NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.67 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20410-il-1000000-n5.txt Download as CSV file: xf-sc20410-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0016 0.13719 0.13502 0.0099 1.0000 0.0102
-17.500 -1.1342 0.10461 0.10207 -0.0079 1.0000 0.0099
-17.250 -1.1990 0.08701 0.08422 -0.0178 1.0000 0.0098
-17.000 -1.2374 0.07476 0.07175 -0.0254 1.0000 0.0097
-16.750 -1.2636 0.06551 0.06231 -0.0314 1.0000 0.0097
-16.500 -1.2827 0.05843 0.05507 -0.0357 1.0000 0.0097
-16.250 -1.2974 0.05286 0.04934 -0.0386 1.0000 0.0098
-16.000 -1.3080 0.04832 0.04466 -0.0405 1.0000 0.0098
-15.750 -1.3151 0.04451 0.04072 -0.0418 1.0000 0.0099
-15.500 -1.3190 0.04125 0.03734 -0.0425 1.0000 0.0099
-15.250 -1.3201 0.03846 0.03444 -0.0430 1.0000 0.0100
-15.000 -1.3183 0.03605 0.03193 -0.0431 1.0000 0.0101
-14.750 -1.3140 0.03397 0.02975 -0.0431 1.0000 0.0102
-14.500 -1.3080 0.03212 0.02780 -0.0430 1.0000 0.0103
-14.250 -1.3002 0.03048 0.02608 -0.0427 1.0000 0.0104
-14.000 -1.2915 0.02899 0.02451 -0.0422 1.0000 0.0105
-13.750 -1.2824 0.02763 0.02306 -0.0416 1.0000 0.0106
-13.500 -1.2734 0.02635 0.02170 -0.0407 1.0000 0.0107
-13.250 -1.2590 0.02514 0.02039 -0.0407 1.0000 0.0108
-13.000 -1.2420 0.02401 0.01918 -0.0409 1.0000 0.0109
-12.750 -1.2233 0.02298 0.01806 -0.0410 1.0000 0.0110
-12.500 -1.2036 0.02206 0.01706 -0.0410 1.0000 0.0111
-12.250 -1.1831 0.02121 0.01612 -0.0410 1.0000 0.0113
-12.000 -1.1618 0.02042 0.01525 -0.0409 1.0000 0.0114
-11.750 -1.1398 0.01966 0.01442 -0.0409 1.0000 0.0116
-11.500 -1.1171 0.01896 0.01366 -0.0408 1.0000 0.0117
-11.250 -1.0939 0.01830 0.01293 -0.0408 1.0000 0.0118
-11.000 -1.0702 0.01769 0.01225 -0.0408 1.0000 0.0120
-10.750 -1.0460 0.01711 0.01162 -0.0408 1.0000 0.0121
-10.500 -1.0216 0.01657 0.01102 -0.0408 1.0000 0.0122
-10.250 -0.9972 0.01588 0.01028 -0.0408 1.0000 0.0125
-10.000 -0.9723 0.01529 0.00965 -0.0409 1.0000 0.0128
-9.750 -0.9469 0.01478 0.00910 -0.0410 1.0000 0.0132
-9.500 -0.9212 0.01432 0.00862 -0.0411 1.0000 0.0136
-9.250 -0.8952 0.01389 0.00817 -0.0411 1.0000 0.0140
-9.000 -0.8690 0.01349 0.00774 -0.0412 1.0000 0.0144
-8.750 -0.8427 0.01310 0.00732 -0.0413 1.0000 0.0147
-8.500 -0.8162 0.01274 0.00694 -0.0414 1.0000 0.0151
-8.250 -0.7897 0.01239 0.00656 -0.0415 1.0000 0.0155
-8.000 -0.7630 0.01201 0.00617 -0.0416 1.0000 0.0163
-7.750 -0.7363 0.01168 0.00584 -0.0417 1.0000 0.0173
-7.500 -0.7097 0.01138 0.00554 -0.0418 1.0000 0.0183
-7.250 -0.6805 0.01108 0.00523 -0.0423 0.9997 0.0197
-7.000 -0.6482 0.01077 0.00495 -0.0436 0.9988 0.0220
-6.750 -0.6157 0.01049 0.00468 -0.0449 0.9978 0.0242
-6.500 -0.5832 0.01022 0.00443 -0.0461 0.9968 0.0268
-6.250 -0.5504 0.00999 0.00420 -0.0474 0.9957 0.0289
-6.000 -0.5172 0.00973 0.00397 -0.0488 0.9947 0.0319
-5.750 -0.4843 0.00952 0.00376 -0.0501 0.9934 0.0341
-5.500 -0.4520 0.00929 0.00355 -0.0512 0.9915 0.0368
-5.250 -0.4193 0.00907 0.00336 -0.0525 0.9896 0.0395
-5.000 -0.3862 0.00889 0.00317 -0.0537 0.9878 0.0418
-4.750 -0.3529 0.00867 0.00300 -0.0551 0.9862 0.0461
-4.500 -0.3195 0.00848 0.00284 -0.0564 0.9846 0.0502
-4.250 -0.2864 0.00826 0.00267 -0.0577 0.9823 0.0580
-4.000 -0.2547 0.00808 0.00252 -0.0587 0.9781 0.0648
-3.750 -0.2218 0.00789 0.00238 -0.0599 0.9747 0.0723
-3.500 -0.1884 0.00769 0.00224 -0.0612 0.9718 0.0846
-3.250 -0.1562 0.00747 0.00211 -0.0622 0.9667 0.1029
-3.000 -0.1230 0.00719 0.00196 -0.0636 0.9599 0.1360
-2.750 -0.0908 0.00692 0.00183 -0.0647 0.9500 0.1753
-2.500 -0.0594 0.00665 0.00170 -0.0656 0.9361 0.2206
-2.250 -0.0284 0.00633 0.00157 -0.0664 0.9197 0.2848
-2.000 0.0029 0.00597 0.00144 -0.0674 0.9014 0.3652
-1.750 0.0363 0.00541 0.00125 -0.0691 0.8806 0.4946
-1.500 0.0673 0.00519 0.00124 -0.0699 0.8571 0.5830
-1.250 0.0957 0.00525 0.00124 -0.0698 0.8268 0.6098
-1.000 0.1244 0.00534 0.00127 -0.0699 0.7967 0.6300
-0.750 0.1522 0.00554 0.00129 -0.0697 0.7465 0.6422
-0.500 0.1801 0.00577 0.00134 -0.0696 0.6929 0.6516
-0.250 0.2070 0.00623 0.00139 -0.0694 0.5874 0.6567
0.000 0.2337 0.00681 0.00152 -0.0693 0.4606 0.6606
0.250 0.2609 0.00735 0.00166 -0.0693 0.3526 0.6656
0.500 0.2889 0.00772 0.00176 -0.0694 0.2821 0.6707
0.750 0.3171 0.00802 0.00187 -0.0696 0.2262 0.6747
1.000 0.3452 0.00833 0.00199 -0.0697 0.1750 0.6779
1.500 0.4022 0.00877 0.00220 -0.0699 0.1178 0.6825
1.750 0.4307 0.00897 0.00231 -0.0700 0.0977 0.6847
2.000 0.4592 0.00917 0.00242 -0.0701 0.0814 0.6867
2.500 0.5163 0.00951 0.00268 -0.0703 0.0619 0.6898
2.750 0.5448 0.00968 0.00281 -0.0704 0.0552 0.6913
3.000 0.5732 0.00984 0.00296 -0.0705 0.0504 0.6929
3.250 0.6015 0.01002 0.00312 -0.0705 0.0455 0.6944
3.500 0.6299 0.01019 0.00327 -0.0706 0.0421 0.6960
3.750 0.6581 0.01039 0.00344 -0.0706 0.0386 0.6977
4.000 0.6863 0.01056 0.00362 -0.0706 0.0367 0.6994
4.250 0.7145 0.01075 0.00380 -0.0707 0.0343 0.7010
4.500 0.7424 0.01098 0.00400 -0.0706 0.0317 0.7027
4.750 0.7704 0.01116 0.00420 -0.0706 0.0301 0.7043
5.000 0.7983 0.01138 0.00441 -0.0706 0.0277 0.7061
5.250 0.8259 0.01161 0.00465 -0.0705 0.0255 0.7080
5.500 0.8536 0.01183 0.00488 -0.0705 0.0233 0.7097
5.750 0.8810 0.01211 0.00515 -0.0704 0.0211 0.7116
6.000 0.9083 0.01237 0.00542 -0.0703 0.0193 0.7135
6.250 0.9354 0.01268 0.00573 -0.0701 0.0176 0.7155
6.500 0.9625 0.01298 0.00605 -0.0700 0.0168 0.7174
6.750 0.9894 0.01328 0.00638 -0.0698 0.0161 0.7193
7.000 1.0162 0.01361 0.00673 -0.0696 0.0155 0.7211
7.250 1.0427 0.01397 0.00711 -0.0693 0.0149 0.7230
7.500 1.0689 0.01437 0.00755 -0.0690 0.0143 0.7251
7.750 1.0949 0.01479 0.00801 -0.0687 0.0139 0.7273
8.000 1.1211 0.01516 0.00844 -0.0684 0.0137 0.7297
8.250 1.1470 0.01557 0.00890 -0.0681 0.0134 0.7321
8.500 1.1726 0.01599 0.00937 -0.0677 0.0132 0.7345
8.750 1.1980 0.01644 0.00988 -0.0673 0.0130 0.7368
9.250 1.2481 0.01739 0.01095 -0.0664 0.0125 0.7416
9.500 1.2727 0.01790 0.01153 -0.0659 0.0123 0.7445
9.750 1.2970 0.01843 0.01212 -0.0654 0.0121 0.7476
10.000 1.3209 0.01898 0.01273 -0.0648 0.0119 0.7508
10.250 1.3444 0.01959 0.01340 -0.0642 0.0116 0.7538
10.500 1.3670 0.02030 0.01418 -0.0634 0.0114 0.7566
10.750 1.3884 0.02113 0.01512 -0.0625 0.0111 0.7597
11.000 1.4090 0.02203 0.01612 -0.0615 0.0110 0.7630
11.250 1.4308 0.02272 0.01690 -0.0607 0.0109 0.7664
11.500 1.4519 0.02345 0.01774 -0.0597 0.0108 0.7697
11.750 1.4724 0.02422 0.01861 -0.0587 0.0107 0.7728
12.000 1.4921 0.02504 0.01954 -0.0576 0.0106 0.7762
12.250 1.5108 0.02591 0.02053 -0.0564 0.0105 0.7799
12.500 1.5286 0.02684 0.02157 -0.0551 0.0104 0.7836
13.000 1.5604 0.02889 0.02387 -0.0520 0.0103 0.7909
13.250 1.5741 0.03000 0.02511 -0.0503 0.0102 0.7951
13.500 1.5859 0.03120 0.02643 -0.0483 0.0101 0.7994
13.750 1.5952 0.03246 0.02783 -0.0460 0.0100 0.8033
14.000 1.5999 0.03375 0.02926 -0.0430 0.0099 0.8077
14.250 1.5994 0.03520 0.03084 -0.0394 0.0099 0.8124
14.750 1.5978 0.03877 0.03470 -0.0339 0.0097 0.8214
15.000 1.5939 0.04107 0.03716 -0.0316 0.0097 0.8263
15.250 1.5882 0.04377 0.04001 -0.0300 0.0096 0.8311
15.500 1.5810 0.04691 0.04331 -0.0291 0.0096 0.8362
15.750 1.5695 0.05092 0.04750 -0.0290 0.0095 0.8417
16.000 1.5540 0.05603 0.05279 -0.0303 0.0095 0.8466
16.250 1.5316 0.06304 0.06002 -0.0337 0.0095 0.8511
16.500 1.4949 0.07446 0.07170 -0.0414 0.0095 0.8548
16.750 1.3409 0.11385 0.11162 -0.0663 0.0098 0.8484
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