wing configuration

7/18/2019 Wing Configuration

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Activity 3: wing configuration

To determine the appropriate airfoil for your design

To determine the airfoil characteristics of your designed aircraft

The NACA 2418 airfoil has a maximum camber of 2% located 40% (0.4 chords)

from the leading edge with a maximum thickness of 18% of the chord. Four-digit series airfoil

by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge.

NACA 2418 ( = 0.18 )

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NACA 2418 ()

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Airfoil Profile: NACA 2418 ( = 6)

= 7.8

Item No.:

①, = READ FROM GRAPH

②, ∝ = READ FROM GRAPH

③,

∆

= 18.24kCL

= 18.24k x ①

Where:

= 1

1

= 1.8 .88 1

.9

=-0.03748

In Figure 9:23

= 0.9 @ A6 = 6

= 0.868 @ AD = 7.8

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④, ∝ = ② + ③

⑤, = READ FROM GRAPH ( A = 6 )

⑥, ∆ = 0.318kCL2

= 0.318k x ①2

⑦, = ⑤ + ⑥

⑧, cos ∝ = cos④

⑨, sin ∝ = sin④

⑩, cos ∝ = ① x ⑧

⑪, ∝ = ⑦ x ⑨

⑫, = ⑩ + ⑪

⑬, sin ∝ = ① x ⑨

⑭, ∝ = ⑦ x ⑧

⑮, = ⑭ ⑬

⑯, C.P. = READ FROM GRAPH (A = 6)

⑰, / = (0.25 ⑯) ⑫

⑱, .. = ⑰ + . . 0.25 ⑫

Where:

..= 0.250.40

⑲, =⑥

⑳, = ⑦ ⑲

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① ② ③ ④ ⑤

- deg. deg. deg. -

-0.38 -4.1 0.26 -3.84 0.0125

-0.1 -2 0.07 -1.93 0.0095

0.14 0 -0.10 -0.10 0.0125

0.29 2.1 -0.20 1.90 0.01750.44 4.1 -0.30 3.80 0.0220

0.73 8.12 -0.50 7.62 0.0420

1.02 12.2 -0.70 11.50 0.0745

1.28 16.3 -0.88 15.42 0.1175

1.43 20.3 -0.98 19.32 0.1790

⑥ ⑦ ⑧ ⑨ ⑩

CDD cosαD sinαD CL cosαD

- - - - -

-0.0017 0.0108 0.99775 -0.06697 -0.37915

-0.0001 0.0094 0.99943 -0.03371 -0.09994

-0.0002 0.0123 1.00000 -0.00167 0.14000

-0.0010 0.0165 0.99945 0.03319 0.28984

-0.0023 0.0197 0.99780 0.06626 0.43903

-0.0064 0.0356 0.99117 0.13262 0.72355

-0.0124 0.0621 0.97992 0.19941 0.99951

-0.0195 0.0980 0.96398 0.26598 1.23389

-0.0244 0.1546 0.94367 0.33088 1.34945

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⑪ ⑫ ⑬ ⑭ ⑮

∝ CN CLsin ∝D CDcos ∝D C

- - - - -

-0.00072 -0.380 0.02545 0.01075 -0.0147

-0.00032 -0.100 0.00337 0.00938 0.0060

-0.00002 0.140 -0.00023 0.01227 0.0125

0.00055 0.290 0.00962 0.01649 0.00690.00130 0.440 0.02915 0.01965 -0.0095

0.00473 0.728 0.09681 0.03533 -0.0615

0.01238 1.012 0.20340 0.06085 -0.1425

0.02606 1.260 0.34045 0.09444 -0.2460

0.05116 1.401 0.47316 0.14592 -0.3272

⑯ ⑰ ⑱ ⑲ ⑳

.. C/ CA CD CD

- - - -

- - - 0.0072 0.0036

- - - 0.0005 0.0089

54.80 -0.04171 -0.04353 0.0010 0.0113

46.50 -0.06243 -0.06620 0.0042 0.0123

39.00 -0.06165 -0.06735 0.0096 0.0101

34.00 -0.06555 -0.07498 0.0264 0.0092

31.00 -0.06071 -0.07383 0.0516 0.0105

29.00 -0.05040 -0.06673 0.0813 0.0167

28.00 -0.04202 -0.06017 0.1014 0.0532

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CL

- -

0.40 0.0197

0.46 CD

0.60 0.0356

BY INTERPOLATION, AT CL = 0.46:

FOR CD:.−..−. = −.19

.3−.19

CD =0.02447

For

:

=

, at Maximum

Where: CL = 0.46

CD = 0.02447

CLCD

= 0.460.02447

= 18.799 1-8



For Vertical and Horizontal Stabilizer (NACA 0009)

Having a design layout cannot be started without the values for a number of factors and

considerations. These includes the airfoil(s), the wing and tail geometries, wing loading, thrust-

to-weight, estimated takeoff gross weight and fuel weight, estimated wing, tail, and engine sizes,and the required fuselage size.

This activity entitled “Wing Configuration” covers the selecting of the airfoil for the wingsand horizontal and vertical stabilizers that will suit the design of the aircraft.

The airfoil, according to Daniel P. Raymer, is the heart of an airplane. This airfoil affects

all the aspect that makes an aircraft fly. This airfoil is also the one responsible for creating lift

according to the Bernoulli’s principle in which the airfoil generates lift by changing velocity of the

air passing over and under itself.

A variety of airfoil has been developed for different purposes of aircraft. Choosing an

airfoil must consider factors such as the airfoil drag during cruise, stall and pitching-moment

characteristics, the thickness available for structure and fuel, and the ease of manufacture. With

today's computational airfoil design capabilities, it is becoming common for the airfoil shapes for

a wing to be custom-designed. Despite the fact, Zurcx777’s designer uses an existing airfoil forthe aircraft that comes closest to the desired characteristics of Zurcx777.

Again, with the help of Aircraft Design – A Conceptual Approach of Daniel P. Raymer, the

airfoil for the Zurcx777 had been chosen.

The NACA 2418 airfoil has a maximum camber of 2% located 40% (0.4 chords) from

the leading edge with a maximum thickness of 18% of the chord. Four-digit series airfoil by

default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge.

The designer considered the “design lift coefficient” for the initial airfoil selection. Theaircraft should be designed so that it flies the design mission at or near the design lift coefficient

to maximize the aerodynamic efficiency.

As the designer finished all the requirements for this activity, the appropriate airfoil

for the design has finally selected along with its airfoil characteristics.

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wing configuration

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