12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 100,000 Max Cl/Cd: 37.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk-il-100000-n5.txt Download as CSV file: xf-joukowsk-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 12% JOUKOWSKI AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9669 0.09262 0.08677 0.0035 1.0000 0.0442
-14.000 -1.0040 0.08160 0.07552 -0.0042 1.0000 0.0439
-13.750 -1.0326 0.07301 0.06668 -0.0102 1.0000 0.0440
-13.500 -1.0550 0.06612 0.05952 -0.0148 1.0000 0.0442
-13.250 -1.0738 0.06031 0.05341 -0.0183 1.0000 0.0446
-13.000 -1.0724 0.05740 0.05051 -0.0192 1.0000 0.0454
-12.750 -1.0743 0.05426 0.04729 -0.0203 1.0000 0.0461
-12.500 -1.0767 0.05124 0.04415 -0.0211 1.0000 0.0469
-12.250 -1.0792 0.04835 0.04110 -0.0216 1.0000 0.0478
-12.000 -1.0809 0.04568 0.03825 -0.0216 1.0000 0.0488
-11.750 -1.0817 0.04325 0.03559 -0.0209 1.0000 0.0501
-11.500 -1.0813 0.04103 0.03310 -0.0198 1.0000 0.0516
-11.250 -1.0736 0.03929 0.03131 -0.0187 1.0000 0.0530
-11.000 -1.0626 0.03782 0.02980 -0.0179 1.0000 0.0548
-10.750 -1.0504 0.03625 0.02812 -0.0171 1.0000 0.0568
-10.500 -1.0368 0.03465 0.02628 -0.0162 1.0000 0.0592
-10.250 -1.0219 0.03316 0.02469 -0.0154 1.0000 0.0616
-10.000 -1.0057 0.03193 0.02345 -0.0147 1.0000 0.0643
-9.750 -0.9881 0.03066 0.02205 -0.0140 1.0000 0.0677
-9.500 -0.9699 0.02939 0.02066 -0.0133 1.0000 0.0711
-9.250 -0.9512 0.02831 0.01957 -0.0126 1.0000 0.0749
-9.000 -0.9309 0.02724 0.01835 -0.0120 1.0000 0.0795
-8.750 -0.9112 0.02616 0.01729 -0.0114 1.0000 0.0840
-8.500 -0.8899 0.02523 0.01626 -0.0108 1.0000 0.0898
-8.250 -0.8688 0.02426 0.01529 -0.0103 1.0000 0.0956
-8.000 -0.8465 0.02343 0.01438 -0.0098 1.0000 0.1031
-7.750 -0.8246 0.02255 0.01354 -0.0093 1.0000 0.1105
-7.500 -0.8016 0.02177 0.01271 -0.0088 1.0000 0.1198
-7.250 -0.7783 0.02104 0.01196 -0.0084 1.0000 0.1300
-7.000 -0.7551 0.02031 0.01128 -0.0080 1.0000 0.1412
-6.750 -0.7312 0.01964 0.01062 -0.0076 1.0000 0.1537
-6.500 -0.7071 0.01901 0.01003 -0.0072 1.0000 0.1678
-6.250 -0.6827 0.01843 0.00948 -0.0069 1.0000 0.1831
-6.000 -0.6580 0.01788 0.00896 -0.0065 1.0000 0.1999
-5.750 -0.6331 0.01738 0.00850 -0.0062 1.0000 0.2177
-5.500 -0.6081 0.01691 0.00807 -0.0059 1.0000 0.2368
-5.250 -0.5830 0.01647 0.00769 -0.0055 1.0000 0.2561
-5.000 -0.5580 0.01605 0.00736 -0.0051 1.0000 0.2760
-4.750 -0.5330 0.01568 0.00705 -0.0047 1.0000 0.2967
-4.500 -0.5079 0.01534 0.00676 -0.0043 1.0000 0.3178
-4.250 -0.4833 0.01501 0.00652 -0.0038 1.0000 0.3383
-4.000 -0.4592 0.01472 0.00632 -0.0033 1.0000 0.3589
-3.750 -0.4358 0.01445 0.00615 -0.0026 1.0000 0.3795
-3.250 -0.3693 0.01405 0.00590 -0.0051 0.9704 0.4257
-3.000 -0.3309 0.01390 0.00579 -0.0071 0.9478 0.4500
-2.750 -0.2942 0.01377 0.00572 -0.0086 0.9257 0.4728
-2.500 -0.2619 0.01367 0.00566 -0.0091 0.9019 0.4946
-2.250 -0.2321 0.01359 0.00559 -0.0089 0.8789 0.5158
-2.000 -0.2049 0.01353 0.00553 -0.0083 0.8561 0.5362
-1.750 -0.1790 0.01347 0.00549 -0.0073 0.8337 0.5555
-1.500 -0.1536 0.01342 0.00544 -0.0062 0.8124 0.5749
-1.250 -0.1282 0.01338 0.00540 -0.0051 0.7920 0.5943
-1.000 -0.1027 0.01334 0.00537 -0.0040 0.7711 0.6138
-0.750 -0.0771 0.01331 0.00534 -0.0030 0.7507 0.6333
-0.500 -0.0514 0.01329 0.00532 -0.0020 0.7308 0.6529
-0.250 -0.0257 0.01328 0.00530 -0.0010 0.7111 0.6727
0.000 0.0000 0.01327 0.00529 0.0000 0.6918 0.6917
0.250 0.0257 0.01328 0.00530 0.0010 0.6726 0.7111
0.500 0.0514 0.01329 0.00532 0.0020 0.6529 0.7307
0.750 0.0771 0.01331 0.00534 0.0030 0.6334 0.7507
1.000 0.1027 0.01334 0.00537 0.0040 0.6138 0.7711
1.250 0.1282 0.01338 0.00540 0.0051 0.5943 0.7920
1.500 0.1536 0.01342 0.00544 0.0062 0.5750 0.8124
1.750 0.1790 0.01347 0.00549 0.0073 0.5556 0.8337
2.000 0.2049 0.01353 0.00553 0.0083 0.5362 0.8561
2.250 0.2321 0.01359 0.00559 0.0089 0.5158 0.8789
2.500 0.2619 0.01367 0.00566 0.0091 0.4945 0.9019
2.750 0.2942 0.01377 0.00572 0.0086 0.4728 0.9257
3.000 0.3309 0.01390 0.00579 0.0071 0.4501 0.9478
3.250 0.3693 0.01405 0.00590 0.0051 0.4256 0.9705
3.750 0.4358 0.01445 0.00615 0.0026 0.3795 1.0000
4.000 0.4592 0.01472 0.00632 0.0033 0.3589 1.0000
4.250 0.4833 0.01501 0.00652 0.0038 0.3383 1.0000
4.500 0.5079 0.01534 0.00676 0.0043 0.3178 1.0000
4.750 0.5330 0.01568 0.00705 0.0047 0.2967 1.0000
5.000 0.5580 0.01605 0.00736 0.0051 0.2760 1.0000
5.250 0.5830 0.01647 0.00769 0.0055 0.2561 1.0000
5.500 0.6080 0.01691 0.00807 0.0059 0.2368 1.0000
5.750 0.6331 0.01738 0.00850 0.0062 0.2177 1.0000
6.000 0.6580 0.01788 0.00896 0.0065 0.1999 1.0000
6.250 0.6826 0.01843 0.00948 0.0069 0.1831 1.0000
6.500 0.7071 0.01901 0.01003 0.0072 0.1678 1.0000
6.750 0.7312 0.01964 0.01062 0.0076 0.1537 1.0000
7.000 0.7550 0.02031 0.01128 0.0080 0.1412 1.0000
7.250 0.7783 0.02104 0.01196 0.0084 0.1300 1.0000
7.500 0.8015 0.02177 0.01271 0.0088 0.1198 1.0000
7.750 0.8246 0.02255 0.01354 0.0093 0.1106 1.0000
8.000 0.8465 0.02342 0.01438 0.0098 0.1031 1.0000
8.250 0.8688 0.02426 0.01528 0.0103 0.0956 1.0000
8.500 0.8899 0.02523 0.01626 0.0108 0.0898 1.0000
8.750 0.9111 0.02616 0.01728 0.0114 0.0839 1.0000
9.000 0.9308 0.02724 0.01835 0.0120 0.0795 1.0000
9.250 0.9511 0.02830 0.01956 0.0127 0.0748 1.0000
9.500 0.9698 0.02939 0.02065 0.0133 0.0711 1.0000
9.750 0.9880 0.03066 0.02204 0.0140 0.0677 1.0000
10.000 1.0056 0.03193 0.02345 0.0147 0.0643 1.0000
10.250 1.0219 0.03316 0.02469 0.0154 0.0617 1.0000
10.500 1.0367 0.03464 0.02628 0.0162 0.0592 1.0000
10.750 1.0503 0.03624 0.02811 0.0171 0.0568 1.0000
11.000 1.0624 0.03780 0.02978 0.0179 0.0547 1.0000
11.250 1.0733 0.03927 0.03128 0.0188 0.0530 1.0000
11.500 1.0811 0.04101 0.03308 0.0198 0.0516 1.0000
11.750 1.0813 0.04324 0.03559 0.0210 0.0501 1.0000
12.000 1.0807 0.04566 0.03822 0.0216 0.0488 1.0000
12.250 1.0791 0.04832 0.04106 0.0217 0.0478 1.0000
12.500 1.0767 0.05120 0.04411 0.0212 0.0469 1.0000
12.750 1.0746 0.05419 0.04720 0.0203 0.0461 1.0000
13.000 1.0733 0.05724 0.05033 0.0193 0.0454 1.0000
13.250 1.0733 0.06034 0.05344 0.0182 0.0446 1.0000
13.500 1.0550 0.06606 0.05946 0.0149 0.0442 1.0000
13.750 1.0324 0.07299 0.06666 0.0103 0.0440 1.0000
14.000 1.0039 0.08154 0.07547 0.0043 0.0439 1.0000
14.250 0.9658 0.09275 0.08691 -0.0037 0.0441 1.0000
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