoil section of lower
Sg 2, fr 6
Effect of Wing Sweep
thickness-to-chord ratio and smaller
on Drag
leading edge radius
(2) Sweepback effect on drag
(a) Reduces peak drag rise
Page 2-12
(9-99) Original


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