Download Solution Exercise Sheet 1 Mec 3707 PDF

TitleSolution Exercise Sheet 1 Mec 3707
File Size60.0 KB
Total Pages5
Document Text Contents
Page 3

0

0

0

0

0512.01

5.6

045.1
1

188.4
a

a

a

a

+
=

















+

=→

π



rada /33.5
0

=→


Since the airfoil section is the same for both wings, a0 is a constant



* Lift slop for the wing with AR=8.5



reerada

a

deg/0763.0/37.4

)095.01)(
)5.8(

33.5
(1

33.5

==→

++

=

π



• Calculate CL For the wing with AR=8.5


( ) ( ) 565.0)3(4.40763.0
0

=−−=−=
=

��

lL
aC αα



Induced drag for wing with AR=8.5



( )
( ) ( )

( )
0131.0

5.8

095.1565.0
1

22

,
==+=

π
δ

πAR

C
C L

iD



Q2.

First solve the angle of attack and the profile drag coefficient, which say the same in this

problem



deg/radian= 180/π= 57.3



2.40732.0
79.0

3.5711.0
1

3.5711.0

35.0

1

1

0

0

1

0

0

==








××

×
+

×

=







+=→

+

==

radian

eAR

a

a

C

ARe

a

a
aC L

L

π

π
α

π

αα





The profile drag can be obtained as follows

012.0
29

35.0
==











=

D

L

L

D

C

C

C
C

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