EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 100,000 Max Cl/Cd: 39.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1213-il-100000-n5.txt Download as CSV file: xf-e1213-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7507 0.09917 0.09302 -0.0179 1.0000 0.0703
-14.750 -0.7520 0.09542 0.08931 -0.0197 1.0000 0.0741
-14.500 -0.7667 0.08940 0.08325 -0.0228 1.0000 0.0779
-14.250 -0.7733 0.08510 0.07899 -0.0250 1.0000 0.0820
-14.000 -0.7966 0.07819 0.07200 -0.0287 1.0000 0.0860
-13.750 -0.8090 0.07326 0.06709 -0.0312 1.0000 0.0902
-13.500 -0.8399 0.06550 0.05921 -0.0356 1.0000 0.0935
-13.250 -0.8610 0.05947 0.05316 -0.0389 1.0000 0.0966
-13.000 -0.8890 0.05245 0.04604 -0.0432 1.0000 0.0992
-12.750 -0.9179 0.04558 0.03901 -0.0477 1.0000 0.1017
-12.500 -0.9392 0.04053 0.03380 -0.0505 1.0000 0.1048
-12.250 -0.9529 0.03735 0.03056 -0.0510 1.0000 0.1082
-12.000 -0.9616 0.03508 0.02816 -0.0498 1.0000 0.1131
-11.750 -0.9654 0.03360 0.02665 -0.0476 1.0000 0.1177
-11.500 -0.9633 0.03230 0.02525 -0.0456 1.0000 0.1238
-11.250 -0.9554 0.03133 0.02425 -0.0439 1.0000 0.1296
-11.000 -0.9454 0.03031 0.02309 -0.0423 1.0000 0.1364
-10.750 -0.9319 0.02970 0.02250 -0.0409 1.0000 0.1425
-10.500 -0.9187 0.02891 0.02155 -0.0394 1.0000 0.1507
-10.250 -0.9015 0.02873 0.02142 -0.0381 1.0000 0.1581
-10.000 -0.8856 0.02830 0.02089 -0.0367 1.0000 0.1659
-9.750 -0.8671 0.02817 0.02076 -0.0353 1.0000 0.1730
-9.500 -0.8505 0.02768 0.02015 -0.0339 1.0000 0.1794
-9.250 -0.8302 0.02756 0.02008 -0.0326 1.0000 0.1843
-9.000 -0.8139 0.02695 0.01932 -0.0311 1.0000 0.1899
-8.750 -0.7965 0.02646 0.01878 -0.0296 1.0000 0.1943
-8.500 -0.7752 0.02624 0.01862 -0.0286 0.9973 0.1984
-8.250 -0.7361 0.02563 0.01782 -0.0313 0.9657 0.2050
-8.000 -0.6959 0.02510 0.01718 -0.0339 0.9311 0.2104
-7.750 -0.6539 0.02478 0.01678 -0.0365 0.9001 0.2157
-7.500 -0.6198 0.02424 0.01597 -0.0377 0.8687 0.2217
-7.250 -0.5903 0.02383 0.01537 -0.0379 0.8403 0.2261
-7.000 -0.5633 0.02361 0.01508 -0.0374 0.8145 0.2300
-6.750 -0.5383 0.02332 0.01461 -0.0366 0.7914 0.2346
-6.500 -0.5145 0.02294 0.01393 -0.0357 0.7707 0.2397
-6.250 -0.4893 0.02261 0.01351 -0.0350 0.7517 0.2435
-6.000 -0.4638 0.02237 0.01321 -0.0343 0.7338 0.2473
-5.750 -0.4384 0.02211 0.01281 -0.0336 0.7174 0.2518
-5.500 -0.4133 0.02180 0.01228 -0.0328 0.7021 0.2568
-5.250 -0.3876 0.02149 0.01184 -0.0322 0.6869 0.2607
-5.000 -0.3612 0.02124 0.01157 -0.0317 0.6722 0.2646
-4.750 -0.3351 0.02102 0.01125 -0.0311 0.6587 0.2692
-4.500 -0.3091 0.02078 0.01083 -0.0305 0.6459 0.2741
-4.250 -0.2827 0.02051 0.01045 -0.0301 0.6325 0.2784
-4.000 -0.2563 0.02030 0.01021 -0.0295 0.6205 0.2825
-3.750 -0.2298 0.02011 0.00995 -0.0290 0.6083 0.2873
-3.500 -0.2032 0.01993 0.00965 -0.0286 0.5966 0.2925
-3.250 -0.1767 0.01974 0.00933 -0.0280 0.5860 0.2971
-3.000 -0.1500 0.01955 0.00917 -0.0276 0.5741 0.3016
-2.750 -0.1234 0.01942 0.00894 -0.0271 0.5643 0.3070
-2.500 -0.0964 0.01928 0.00872 -0.0267 0.5530 0.3127
-2.250 -0.0697 0.01912 0.00852 -0.0262 0.5435 0.3176
-2.000 -0.0430 0.01899 0.00841 -0.0258 0.5329 0.3231
-1.750 -0.0162 0.01891 0.00823 -0.0253 0.5240 0.3297
-1.500 0.0107 0.01880 0.00810 -0.0249 0.5137 0.3359
-1.250 0.0372 0.01870 0.00798 -0.0244 0.5052 0.3419
-1.000 0.0641 0.01863 0.00791 -0.0240 0.4953 0.3494
-0.500 0.1173 0.01850 0.00779 -0.0231 0.4778 0.3653
-0.250 0.1441 0.01847 0.00769 -0.0226 0.4699 0.3745
0.000 0.1704 0.01841 0.00772 -0.0221 0.4612 0.3837
0.250 0.1970 0.01839 0.00768 -0.0217 0.4530 0.3951
0.500 0.2233 0.01837 0.00770 -0.0212 0.4452 0.4078
0.750 0.2496 0.01835 0.00775 -0.0207 0.4369 0.4221
1.000 0.2759 0.01834 0.00772 -0.0201 0.4302 0.4386
1.250 0.3020 0.01834 0.00786 -0.0197 0.4216 0.4579
1.500 0.3280 0.01833 0.00790 -0.0191 0.4145 0.4815
1.750 0.3540 0.01834 0.00802 -0.0186 0.4073 0.5104
2.000 0.3799 0.01833 0.00816 -0.0180 0.3996 0.5447
2.250 0.4052 0.01831 0.00823 -0.0172 0.3936 0.5860
2.500 0.4298 0.01831 0.00848 -0.0163 0.3859 0.6358
2.750 0.4542 0.01827 0.00864 -0.0153 0.3792 0.6961
3.000 0.4808 0.01825 0.00883 -0.0144 0.3731 0.7688
3.250 0.5194 0.01834 0.00916 -0.0159 0.3647 0.8526
3.500 0.5719 0.01853 0.00930 -0.0202 0.3574 0.9243
3.750 0.6164 0.01882 0.00963 -0.0235 0.3490 0.9730
4.000 0.6591 0.01909 0.00981 -0.0265 0.3420 1.0000
4.250 0.6806 0.01939 0.01002 -0.0254 0.3370 1.0000
4.500 0.7020 0.01971 0.01034 -0.0243 0.3308 1.0000
4.750 0.7237 0.02000 0.01055 -0.0232 0.3254 1.0000
5.000 0.7457 0.02032 0.01076 -0.0221 0.3208 1.0000
5.250 0.7670 0.02071 0.01119 -0.0211 0.3149 1.0000
5.500 0.7888 0.02107 0.01152 -0.0200 0.3098 1.0000
5.750 0.8111 0.02141 0.01177 -0.0190 0.3055 1.0000
6.000 0.8326 0.02184 0.01221 -0.0180 0.3006 1.0000
6.250 0.8539 0.02227 0.01266 -0.0170 0.2953 1.0000
6.500 0.8758 0.02265 0.01301 -0.0160 0.2907 1.0000
6.750 0.8984 0.02305 0.01329 -0.0152 0.2869 1.0000
7.000 0.9186 0.02360 0.01396 -0.0141 0.2822 1.0000
7.250 0.9395 0.02411 0.01450 -0.0131 0.2778 1.0000
7.500 0.9611 0.02455 0.01492 -0.0122 0.2738 1.0000
7.750 0.9838 0.02499 0.01525 -0.0114 0.2704 1.0000
8.000 1.0019 0.02566 0.01606 -0.0102 0.2659 1.0000
8.250 1.0211 0.02625 0.01671 -0.0091 0.2617 1.0000
8.500 1.0414 0.02679 0.01725 -0.0081 0.2582 1.0000
8.750 1.0629 0.02731 0.01772 -0.0073 0.2553 1.0000
9.000 1.0814 0.02801 0.01848 -0.0062 0.2520 1.0000
9.250 1.0967 0.02883 0.01942 -0.0048 0.2482 1.0000
9.500 1.1134 0.02953 0.02020 -0.0036 0.2446 1.0000
9.750 1.1317 0.03015 0.02081 -0.0025 0.2415 1.0000
10.000 1.1521 0.03072 0.02133 -0.0016 0.2389 1.0000
10.250 1.1659 0.03165 0.02235 -0.0002 0.2362 1.0000
10.500 1.1744 0.03276 0.02363 0.0016 0.2332 1.0000
10.750 1.1831 0.03378 0.02475 0.0035 0.2302 1.0000
11.000 1.1929 0.03466 0.02569 0.0053 0.2275 1.0000
11.250 1.2068 0.03540 0.02642 0.0066 0.2250 1.0000
11.500 1.2265 0.03602 0.02699 0.0074 0.2228 1.0000
11.750 1.2220 0.03772 0.02887 0.0098 0.2204 1.0000
12.000 1.2126 0.03991 0.03126 0.0117 0.2179 1.0000
12.250 1.2047 0.04226 0.03377 0.0128 0.2153 1.0000
12.500 1.2026 0.04441 0.03602 0.0135 0.2127 1.0000
12.750 1.2104 0.04590 0.03754 0.0140 0.2104 1.0000
13.000 1.2303 0.04650 0.03811 0.0145 0.2084 1.0000
13.250 1.2230 0.04939 0.04111 0.0146 0.2062 1.0000
13.500 0.9283 0.09053 0.08302 -0.0040 0.1914 1.0000
13.750 0.9723 0.08675 0.07921 -0.0014 0.1921 1.0000
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