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Camber New

The document presents observations related to the performance of a cambered airfoil (NACA 2412) at various angles of attack, detailing parameters such as freestream velocity, motor speed, air density, and dynamic pressure. It includes data on pressure distribution, pressure coefficients, and lift and drag coefficients across different measurement ports. The results illustrate the aerodynamic characteristics of the airfoil under specified conditions.

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12 Dhanya Shri
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12 views13 pages

Camber New

The document presents observations related to the performance of a cambered airfoil (NACA 2412) at various angles of attack, detailing parameters such as freestream velocity, motor speed, air density, and dynamic pressure. It includes data on pressure distribution, pressure coefficients, and lift and drag coefficients across different measurement ports. The results illustrate the aerodynamic characteristics of the airfoil under specified conditions.

Uploaded by

12 Dhanya Shri
Copyright
© © All Rights Reserved
We take content rights seriously. If you suspect this is your content, claim it here.
Available Formats
Download as XLSX, PDF, TXT or read online on Scribd
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Observations

Freestream velocity in m/sec = 23.2


Motor Speed in RPM = 900
Air density(at the altitude 920m) in kg/m3= 1.133
Manometer liquid (water) density in kg/m3 = 1000
Acceleration due to gravity m/sec2 = 9.81
Dynamic Pressure in N/m2 304.91
Chord length in m = 0.204

Location of Port from LE


Port number x/C hinfinity
(x) in m
1 0.0200 0.098 26.6
2 0.046 0.225 26.6
3 0.065 0.319 26.6
4 0.085 0.417 26.6
5 0.11 0.539 26.6
6 0.133 0.652 26.6
7 0.161 0.789 26.6
8 0.164 0.804 26.6
9 0.134 0.657 26.6
10 0.109 0.534 26.6
11 0.084 0.412 26.6
12 0.064 0.314 26.6
13 0.044 0.216 26.6
14 0.02 0.098 26.6
15 0 0.000 26.6

Angle of Attack Cpl Cpu Del Cp


-0.6113 -0.6435 0.0322
-0.4504 -0.6435 0.1930
-0.3861 -0.5148 0.1287
0 -0.3217 -0.5791 0.2574
-0.1930 -0.5469 0.3539
-0.0965 -0.4826 0.3861
0.0322 -0.2896 0.3217
-0.3217 -0.9008 0.5791
-0.2574 -0.8687 0.6113
-0.2252 -0.7078 0.4826
2 -0.1287 -0.6756 0.5469
-0.0643 -0.5791 0.5148
0.0000 -0.4504 0.4504
0.0643 -0.2252 0.2896
-0.1287 -0.9652 0.8365
-0.3217 -0.8687 0.5469

3
-0.2896 -0.7078 0.4183
3 -0.2574 -0.7400 0.4826
-0.1609 -0.6113 0.4504
-0.0965 -0.5148 0.4183
0.0643 -0.3217 0.3861
-0.0965 -1.1261 1.0295
-0.0643 -1.0295 0.9652
-0.0965 -0.7722 0.6756
4 -0.0643 -0.6756 0.6113
0.0000 -0.5791 0.5791
0.0322 -0.4183 0.4504
0.0965 -0.1930 0.2896
-0.0322 -1.4800 1.4478
-0.0643 -1.2226 1.1582
-0.1287 -0.7722 0.6435
6 -0.1287 -0.8365 0.7078
-0.0643 -0.6756 0.6113
-0.0322 -0.5791 0.5469
0.0965 -0.3217 0.4183
0.2574 -1.8017 2.0591
0.1287 -1.5121 1.6408
0.0643 -0.9008 0.9652
9 0.0322 -0.8687 0.9008
0.0322 -0.7400 0.7722
0.0322 -0.5469 0.5791
0.1287 -0.2574 0.3861
0.4504 -1.8339 2.2843
0.3217 -1.3513 1.6730
0.2574 -0.9330 1.1904
10 0.1930 -0.7722 0.9652
0.1930 -0.6113 0.8043
0.1930 -0.3861 0.5791
0.1930 -0.0643 0.2574
0.5469 -2.0913 2.6382
0.0643 -1.4800 1.5443
0.1609 -1.0295 1.1904
12 0.0322 -0.9008 0.9330
0.0965 -0.7400 0.8365
0.0322 -0.4826 0.5148
0.1609 -0.1930 0.3539
0.6435 -2.0913 2.7347
0.4504 -1.5765 2.0269
0.3217 -1.0617 1.3834
14 0.2252 -0.8365 1.0617
0.1930 -0.5791 0.7722
0.1609 -0.2574 0.4183
0.1609 0.0000 0.1609
0.6435 -2.3486 2.9921

15
0.3861 -1.5443 1.9304
0.2896 -1.0295 1.3191
15 0.1930 -0.8043 0.9974
0.1287 -0.5148 0.6435
0.0965 -0.3217 0.4183
0.1930 -0.2252 0.4183
Pressure distribution over a Cambered airfoil
Airfoil: NACA 2412

Angle of Attack in Degree


hi 0 2 3 4 6 9 10
28.6 29.4 29.6 30.1 31.2 32.2 32.3
28.6 29.3 29.3 29.8 30.4 31.3 30.8
28.2 28.8 28.8 29 29 29.4 29.5
28.4 28.7 28.9 28.7 29.2 29.3 29
28.3 28.4 28.5 28.4 28.7 28.9 28.5
28.1 28 28.2 27.9 28.4 28.3 27.8
27.5 27.3 27.6 27.2 27.6 27.4 26.8
26.5 26.4 26.4 26.3 26.3 26.2 26
26.9 26.6 26.9 26.5 26.7 26.5 26
27.2 26.8 27.1 26.6 26.8 26.5 26
27.6 27 27.4 26.8 27 26.5 26
27.8 27.3 27.5 26.9 27 26.4 25.8
28 27.4 27.6 26.8 26.8 26.2 25.6
28.5 27.6 27 26.9 26.7 25.8 25.2
23.3 23.4 23.8 24.4 26 28.7 29.7

D(x/c) Del Cp D(x/c) Cn Cl Cd


0.0980 0.0032 0.1960 0.1960 0.0000
0.1274 0.0246
0.0932 0.0120
0.0981 0.0252
0.1225 0.0434
0.1127 0.0435
0.1373 0.0442
0.0980 0.0568 0.3868 0.3868 0.0135
0.1274 0.0779
0.0932 0.0450
0.0981 0.0537
0.1225 0.0631
0.1127 0.0508
0.1373 0.0398
0.0980 0.0820 0.3933 0.3928 0.0206
0.1274 0.0697
0.0932 0.0390
0.0981 0.0473
0.1225 0.0552
0.1127 0.0471
0.1373 0.0530
0.0980 0.1009 0.5083 0.5070 0.0355
0.1274 0.1230
0.0932 0.0630
0.0981 0.0600
0.1225 0.0709
0.1127 0.0508
0.1373 0.0398
0.0980 0.1419 0.6128 0.6094 0.0641
0.1274 0.1476
0.0932 0.0600
0.0981 0.0694
0.1225 0.0749
0.1127 0.0616
0.1373 0.0574
0.0980 0.2018 0.8020 0.7921 0.1255
0.1274 0.2090
0.0932 0.0900
0.0981 0.0884
0.1225 0.0946
0.1127 0.0653
0.1373 0.0530
0.0980 0.2239 0.8418 0.8290 0.1462
0.1274 0.2131
0.0932 0.1109
0.0981 0.0947
0.1225 0.0985
0.1127 0.0653
0.1373 0.0353
0.0980 0.2585 0.8668 0.8479 0.1802
0.1274 0.1967
0.0932 0.1109
0.0981 0.0915
0.1225 0.1025
0.1127 0.0580
0.1373 0.0486
0.0980 0.2680 0.9231 0.8957 0.2234
0.1274 0.2582
0.0932 0.1289
0.0981 0.1042
0.1225 0.0946
0.1127 0.0471
0.1373 0.0221
0.0980 0.2932 0.9433 0.9112 0.2442
0.1274 0.2459
0.0932 0.1229
0.0981 0.0978
0.1225 0.0788
0.1127 0.0471
0.1373 0.0574
er a Cambered airfoil

Pressure Coefficient Cp
12 14 15 Cp(0) Cp(2) Cp(3) Cp(4)
33.1 33.1 33.9 -0.643 -0.901 -0.965 -1.126
31.2 31.5 31.4 -0.643 -0.869 -0.869 -1.030
29.8 29.9 29.8 -0.515 -0.708 -0.708 -0.772
29.4 29.2 29.1 -0.579 -0.676 -0.740 -0.676
28.9 28.4 28.2 -0.547 -0.579 -0.611 -0.579
28.1 27.4 27.6 -0.483 -0.450 -0.515 -0.418
27.2 26.6 27.3 -0.290 -0.225 -0.322 -0.193
26.1 26.1 26 0.032 0.064 0.064 0.097
26.5 26.1 26.3 -0.097 0.000 -0.097 0.032
26.3 26 26.2 -0.193 -0.064 -0.161 0.000
26.5 25.9 26 -0.322 -0.129 -0.257 -0.064
26.1 25.6 25.7 -0.386 -0.225 -0.290 -0.097
26.4 25.2 25.4 -0.450 -0.257 -0.322 -0.064
24.9 24.6 24.6 -0.611 -0.322 -0.129 -0.097
32.6 33.6 36.6 1.062 1.030 0.901 0.708

AoA in AoA in Coefficient Coefficient


L/D
degree radian of Lift of Drag
0 0 0.19602758 0 0
2 0.03491111 0.38684311 0.01350238 28.649995
3 0.05236667 0.39276432 0.02058658 19.0786584
4 0.06982222 0.5070196 0.03545888 14.2988062
6 0.10473333 0.60944028 0.06406312 9.51312189
9 0.1571 0.7921475 0.12548038 6.31291934
10 0.17455556 0.8289761 0.1461902 5.67053142
12 0.20946667 0.84789283 0.18024925 4.70400197
14 0.24437778 0.89570547 0.2233546 4.01023966
15 0.26183333 0.91117409 0.24418151 3.73154413
Pressure Coefficient Cp
Cp(6) Cp(9) Cp(10) Cp(12) Cp(14) Cp(15)
-1.480 -1.802 -1.834 -2.091 -2.091 -2.349
-1.223 -1.512 -1.351 -1.480 -1.576 -1.544
-0.772 -0.901 -0.933 -1.030 -1.062 -1.030
-0.837 -0.869 -0.772 -0.901 -0.837 -0.804
-0.676 -0.740 -0.611 -0.740 -0.579 -0.515
-0.579 -0.547 -0.386 -0.483 -0.257 -0.322
-0.322 -0.257 -0.064 -0.193 0.000 -0.225
0.097 0.129 0.193 0.161 0.161 0.193
-0.032 0.032 0.193 0.032 0.161 0.097
-0.064 0.032 0.193 0.097 0.193 0.129
-0.129 0.032 0.193 0.032 0.225 0.193
-0.129 0.064 0.257 0.161 0.322 0.290
-0.064 0.129 0.322 0.064 0.450 0.386
-0.032 0.257 0.450 0.547 0.643 0.643
0.193 -0.676 -0.997 -1.930 -2.252 -3.217

Lift Curve
1

0.9

0.8

0.7
Coefficient of lift

0.6

0.5

0.4

0.3

0.2

0.1

0
0 2 4 6 8 10 12 14 16

AoA
0.1

0
0 2 4 6 8 10 12 14 16

AoA

L/D Curve
35

30

25

20
L/D Ratio

15

10

0
0 2 4 6 8 10 12 14 16

Angle of Attack

Drag Curve
0.3

0.25

0.2
Coefficient of drag

0.15

0.1

0.05

0
0 2 4 6 8 10 12 14 16

Angle of Attack
0.05

0
0 2 4 6 8 10 12 14 16

Angle of Attack

0.800 1.000 1.200 1.400 1.600 1.800 2.000


0

0.2

0.4

0.6

0.8

1.2
14 16
14 16

14 16

14 16
14 16

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