S3010-103-84 (s3010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 50,000 Max Cl/Cd: 36.25 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3010-il-50000-n5.txt Download as CSV file: xf-s3010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4323 0.10367 0.09663 -0.0222 1.0000 0.0522
-9.250 -0.4233 0.10023 0.09322 -0.0223 1.0000 0.0515
-9.000 -0.4191 0.09643 0.08947 -0.0237 1.0000 0.0511
-8.750 -0.4166 0.09251 0.08562 -0.0255 1.0000 0.0507
-8.500 -0.4159 0.08844 0.08163 -0.0277 1.0000 0.0505
-8.250 -0.4165 0.08429 0.07756 -0.0300 1.0000 0.0502
-8.000 -0.4184 0.08014 0.07350 -0.0325 1.0000 0.0498
-7.750 -0.4213 0.07529 0.06874 -0.0364 1.0000 0.0495
-7.500 -0.4224 0.07020 0.06368 -0.0403 1.0000 0.0489
-7.250 -0.4249 0.06506 0.05850 -0.0436 1.0000 0.0486
-7.000 -0.4266 0.06027 0.05363 -0.0460 1.0000 0.0483
-6.750 -0.4271 0.05582 0.04904 -0.0474 1.0000 0.0480
-6.500 -0.4262 0.05171 0.04471 -0.0479 1.0000 0.0479
-6.250 -0.4227 0.04799 0.04072 -0.0477 1.0000 0.0478
-6.000 -0.4167 0.04457 0.03698 -0.0470 1.0000 0.0477
-5.750 -0.4082 0.04138 0.03341 -0.0462 1.0000 0.0478
-5.500 -0.3970 0.03848 0.03010 -0.0452 1.0000 0.0482
-5.250 -0.3834 0.03593 0.02713 -0.0442 1.0000 0.0487
-5.000 -0.3676 0.03366 0.02444 -0.0431 1.0000 0.0496
-4.750 -0.3502 0.03167 0.02202 -0.0420 1.0000 0.0510
-4.500 -0.3164 0.02976 0.01986 -0.0440 0.9924 0.0544
-4.250 -0.2780 0.02818 0.01802 -0.0464 0.9833 0.0598
-4.000 -0.2404 0.02655 0.01609 -0.0482 0.9739 0.0645
-3.750 -0.2037 0.02532 0.01477 -0.0501 0.9640 0.0738
-3.500 -0.1652 0.02412 0.01354 -0.0523 0.9547 0.0918
-3.250 -0.1261 0.02291 0.01249 -0.0549 0.9452 0.1359
-3.000 -0.0901 0.02175 0.01175 -0.0571 0.9345 0.2214
-2.750 -0.0539 0.02081 0.01126 -0.0591 0.9244 0.3320
-2.500 -0.0201 0.02009 0.01103 -0.0601 0.9140 0.4555
-2.250 0.0068 0.01960 0.01094 -0.0592 0.9016 0.5716
-2.000 0.0319 0.01924 0.01090 -0.0574 0.8895 0.6839
-1.750 0.0605 0.01896 0.01077 -0.0556 0.8785 0.7971
-1.500 0.1156 0.01865 0.01037 -0.0592 0.8696 0.9217
-1.250 0.1745 0.01846 0.00983 -0.0651 0.8582 1.0000
-1.000 0.2007 0.01854 0.00963 -0.0649 0.8438 1.0000
-0.750 0.2270 0.01864 0.00947 -0.0646 0.8298 1.0000
-0.500 0.2532 0.01875 0.00934 -0.0642 0.8162 1.0000
-0.250 0.2797 0.01886 0.00923 -0.0637 0.8029 1.0000
0.000 0.3061 0.01896 0.00914 -0.0631 0.7898 1.0000
0.250 0.3308 0.01912 0.00913 -0.0624 0.7755 1.0000
0.500 0.3557 0.01928 0.00914 -0.0616 0.7613 1.0000
0.750 0.3808 0.01944 0.00917 -0.0608 0.7473 1.0000
1.000 0.4063 0.01961 0.00921 -0.0601 0.7333 1.0000
1.250 0.4318 0.01978 0.00927 -0.0594 0.7194 1.0000
1.500 0.4574 0.01995 0.00933 -0.0586 0.7055 1.0000
1.750 0.4831 0.02013 0.00941 -0.0579 0.6917 1.0000
2.000 0.5089 0.02030 0.00950 -0.0571 0.6779 1.0000
2.250 0.5347 0.02048 0.00959 -0.0564 0.6641 1.0000
2.500 0.5605 0.02065 0.00971 -0.0556 0.6503 1.0000
2.750 0.5859 0.02087 0.00988 -0.0548 0.6359 1.0000
3.000 0.6112 0.02111 0.01007 -0.0541 0.6211 1.0000
3.250 0.6364 0.02136 0.01031 -0.0533 0.6062 1.0000
3.500 0.6615 0.02162 0.01054 -0.0526 0.5913 1.0000
3.750 0.6866 0.02190 0.01078 -0.0518 0.5761 1.0000
4.000 0.7117 0.02218 0.01106 -0.0511 0.5609 1.0000
4.250 0.7366 0.02248 0.01137 -0.0503 0.5456 1.0000
4.500 0.7614 0.02280 0.01168 -0.0495 0.5301 1.0000
4.750 0.7861 0.02313 0.01202 -0.0487 0.5146 1.0000
5.000 0.8106 0.02349 0.01240 -0.0480 0.4989 1.0000
5.250 0.8349 0.02387 0.01279 -0.0472 0.4831 1.0000
5.500 0.8589 0.02427 0.01320 -0.0464 0.4670 1.0000
5.750 0.8823 0.02474 0.01372 -0.0456 0.4502 1.0000
6.000 0.9053 0.02523 0.01429 -0.0448 0.4334 1.0000
6.250 0.9282 0.02574 0.01485 -0.0439 0.4165 1.0000
6.500 0.9507 0.02628 0.01543 -0.0431 0.3996 1.0000
6.750 0.9728 0.02684 0.01607 -0.0422 0.3828 1.0000
7.000 0.9946 0.02744 0.01671 -0.0412 0.3661 1.0000
7.250 1.0160 0.02807 0.01739 -0.0403 0.3496 1.0000
7.500 1.0369 0.02874 0.01810 -0.0393 0.3333 1.0000
7.750 1.0572 0.02946 0.01889 -0.0383 0.3173 1.0000
8.000 1.0767 0.03025 0.01972 -0.0373 0.3014 1.0000
8.250 1.0952 0.03113 0.02069 -0.0362 0.2855 1.0000
8.500 1.1130 0.03207 0.02170 -0.0351 0.2702 1.0000
8.750 1.1301 0.03306 0.02279 -0.0340 0.2553 1.0000
9.000 1.1466 0.03411 0.02390 -0.0328 0.2414 1.0000
9.250 1.1620 0.03522 0.02506 -0.0316 0.2279 1.0000
9.500 1.1761 0.03647 0.02643 -0.0303 0.2150 1.0000
9.750 1.1884 0.03782 0.02793 -0.0290 0.2026 1.0000
10.000 1.1998 0.03927 0.02953 -0.0276 0.1911 1.0000
10.250 1.2109 0.04074 0.03108 -0.0263 0.1809 1.0000
10.500 1.2217 0.04212 0.03245 -0.0249 0.1713 1.0000
10.750 1.2258 0.04402 0.03462 -0.0232 0.1622 1.0000
11.000 1.2324 0.04573 0.03638 -0.0217 0.1544 1.0000
11.250 1.2352 0.04773 0.03855 -0.0202 0.1468 1.0000
11.500 1.2388 0.04987 0.04080 -0.0190 0.1401 1.0000
11.750 1.2394 0.05229 0.04343 -0.0180 0.1338 1.0000
12.000 1.2429 0.05456 0.04577 -0.0172 0.1280 1.0000
12.250 1.2365 0.05793 0.04942 -0.0169 0.1229 1.0000
12.500 1.2422 0.06006 0.05156 -0.0163 0.1176 1.0000
12.750 1.2329 0.06416 0.05592 -0.0166 0.1139 1.0000
13.000 1.2191 0.06896 0.06100 -0.0177 0.1105 1.0000
13.250 1.2136 0.07277 0.06493 -0.0185 0.1066 1.0000
13.500 1.2136 0.07605 0.06826 -0.0189 0.1028 1.0000
13.750 1.1858 0.08376 0.07627 -0.0224 0.1016 1.0000
14.000 1.1503 0.09356 0.08633 -0.0276 0.1010 1.0000
14.250 1.0979 0.10810 0.10104 -0.0362 0.1015 1.0000
14.500 1.0197 0.13183 0.12469 -0.0505 0.1018 1.0000
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Polar data table (+)
Polar graphs
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