12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 50,000 Max Cl/Cd: 26.44 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk-il-50000-n5.txt Download as CSV file: xf-joukowsk-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7858 0.09575 0.08806 0.0060 1.0000 0.0877
-11.500 -0.8944 0.07122 0.06329 -0.0127 1.0000 0.0838
-11.250 -0.9288 0.06370 0.05553 -0.0173 1.0000 0.0837
-11.000 -0.9435 0.05944 0.05110 -0.0185 1.0000 0.0850
-10.750 -0.9555 0.05582 0.04728 -0.0185 1.0000 0.0865
-10.500 -0.9622 0.05222 0.04337 -0.0183 1.0000 0.0888
-10.250 -0.9656 0.04857 0.03926 -0.0179 1.0000 0.0914
-10.000 -0.9528 0.04649 0.03714 -0.0173 1.0000 0.0947
-9.750 -0.9400 0.04458 0.03513 -0.0167 1.0000 0.0989
-9.500 -0.9302 0.04196 0.03209 -0.0161 1.0000 0.1037
-9.250 -0.9129 0.04032 0.03048 -0.0155 1.0000 0.1086
-9.000 -0.8968 0.03853 0.02850 -0.0149 1.0000 0.1147
-8.750 -0.8790 0.03679 0.02663 -0.0143 1.0000 0.1210
-8.500 -0.8605 0.03531 0.02503 -0.0137 1.0000 0.1288
-8.250 -0.8409 0.03388 0.02356 -0.0131 1.0000 0.1366
-8.000 -0.8212 0.03244 0.02192 -0.0125 1.0000 0.1467
-7.750 -0.8006 0.03129 0.02081 -0.0119 1.0000 0.1566
-7.500 -0.7798 0.03014 0.01965 -0.0113 1.0000 0.1681
-7.250 -0.7584 0.02902 0.01850 -0.0107 1.0000 0.1810
-7.000 -0.7369 0.02801 0.01745 -0.0101 1.0000 0.1956
-6.750 -0.7149 0.02706 0.01651 -0.0095 1.0000 0.2112
-6.500 -0.6927 0.02620 0.01567 -0.0089 1.0000 0.2284
-6.250 -0.6702 0.02540 0.01490 -0.0083 1.0000 0.2468
-6.000 -0.6473 0.02465 0.01414 -0.0078 1.0000 0.2667
-5.750 -0.6242 0.02397 0.01347 -0.0072 1.0000 0.2876
-5.500 -0.6010 0.02337 0.01296 -0.0065 1.0000 0.3081
-5.250 -0.5776 0.02281 0.01242 -0.0058 1.0000 0.3302
-5.000 -0.5540 0.02228 0.01191 -0.0052 1.0000 0.3530
-4.750 -0.5304 0.02182 0.01155 -0.0044 1.0000 0.3746
-4.500 -0.5068 0.02139 0.01114 -0.0037 1.0000 0.3975
-4.250 -0.4832 0.02099 0.01079 -0.0029 1.0000 0.4201
-4.000 -0.4599 0.02064 0.01053 -0.0020 1.0000 0.4418
-3.750 -0.4369 0.02030 0.01024 -0.0011 1.0000 0.4643
-3.500 -0.4143 0.01999 0.00999 -0.0002 1.0000 0.4866
-3.250 -0.3925 0.01972 0.00982 0.0010 1.0000 0.5074
-3.000 -0.3723 0.01948 0.00966 0.0023 1.0000 0.5287
-2.750 -0.3532 0.01926 0.00950 0.0037 1.0000 0.5501
-2.500 -0.3352 0.01909 0.00941 0.0052 1.0000 0.5709
-2.250 -0.3187 0.01898 0.00938 0.0070 1.0000 0.5909
-2.000 -0.2749 0.01897 0.00943 0.0039 0.9771 0.6173
-1.750 -0.2299 0.01899 0.00951 0.0008 0.9569 0.6427
-1.500 -0.1887 0.01899 0.00956 -0.0013 0.9352 0.6674
-1.250 -0.1495 0.01899 0.00960 -0.0029 0.9134 0.6915
-1.000 -0.1132 0.01900 0.00966 -0.0036 0.8917 0.7137
-0.750 -0.0823 0.01901 0.00969 -0.0034 0.8682 0.7361
-0.500 -0.0530 0.01901 0.00969 -0.0027 0.8458 0.7586
-0.250 -0.0258 0.01902 0.00972 -0.0014 0.8238 0.7795
0.000 0.0000 0.01902 0.00973 0.0000 0.8011 0.8011
0.250 0.0257 0.01902 0.00972 0.0014 0.7795 0.8238
0.500 0.0530 0.01901 0.00969 0.0027 0.7586 0.8458
0.750 0.0822 0.01900 0.00969 0.0034 0.7360 0.8682
1.000 0.1132 0.01900 0.00966 0.0036 0.7137 0.8917
1.250 0.1494 0.01899 0.00960 0.0029 0.6915 0.9134
1.500 0.1887 0.01899 0.00956 0.0013 0.6674 0.9352
1.750 0.2299 0.01899 0.00951 -0.0008 0.6428 0.9570
2.000 0.2749 0.01897 0.00943 -0.0039 0.6172 0.9772
2.250 0.3186 0.01897 0.00938 -0.0070 0.5909 1.0000
2.500 0.3352 0.01909 0.00941 -0.0052 0.5710 1.0000
2.750 0.3531 0.01926 0.00950 -0.0037 0.5501 1.0000
3.000 0.3723 0.01948 0.00966 -0.0023 0.5287 1.0000
3.250 0.3925 0.01972 0.00982 -0.0010 0.5075 1.0000
3.500 0.4143 0.01999 0.00998 0.0002 0.4866 1.0000
3.750 0.4369 0.02030 0.01023 0.0011 0.4643 1.0000
4.000 0.4599 0.02064 0.01053 0.0020 0.4418 1.0000
4.250 0.4832 0.02099 0.01079 0.0029 0.4201 1.0000
4.500 0.5068 0.02139 0.01114 0.0037 0.3975 1.0000
4.750 0.5304 0.02182 0.01155 0.0044 0.3746 1.0000
5.000 0.5539 0.02228 0.01191 0.0052 0.3530 1.0000
5.250 0.5776 0.02281 0.01242 0.0058 0.3302 1.0000
5.500 0.6010 0.02337 0.01296 0.0065 0.3082 1.0000
5.750 0.6242 0.02397 0.01347 0.0072 0.2876 1.0000
6.000 0.6473 0.02465 0.01414 0.0078 0.2667 1.0000
6.250 0.6701 0.02540 0.01489 0.0084 0.2468 1.0000
6.500 0.6927 0.02620 0.01567 0.0090 0.2284 1.0000
6.750 0.7149 0.02706 0.01651 0.0096 0.2112 1.0000
7.000 0.7368 0.02801 0.01745 0.0101 0.1956 1.0000
7.250 0.7584 0.02902 0.01850 0.0107 0.1810 1.0000
7.500 0.7797 0.03014 0.01965 0.0113 0.1682 1.0000
7.750 0.8006 0.03129 0.02081 0.0119 0.1566 1.0000
8.000 0.8212 0.03244 0.02192 0.0125 0.1467 1.0000
8.250 0.8409 0.03388 0.02356 0.0131 0.1366 1.0000
8.500 0.8604 0.03531 0.02503 0.0137 0.1287 1.0000
8.750 0.8789 0.03679 0.02663 0.0143 0.1210 1.0000
9.000 0.8967 0.03852 0.02849 0.0149 0.1148 1.0000
9.250 0.9128 0.04031 0.03047 0.0155 0.1085 1.0000
9.500 0.9303 0.04195 0.03209 0.0161 0.1038 1.0000
9.750 0.9400 0.04457 0.03512 0.0167 0.0990 1.0000
10.000 0.9529 0.04648 0.03713 0.0173 0.0947 1.0000
10.250 0.9655 0.04856 0.03927 0.0179 0.0914 1.0000
10.500 0.9622 0.05221 0.04336 0.0183 0.0888 1.0000
10.750 0.9556 0.05581 0.04727 0.0185 0.0866 1.0000
11.000 0.9436 0.05942 0.05108 0.0186 0.0850 1.0000
11.250 0.9288 0.06369 0.05552 0.0173 0.0837 1.0000
11.500 0.8940 0.07126 0.06333 0.0127 0.0838 1.0000
11.750 0.7856 0.09577 0.08807 -0.0060 0.0876 1.0000
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Polar data table (+)
Polar graphs
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