NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 500,000 Max Cl/Cd: 63.65 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20710-il-500000-n5.txt Download as CSV file: xf-sc20710-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9609 0.07610 0.07282 -0.0491 1.0000 0.0135
-15.750 -0.9967 0.06457 0.06102 -0.0570 1.0000 0.0134
-15.500 -1.0174 0.05729 0.05355 -0.0618 1.0000 0.0134
-15.250 -1.0317 0.05192 0.04802 -0.0648 1.0000 0.0134
-15.000 -1.0415 0.04773 0.04367 -0.0666 1.0000 0.0135
-14.750 -1.0490 0.04423 0.04004 -0.0675 1.0000 0.0135
-14.500 -1.0546 0.04131 0.03699 -0.0677 1.0000 0.0136
-14.250 -1.0591 0.03880 0.03435 -0.0673 1.0000 0.0137
-14.000 -1.0631 0.03662 0.03207 -0.0662 1.0000 0.0138
-13.750 -1.0677 0.03477 0.03012 -0.0644 1.0000 0.0139
-13.500 -1.0758 0.03323 0.02848 -0.0614 1.0000 0.0140
-13.250 -1.0800 0.03175 0.02691 -0.0588 1.0000 0.0141
-13.000 -1.0761 0.03023 0.02528 -0.0576 1.0000 0.0142
-12.750 -1.0678 0.02879 0.02372 -0.0569 1.0000 0.0144
-12.500 -1.0558 0.02742 0.02222 -0.0565 1.0000 0.0146
-12.250 -1.0385 0.02610 0.02077 -0.0569 0.9997 0.0148
-12.000 -1.0115 0.02477 0.01928 -0.0589 0.9987 0.0151
-11.750 -0.9840 0.02358 0.01795 -0.0607 0.9975 0.0153
-11.500 -0.9560 0.02251 0.01674 -0.0623 0.9965 0.0156
-11.250 -0.9273 0.02157 0.01568 -0.0639 0.9955 0.0159
-11.000 -0.8983 0.02048 0.01451 -0.0657 0.9947 0.0164
-10.750 -0.8681 0.01970 0.01367 -0.0674 0.9940 0.0169
-10.500 -0.8395 0.01900 0.01293 -0.0686 0.9928 0.0174
-10.250 -0.8103 0.01832 0.01217 -0.0698 0.9916 0.0179
-10.000 -0.7805 0.01766 0.01145 -0.0711 0.9905 0.0184
-9.750 -0.7502 0.01704 0.01075 -0.0725 0.9894 0.0190
-9.500 -0.7193 0.01646 0.01010 -0.0739 0.9884 0.0196
-9.250 -0.6880 0.01583 0.00943 -0.0754 0.9875 0.0204
-9.000 -0.6564 0.01535 0.00894 -0.0769 0.9866 0.0214
-8.750 -0.6243 0.01491 0.00846 -0.0784 0.9858 0.0226
-8.500 -0.5917 0.01449 0.00799 -0.0799 0.9851 0.0239
-8.250 -0.5588 0.01404 0.00754 -0.0816 0.9845 0.0257
-8.000 -0.5259 0.01370 0.00719 -0.0831 0.9839 0.0277
-7.750 -0.4941 0.01338 0.00682 -0.0844 0.9830 0.0296
-7.500 -0.4644 0.01298 0.00644 -0.0853 0.9812 0.0319
-7.250 -0.4333 0.01269 0.00613 -0.0864 0.9796 0.0341
-7.000 -0.4014 0.01240 0.00581 -0.0876 0.9783 0.0361
-6.750 -0.3689 0.01207 0.00551 -0.0890 0.9772 0.0390
-6.500 -0.3364 0.01183 0.00527 -0.0903 0.9762 0.0421
-6.250 -0.3035 0.01155 0.00500 -0.0918 0.9754 0.0459
-6.000 -0.2704 0.01131 0.00479 -0.0932 0.9746 0.0509
-5.750 -0.2368 0.01105 0.00456 -0.0948 0.9739 0.0569
-5.500 -0.2033 0.01083 0.00435 -0.0963 0.9733 0.0632
-5.250 -0.1693 0.01058 0.00415 -0.0979 0.9728 0.0733
-5.000 -0.1351 0.01033 0.00397 -0.0996 0.9723 0.0859
-4.750 -0.1008 0.01010 0.00381 -0.1013 0.9718 0.1037
-4.250 -0.0356 0.00948 0.00352 -0.1042 0.9689 0.1786
-4.000 -0.0006 0.00908 0.00336 -0.1063 0.9677 0.2423
-3.500 0.0779 0.00790 0.00302 -0.1128 0.9674 0.4656
-3.250 0.1136 0.00761 0.00308 -0.1149 0.9668 0.5641
-3.000 0.1456 0.00758 0.00312 -0.1158 0.9654 0.5899
-2.750 0.1782 0.00756 0.00316 -0.1167 0.9640 0.6135
-2.500 0.2127 0.00751 0.00316 -0.1180 0.9623 0.6333
-2.250 0.2487 0.00741 0.00309 -0.1196 0.9601 0.6475
-2.000 0.2818 0.00728 0.00299 -0.1204 0.9542 0.6529
-1.750 0.3188 0.00703 0.00272 -0.1219 0.9442 0.6591
-1.500 0.3506 0.00690 0.00261 -0.1223 0.9304 0.6659
-1.250 0.3811 0.00684 0.00253 -0.1224 0.9102 0.6721
-1.000 0.4118 0.00682 0.00243 -0.1226 0.8835 0.6787
-0.750 0.4392 0.00692 0.00242 -0.1219 0.8389 0.6835
-0.500 0.4576 0.00775 0.00246 -0.1193 0.6613 0.6871
-0.250 0.4758 0.00891 0.00278 -0.1174 0.4739 0.6899
0.000 0.4991 0.00971 0.00302 -0.1167 0.3445 0.6925
0.250 0.5245 0.01027 0.00321 -0.1164 0.2560 0.6946
0.500 0.5502 0.01074 0.00342 -0.1160 0.1906 0.6964
0.750 0.5765 0.01114 0.00362 -0.1157 0.1426 0.6985
1.000 0.6033 0.01149 0.00382 -0.1155 0.1087 0.7007
1.250 0.6306 0.01177 0.00402 -0.1154 0.0889 0.7030
1.500 0.6581 0.01203 0.00421 -0.1153 0.0753 0.7055
1.750 0.6857 0.01229 0.00441 -0.1152 0.0660 0.7082
2.000 0.7131 0.01257 0.00464 -0.1150 0.0579 0.7106
2.250 0.7402 0.01279 0.00487 -0.1148 0.0525 0.7124
2.500 0.7671 0.01307 0.00512 -0.1145 0.0472 0.7142
2.750 0.7943 0.01331 0.00537 -0.1143 0.0436 0.7161
3.000 0.8211 0.01361 0.00565 -0.1141 0.0402 0.7182
3.250 0.8482 0.01387 0.00593 -0.1138 0.0377 0.7204
3.500 0.8751 0.01415 0.00621 -0.1136 0.0351 0.7226
3.750 0.9016 0.01452 0.00655 -0.1133 0.0326 0.7249
4.000 0.9285 0.01480 0.00687 -0.1130 0.0309 0.7268
4.250 0.9547 0.01511 0.00721 -0.1126 0.0289 0.7286
4.500 0.9804 0.01549 0.00760 -0.1122 0.0271 0.7307
4.750 1.0063 0.01586 0.00802 -0.1117 0.0256 0.7331
5.000 1.0322 0.01623 0.00843 -0.1112 0.0241 0.7356
5.250 1.0579 0.01662 0.00883 -0.1108 0.0227 0.7379
5.500 1.0832 0.01709 0.00932 -0.1103 0.0215 0.7402
5.750 1.1088 0.01751 0.00978 -0.1098 0.0205 0.7424
6.000 1.1338 0.01794 0.01027 -0.1092 0.0196 0.7441
6.250 1.1584 0.01841 0.01078 -0.1085 0.0188 0.7458
6.500 1.1825 0.01894 0.01136 -0.1078 0.0182 0.7477
6.750 1.2059 0.01960 0.01206 -0.1070 0.0176 0.7497
7.000 1.2297 0.02018 0.01274 -0.1062 0.0172 0.7519
7.250 1.2531 0.02081 0.01345 -0.1053 0.0168 0.7542
7.500 1.2762 0.02147 0.01420 -0.1044 0.0164 0.7564
7.750 1.2990 0.02216 0.01497 -0.1035 0.0161 0.7586
8.000 1.3212 0.02285 0.01575 -0.1025 0.0157 0.7603
8.250 1.3428 0.02357 0.01657 -0.1014 0.0154 0.7623
8.500 1.3641 0.02433 0.01742 -0.1003 0.0151 0.7645
8.750 1.3847 0.02513 0.01831 -0.0991 0.0149 0.7668
9.000 1.4044 0.02602 0.01929 -0.0977 0.0146 0.7692
9.250 1.4216 0.02724 0.02060 -0.0961 0.0142 0.7715
9.500 1.4404 0.02819 0.02170 -0.0946 0.0140 0.7738
9.750 1.4579 0.02921 0.02289 -0.0930 0.0138 0.7757
10.000 1.4740 0.03034 0.02419 -0.0911 0.0137 0.7777
10.250 1.4886 0.03156 0.02559 -0.0891 0.0135 0.7798
10.500 1.5017 0.03288 0.02708 -0.0868 0.0133 0.7820
10.750 1.5130 0.03426 0.02865 -0.0844 0.0131 0.7843
11.000 1.5219 0.03573 0.03030 -0.0817 0.0130 0.7868
11.250 1.5274 0.03727 0.03201 -0.0785 0.0128 0.7892
11.500 1.5271 0.03880 0.03373 -0.0744 0.0127 0.7912
11.750 1.5267 0.04057 0.03569 -0.0707 0.0126 0.7932
12.000 1.5254 0.04249 0.03780 -0.0672 0.0125 0.7952
12.250 1.5214 0.04473 0.04022 -0.0638 0.0124 0.7973
12.500 1.5158 0.04719 0.04288 -0.0607 0.0123 0.7994
12.750 1.5081 0.05000 0.04587 -0.0580 0.0123 0.8015
13.000 1.4975 0.05332 0.04938 -0.0558 0.0122 0.8037
13.250 1.4835 0.05731 0.05358 -0.0544 0.0122 0.8056
13.500 1.4647 0.06234 0.05885 -0.0541 0.0121 0.8071
13.750 1.4420 0.06876 0.06550 -0.0557 0.0121 0.8087
14.000 1.4094 0.07855 0.07558 -0.0612 0.0121 0.8099
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