12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 200,000 Max Cl/Cd: 47.82 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk-il-200000.txt Download as CSV file: xf-joukowsk-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9787 0.09874 0.09467 0.0061 1.0000 0.0444
-14.500 -1.0214 0.08641 0.08215 -0.0027 1.0000 0.0440
-14.250 -1.0561 0.07670 0.07223 -0.0096 1.0000 0.0436
-14.000 -1.0865 0.06866 0.06396 -0.0153 1.0000 0.0435
-13.750 -1.1121 0.06212 0.05717 -0.0194 1.0000 0.0434
-13.500 -1.1334 0.05685 0.05166 -0.0221 1.0000 0.0436
-13.250 -1.1517 0.05248 0.04703 -0.0235 1.0000 0.0438
-13.000 -1.1679 0.04896 0.04324 -0.0237 1.0000 0.0441
-12.750 -1.1808 0.04620 0.04021 -0.0225 1.0000 0.0444
-12.500 -1.1887 0.04346 0.03722 -0.0207 1.0000 0.0448
-12.250 -1.1777 0.04088 0.03462 -0.0201 1.0000 0.0459
-12.000 -1.1660 0.03934 0.03304 -0.0192 1.0000 0.0471
-11.750 -1.1559 0.03776 0.03134 -0.0182 1.0000 0.0485
-11.500 -1.1449 0.03608 0.02945 -0.0172 1.0000 0.0500
-11.250 -1.1335 0.03441 0.02748 -0.0160 1.0000 0.0515
-11.000 -1.1179 0.03217 0.02511 -0.0153 1.0000 0.0531
-10.750 -1.0986 0.03082 0.02378 -0.0147 1.0000 0.0549
-10.500 -1.0799 0.02968 0.02255 -0.0140 1.0000 0.0571
-10.250 -1.0610 0.02854 0.02119 -0.0133 1.0000 0.0596
-10.000 -1.0413 0.02685 0.01944 -0.0126 1.0000 0.0622
-9.750 -1.0201 0.02581 0.01843 -0.0121 1.0000 0.0649
-9.500 -0.9986 0.02487 0.01736 -0.0115 1.0000 0.0683
-9.250 -0.9774 0.02356 0.01599 -0.0109 1.0000 0.0719
-9.000 -0.9551 0.02268 0.01514 -0.0103 1.0000 0.0758
-8.750 -0.9317 0.02195 0.01424 -0.0098 1.0000 0.0803
-8.500 -0.9100 0.02076 0.01317 -0.0093 1.0000 0.0855
-8.250 -0.8859 0.02009 0.01239 -0.0088 1.0000 0.0914
-8.000 -0.8634 0.01909 0.01148 -0.0083 1.0000 0.0980
-7.750 -0.8391 0.01839 0.01072 -0.0078 1.0000 0.1058
-7.500 -0.8155 0.01763 0.01002 -0.0074 1.0000 0.1146
-7.250 -0.7915 0.01688 0.00931 -0.0070 1.0000 0.1247
-7.000 -0.7670 0.01621 0.00868 -0.0066 1.0000 0.1364
-6.750 -0.7421 0.01560 0.00810 -0.0063 1.0000 0.1499
-6.500 -0.7171 0.01501 0.00758 -0.0060 1.0000 0.1649
-6.250 -0.6919 0.01447 0.00712 -0.0057 1.0000 0.1817
-6.000 -0.6664 0.01397 0.00669 -0.0054 1.0000 0.2001
-5.750 -0.6405 0.01353 0.00630 -0.0051 1.0000 0.2202
-5.500 -0.6148 0.01309 0.00596 -0.0049 1.0000 0.2407
-5.250 -0.5891 0.01269 0.00566 -0.0046 1.0000 0.2619
-5.000 -0.5631 0.01235 0.00538 -0.0043 1.0000 0.2843
-4.750 -0.5374 0.01202 0.00515 -0.0040 1.0000 0.3061
-4.500 -0.5120 0.01171 0.00495 -0.0036 1.0000 0.3281
-4.250 -0.4871 0.01146 0.00476 -0.0032 1.0000 0.3505
-4.000 -0.4639 0.01121 0.00462 -0.0024 1.0000 0.3715
-3.750 -0.4432 0.01101 0.00452 -0.0013 1.0000 0.3917
-3.500 -0.4167 0.01086 0.00445 -0.0015 0.9959 0.4141
-3.250 -0.3696 0.01069 0.00440 -0.0054 0.9827 0.4414
-3.000 -0.3259 0.01057 0.00432 -0.0085 0.9659 0.4680
-2.750 -0.2860 0.01043 0.00429 -0.0106 0.9466 0.4915
-2.500 -0.2521 0.01035 0.00426 -0.0113 0.9254 0.5142
-2.250 -0.2256 0.01031 0.00422 -0.0104 0.9007 0.5353
-2.000 -0.2016 0.01026 0.00420 -0.0090 0.8781 0.5547
-1.750 -0.1777 0.01022 0.00417 -0.0075 0.8556 0.5740
-1.500 -0.1534 0.01018 0.00414 -0.0062 0.8336 0.5936
-1.250 -0.1287 0.01015 0.00411 -0.0049 0.8128 0.6133
-1.000 -0.1036 0.01014 0.00407 -0.0038 0.7928 0.6332
-0.750 -0.0778 0.01012 0.00405 -0.0028 0.7722 0.6534
-0.500 -0.0518 0.01010 0.00403 -0.0019 0.7517 0.6731
-0.250 -0.0259 0.01008 0.00403 -0.0009 0.7316 0.6924
0.000 0.0000 0.01008 0.00403 0.0000 0.7119 0.7119
0.250 0.0259 0.01008 0.00403 0.0010 0.6924 0.7316
0.500 0.0518 0.01010 0.00403 0.0019 0.6731 0.7517
0.750 0.0778 0.01012 0.00405 0.0028 0.6534 0.7722
1.000 0.1036 0.01014 0.00407 0.0038 0.6332 0.7928
1.250 0.1287 0.01015 0.00411 0.0049 0.6133 0.8128
1.500 0.1534 0.01018 0.00414 0.0062 0.5936 0.8336
1.750 0.1777 0.01022 0.00417 0.0075 0.5741 0.8555
2.000 0.2016 0.01026 0.00420 0.0090 0.5547 0.8781
2.250 0.2256 0.01031 0.00422 0.0104 0.5353 0.9007
2.500 0.2521 0.01035 0.00426 0.0113 0.5142 0.9254
2.750 0.2860 0.01043 0.00429 0.0106 0.4915 0.9466
3.000 0.3258 0.01057 0.00432 0.0085 0.4680 0.9658
3.250 0.3695 0.01069 0.00440 0.0054 0.4413 0.9827
3.500 0.4168 0.01086 0.00445 0.0015 0.4141 0.9959
3.750 0.4432 0.01101 0.00452 0.0013 0.3917 1.0000
4.000 0.4639 0.01121 0.00462 0.0024 0.3714 1.0000
4.250 0.4871 0.01146 0.00476 0.0032 0.3505 1.0000
4.500 0.5120 0.01171 0.00495 0.0036 0.3281 1.0000
4.750 0.5374 0.01201 0.00515 0.0040 0.3060 1.0000
5.000 0.5631 0.01235 0.00538 0.0043 0.2844 1.0000
5.250 0.5891 0.01269 0.00566 0.0046 0.2619 1.0000
5.500 0.6148 0.01309 0.00596 0.0049 0.2407 1.0000
5.750 0.6405 0.01353 0.00630 0.0051 0.2202 1.0000
6.000 0.6664 0.01397 0.00669 0.0054 0.2001 1.0000
6.250 0.6919 0.01447 0.00712 0.0057 0.1817 1.0000
6.500 0.7171 0.01501 0.00758 0.0060 0.1649 1.0000
6.750 0.7421 0.01560 0.00810 0.0063 0.1499 1.0000
7.000 0.7670 0.01621 0.00868 0.0066 0.1364 1.0000
7.250 0.7915 0.01688 0.00932 0.0070 0.1247 1.0000
7.500 0.8154 0.01763 0.01002 0.0074 0.1147 1.0000
7.750 0.8391 0.01839 0.01072 0.0078 0.1058 1.0000
8.000 0.8634 0.01909 0.01148 0.0083 0.0980 1.0000
8.250 0.8859 0.02009 0.01239 0.0088 0.0915 1.0000
8.500 0.9099 0.02076 0.01317 0.0093 0.0855 1.0000
8.750 0.9316 0.02194 0.01424 0.0098 0.0803 1.0000
9.000 0.9550 0.02267 0.01513 0.0104 0.0759 1.0000
9.250 0.9772 0.02356 0.01599 0.0109 0.0719 1.0000
9.500 0.9985 0.02486 0.01735 0.0115 0.0683 1.0000
9.750 1.0200 0.02580 0.01842 0.0121 0.0649 1.0000
10.000 1.0413 0.02685 0.01944 0.0127 0.0621 1.0000
10.250 1.0609 0.02853 0.02118 0.0133 0.0596 1.0000
10.500 1.0798 0.02968 0.02255 0.0141 0.0571 1.0000
10.750 1.0984 0.03081 0.02377 0.0148 0.0549 1.0000
11.000 1.1176 0.03217 0.02510 0.0154 0.0530 1.0000
11.250 1.1330 0.03439 0.02746 0.0161 0.0514 1.0000
11.500 1.1446 0.03606 0.02943 0.0172 0.0500 1.0000
11.750 1.1556 0.03774 0.03132 0.0183 0.0484 1.0000
12.000 1.1658 0.03933 0.03303 0.0193 0.0471 1.0000
12.250 1.1777 0.04085 0.03458 0.0201 0.0459 1.0000
12.500 1.1885 0.04346 0.03722 0.0207 0.0448 1.0000
12.750 1.1803 0.04617 0.04018 0.0226 0.0443 1.0000
13.000 1.1674 0.04898 0.04326 0.0237 0.0441 1.0000
13.250 1.1515 0.05249 0.04704 0.0236 0.0438 1.0000
13.500 1.1330 0.05678 0.05159 0.0221 0.0435 1.0000
13.750 1.1119 0.06209 0.05714 0.0194 0.0434 1.0000
14.000 1.0861 0.06863 0.06393 0.0153 0.0434 1.0000
14.250 1.0561 0.07663 0.07216 0.0097 0.0436 1.0000
14.500 1.0204 0.08649 0.08223 0.0025 0.0439 1.0000
14.750 0.9799 0.09839 0.09431 -0.0058 0.0444 1.0000
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