aerofoil reort

8/18/2019 Aerofoil Reort

1/21

Preesure (Pascal)

Angle of Attack (deg)ProbeNumber

x/c 0 2 6 10 15

1 0 110 299 960 1555 615

20.016

510 !50 122 56 9"

! 0.0! 611 "!2 1!05 1695 6#

# 0.0 621 #"# 259 160 215

5 0.10# 6! 90 1066 1152 656

6 0.1! 6#! 5#" !6 2"0 !26

0.16 6## 66 921 1015 6##

" 0.202 6!# 55 #0 !!6 !"!

9 0.2!! 62# 15 "29 "91 6##

10 0.265 611 55! #!0 !66 #1#11 0.29 600 6"6 66 "0! 6#1

12 0.!!1 596 5#" ##0 !9# ##0

1! 0.!9 566 6!0 69! 05 6#2

1# 0.5 550 516 ## #19 #"0

15 0.6 510 5!6 5 565 6#"

16 0.!1 #"5 # #!0 #29 52"

1 0."02 ##" #5 #91 #2 661

1" 0."!5 #6! #6! #26 ##2 50

19 0." #2# ##6 #59 #52 661

20 0.902 #!5 #!" #16 #!6 5""P $n% & #!.#mm of 'g

P stag &110 Pascal


2/21

Angle of Attack (deg) 0 2 6 10 16

SL.No

x(m

m)

x/c PI(P

a) Cp

Cp*(x/c)

Cp Cp*(x/

c) Cp

Cp*(x/

c) Cp

Cp*(x/

c) Cp

Cp*(x/

c)

1 0 0 110 1 00.9"9

"0

0."#99

090

0.##"

#50

0.910"

2"0

! 5.60.0!

611

0.9115!#

0.0!!2

0."25

11

0.0!22

"!

0.""9

"9

0.0291

9!

0.201

2#

0.0266

#5

0.9051

"

0.0!!#

92

5 15.60.10

#6!

0.9069#!

0.09#!22

0."99

2

0.0915

12

0."!11

92

0.0"6#

##

0."160

06

0.0"#"

65

0.90!5

""

0.09!9

!

25.10.16

6##

0.9050

0.15125!

0.""#1

65

0.1#6

56

0."56

95

0.1#!0

"5

0."#01

9

0.1#0!

1!

0.905

0

0.1512

5!

9 !#.90.2!

!62#

0.9092!9

0.211"5!

0."9!1

0.20"1

09

0."!0

#1

0.20!#

1"

0."620

9!

0.200"

6"

0.905

0

0.2110

!

11 ##.60.29

600

0.91!#

0.21!0!

0."9"2

91

0.266

92

0.""#1

65

0.2625

9

0."6

!2

0.2606

5

0.9062

!

0.2691

52

1! 59.60.!9

566

0.919#"

0.!650!#

0.90"1

"

0.!605

#

0."90

55

0.!561

!1

0."9#9

!6

0.!552

9

0.9060

61

0.!59

06

15 90 0.6 5100.929!

690.556

21

0.92#

"

0.55#"

6

0.915

!"

0.5505

2!

0.9196

5

0.551

9#

0.9050

01

0.5#!0

01

1 120.!

0."02

##" 0.9#0!1

0.5#1!#

0.9!55#9

0.50!1

0.9!22#

0.#"0#5

0.9!609

0.50!5

0.90206

0.2!9

191!0.

50." #2#

0.9##555

0."2162

0.9#06

0."1"!

"!

0.9!"!

#

0."16!

"6

0.9!96

1

0."1#

61

0.902

06

0."5!

5#

2 2.5 0.01 510 0.929! 0.0155 0.956 0.0159 0.99" 0.0166 1.0095 0.016" 1.0021 0.016


3/21

6 69 2 21 92 "1 65 !5 59 19 !5

# 10.5 0.0 6210.909

690.06!6

"#

0.9!!9

6

0.065!

0.9!6

9

0.06"1

5"

0.9911

1

0.069!

"2

0.9"1#

59

0.06"

02

6 20.50.1!

6#!0.905"

"#0.12#1

06

0.9226

59

0.126#

0#

0.95#6

19

0.1!0

"!

0.9699

"2

0.1!2"

""

0.9615

06

0.1!1

26

" !0.!0.20

26!#

0.90#!

0.1"!!1

0.9210

0.1"60

56

0.9#5

56

0.191#

06

0.9600

9!

0.19!9

!9

0.951

9#

0.1922

62

10 !9.0.26

5611

0.9115!#

0.2#155

0.921

6

0.2##2

1

0.9#!#

95

0.2500

26

0.95#

96

0.25!0

21

0.9#6!

2

0.250

5

12 #9.60.!!

1596

0.91#1"!

0.!02595

0.9226

590.!05#

0.9#1

29

0.!11

12

0.9#9"

52

0.!1##

01

0.9#1

29

0.!11

12

1# 5 0.5 5500.922!

06

0.#611

5!

0.92"!

09

0.#6#1

55

0.9#0#

9!

0.#02

#

0.9#5#

!

0.#2

19

0.9!#6

66

0.#6!

!!

16109.

0.!

1#"5

0.9!!"!

0.6"2596

0.9#0#

9!

0.6"5

01

0.9#!#

95

0.6"96

95

0.9#!6

2

0.6"9"

2#

0.9261

9

0.60

#5

1"125.

20."!

5#6!

0.9!66"

0."295!

0.9!6

6"

0."29

5!

0.9##2

01

0.""#

0"

0.9#1!

6

0."60

#9

0.91"

#

0.61

6

201!5.

!0.90

2#!5

0.9#2612

0."502!6

0.9#20

"2

0."#9

5"

0.9#59

6

0."5!2

62

0.9#2#

!6

0."500

0.9155

96

0."25"

6


4/21


5/21

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."

1

, x/c -s x/c for Angle of Attack 0 deg

o+er s$de of

aerofo$l

er s$de of

aerofo$l

c/x

, x/c


6/21

0 0.2 0.# 0.6 0." 10."

0."5

0.9

0.95

1

*s x/c for Angle of Attack 2 deg

At lo+er s$de ofaerofo$l

At uer s $de of

aerofo$l

x/c

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."

1


o+er s$de of

aerofo$l

er s$de of

aerofo$l

c/x

, x/c


7/21

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."1

1.2


At lo+er s$de of

aerofo$l

At uer s $de of

aerofo$l

x/c


8/21

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."

1


o+er s$de ofaerofo$l

er s$de of

aerofo$l

c/x

, x/c


9/21


10/21


11/21


12/21


13/21

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."

1

1.2


At lo+er s$de of

aerofo$l

At uer s $de ofaerofo$l

x/c


14/21

0 0.2 0.# 0.6 0." 10

0.2

0.#

0.6

0."

1

() , x/c -s x/c for Angle of Attack 10 deg

o+er s$de of

aerofo$l

er s$de of

aerofo$l

c/x

() , x/c


15/21


16/21


17/21


18/21

0.

0.

1.

() , x

() , x/


19/21

Angleof

Attac

k (deg)

Coec!ent of P!tc"!

ng#oment Cm

0 0.025

2 0.0!09

6 0.0!"#

10 0.0!9

15 0.0!62

Angle of Attack A$A

(deg)

Coec!ent

of L!ft(Cl)

0 0.012#

2 0.0!1

6 0.06#1

10 0.0"

15 0.0#5"tall Angle & 10

deg


20/21


21/21

0 2 # 6 " 10 12 1# 160

0.01

0.02

0.0!

0.0#

0.05

AA *s m

AA(deg)

m

aerofoil reort

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