uav - lecture 11 zdobyslaw goraj

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UAV - lecture 11 – Zdobyslaw Goraj

Selection of wing section, part 2

Warsaw, 21 May, 2020

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Aerodynamic characteristics of high lift,

thick, high altitude wing sections

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TLD wing section (Transonic, Loitering, Double)

Two-elements wing sections for transonic loitering (patrolling)

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Comparison of high altitude wing sections

for Re = 1*106 (1/3)

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for Re = 1*106 (2/3)

Altitude factor

Transonic, Loitering, Double

High Altitude Slotted Airfoil

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for Re = 1*106 (3/3)

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Wing section LRT (1/5)

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alpfa

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Wing section HASA (1/2) High Altitude Slotted Airfoil

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Wing section HASA (2/2) High Altitude Slotted Airfoil

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Wing section TLD – 0.65/15A (1/2)

TLD - (Transonic, Loitering, Double)

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Wing section TLD – 0.65/15A (2/2)

Margin of safe speed TLD -Transonic, Loitering, Double

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Comparison of high altitude wing section (1/2)

TLD -Transonic, Loitering, Double

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Comparison of high altitude wing section (2/2)

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Influence of the wing section upper surface

modification on turbulence free flow (1/2)

Flow turbulence free

Flow partly turbulent

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Influence of the wing section upper surface

modification on turbulence free flow (2/2)

Turbulent flow excited at the leading edge

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Influence of wing section (TLD) thickness

on aerodynamic characteristics (1/3)


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Lower lift Lower lift


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Influence of Mach number on aerodynamic characteristics (1/6)

TLD; Re=1*106; Ncr=12


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Influence of Mach number on aerodynamic characteristics(2/6)

TLD; Re=1*106; Ncr=12


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Lift coefficient Cl as a function of max aerodynamic efficiency, versus Mach number

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TLD; Re=1*106; Ncr=12


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Influence of Mach number on aerodynamic characteristics (6/6)

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TLD with flaps deflected (1/5)

Ma=0.20; Re = 3*106


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Ma=0.65; Re = 1*106


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Ma=0.65; Re = 1*106


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Ma=0.65; Re = 1*106


Lift coefficient Cl as a function of max

aerodynamic efficiency, versus Mach number

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Re = 1.5*106


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Flaps as a aerodynamic brake (1/3)

Dimensionless thickness ~ 21%

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Other subsonic wing sections: SA-14 i LA203A

Liebeck

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Comparison of wing sections: SA-14 i LA203A

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Wing sections well

selected for STOL

HT/EX – Horizontal Tail Airfoil

with Extended Range

of Control Power

Dimensionless thickness ~ 18,5%

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Wing section DSA/EX (Double Slotted Airfoil with

Extended range of control power) for STOL 3-elements wing section of increased control effectivity

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Pressure distribution on DSA/EX wing section

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Lift coefficient versus flap deflection, DSA/EX

Lotka i klapa na płacie

głównym są dwuelementowe

Ster na stateczniku jest

jednoelementowy

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Change of

CLmax

versus Re

number

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Elevator efficiency

with DSA/EX wing

section

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Landing run distance with different flap setting

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Landing run distance versus wing loading

uav - lecture 11 zdobyslaw goraj

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