NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 500,000 Max Cl/Cd: 71.58 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20710-il-500000.txt Download as CSV file: xf-sc20710-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6698 0.09315 0.09054 -0.0382 1.0000 0.0246
-12.750 -0.7743 0.06333 0.06047 -0.0582 1.0000 0.0226
-12.500 -0.8190 0.05489 0.05182 -0.0622 1.0000 0.0223
-12.250 -0.8594 0.04925 0.04598 -0.0619 1.0000 0.0221
-12.000 -0.8977 0.04593 0.04252 -0.0576 1.0000 0.0219
-11.750 -0.9278 0.04126 0.03756 -0.0561 1.0000 0.0217
-11.500 -0.9385 0.03686 0.03279 -0.0558 1.0000 0.0218
-11.250 -0.9352 0.03345 0.02904 -0.0556 1.0000 0.0219
-11.000 -0.9241 0.03070 0.02599 -0.0556 1.0000 0.0221
-10.750 -0.9081 0.02844 0.02346 -0.0557 1.0000 0.0224
-10.500 -0.8892 0.02648 0.02125 -0.0559 1.0000 0.0228
-10.250 -0.8681 0.02485 0.01940 -0.0560 1.0000 0.0232
-10.000 -0.8456 0.02352 0.01787 -0.0562 1.0000 0.0236
-9.750 -0.8218 0.02267 0.01685 -0.0563 1.0000 0.0240
-9.500 -0.7984 0.02073 0.01478 -0.0568 1.0000 0.0249
-9.250 -0.7738 0.01994 0.01397 -0.0570 1.0000 0.0256
-9.000 -0.7483 0.01923 0.01321 -0.0573 1.0000 0.0263
-8.750 -0.7219 0.01854 0.01245 -0.0577 1.0000 0.0271
-8.500 -0.6949 0.01788 0.01172 -0.0581 1.0000 0.0281
-8.250 -0.6675 0.01734 0.01109 -0.0586 1.0000 0.0290
-8.000 -0.6374 0.01627 0.00997 -0.0599 1.0000 0.0306
-7.750 -0.6064 0.01577 0.00949 -0.0612 0.9997 0.0323
-7.500 -0.5730 0.01539 0.00907 -0.0628 0.9989 0.0346
-7.250 -0.5387 0.01472 0.00838 -0.0648 0.9984 0.0376
-7.000 -0.5050 0.01442 0.00809 -0.0665 0.9976 0.0408
-6.750 -0.4711 0.01413 0.00776 -0.0681 0.9968 0.0436
-6.500 -0.4362 0.01361 0.00727 -0.0703 0.9963 0.0478
-6.250 -0.4025 0.01341 0.00704 -0.0719 0.9957 0.0513
-6.000 -0.3673 0.01299 0.00664 -0.0740 0.9953 0.0561
-5.750 -0.3330 0.01279 0.00645 -0.0757 0.9947 0.0612
-5.500 -0.2976 0.01247 0.00616 -0.0777 0.9944 0.0685
-5.250 -0.2624 0.01224 0.00595 -0.0797 0.9939 0.0777
-5.000 -0.2274 0.01190 0.00572 -0.0816 0.9932 0.0948
-4.750 -0.1912 0.01152 0.00551 -0.0839 0.9926 0.1303
-4.500 -0.1511 0.01092 0.00532 -0.0875 0.9930 0.2222
-4.250 -0.1056 0.01002 0.00509 -0.0926 0.9944 0.3918
-4.000 -0.0644 0.00943 0.00514 -0.0963 0.9951 0.5587
-3.750 -0.0297 0.00947 0.00527 -0.0978 0.9944 0.6036
-3.500 0.0032 0.00954 0.00537 -0.0989 0.9929 0.6261
-3.250 0.0350 0.00963 0.00546 -0.0997 0.9907 0.6445
-3.000 0.0672 0.00976 0.00561 -0.1005 0.9888 0.6600
-2.750 0.1005 0.00986 0.00573 -0.1016 0.9871 0.6684
-2.500 0.1379 0.00994 0.00580 -0.1035 0.9853 0.6791
-2.250 0.1753 0.01002 0.00594 -0.1052 0.9824 0.6894
-2.000 0.2084 0.01000 0.00596 -0.1059 0.9770 0.6979
-1.750 0.2514 0.00980 0.00579 -0.1088 0.9734 0.7020
-1.500 0.2935 0.00945 0.00544 -0.1113 0.9663 0.7071
-1.250 0.3407 0.00904 0.00507 -0.1148 0.9614 0.7124
-1.000 0.3867 0.00857 0.00466 -0.1179 0.9550 0.7160
-0.750 0.4230 0.00830 0.00442 -0.1190 0.9461 0.7206
-0.500 0.4559 0.00812 0.00424 -0.1196 0.9345 0.7255
-0.250 0.4868 0.00795 0.00410 -0.1197 0.9193 0.7281
0.000 0.5173 0.00783 0.00398 -0.1197 0.8994 0.7300
0.250 0.5455 0.00781 0.00392 -0.1192 0.8689 0.7320
0.500 0.5712 0.00798 0.00382 -0.1180 0.7825 0.7342
0.750 0.5834 0.00943 0.00409 -0.1144 0.5387 0.7367
1.000 0.6020 0.01068 0.00446 -0.1130 0.3471 0.7393
1.250 0.6253 0.01164 0.00477 -0.1124 0.2068 0.7420
1.500 0.6494 0.01231 0.00505 -0.1118 0.1262 0.7440
1.750 0.6747 0.01276 0.00535 -0.1113 0.0940 0.7457
2.000 0.7010 0.01312 0.00565 -0.1109 0.0783 0.7475
2.250 0.7273 0.01351 0.00599 -0.1105 0.0682 0.7495
2.500 0.7541 0.01380 0.00626 -0.1102 0.0618 0.7520
2.750 0.7808 0.01422 0.00667 -0.1099 0.0566 0.7548
3.000 0.8088 0.01449 0.00694 -0.1100 0.0528 0.7576
3.250 0.8343 0.01502 0.00744 -0.1095 0.0481 0.7595
3.500 0.8608 0.01525 0.00772 -0.1091 0.0455 0.7611
3.750 0.8869 0.01555 0.00804 -0.1087 0.0424 0.7628
4.000 0.9110 0.01623 0.00872 -0.1079 0.0392 0.7648
4.250 0.9375 0.01655 0.00909 -0.1075 0.0368 0.7669
4.500 0.9635 0.01697 0.00950 -0.1071 0.0344 0.7693
4.750 0.9873 0.01791 0.01046 -0.1063 0.0322 0.7718
5.000 1.0142 0.01834 0.01093 -0.1061 0.0306 0.7743
5.250 1.0391 0.01877 0.01140 -0.1054 0.0290 0.7761
5.500 1.0631 0.01933 0.01199 -0.1046 0.0278 0.7780
5.750 1.0845 0.02071 0.01343 -0.1034 0.0266 0.7802
6.000 1.1093 0.02132 0.01416 -0.1027 0.0260 0.7827
6.250 1.1339 0.02212 0.01506 -0.1020 0.0253 0.7851
6.500 1.1585 0.02299 0.01603 -0.1014 0.0246 0.7876
6.750 1.1829 0.02392 0.01704 -0.1007 0.0240 0.7900
7.000 1.2057 0.02480 0.01803 -0.0998 0.0234 0.7917
7.250 1.2281 0.02574 0.01906 -0.0988 0.0230 0.7935
7.500 1.2498 0.02686 0.02026 -0.0978 0.0225 0.7956
7.750 1.2684 0.02923 0.02282 -0.0964 0.0219 0.7977
8.000 1.2876 0.03071 0.02455 -0.0950 0.0215 0.8002
8.250 1.3061 0.03233 0.02643 -0.0934 0.0212 0.8027
8.500 1.1734 0.06493 0.06196 -0.0733 0.0291 0.8025
8.750 1.1804 0.06608 0.06315 -0.0715 0.0284 0.8049
9.000 1.1794 0.06785 0.06501 -0.0689 0.0280 0.8067
9.250 1.1680 0.06982 0.06709 -0.0651 0.0278 0.8087
9.500 1.1543 0.07245 0.06983 -0.0619 0.0276 0.8108
9.750 1.1415 0.07534 0.07280 -0.0598 0.0275 0.8130
10.000 1.1257 0.07910 0.07666 -0.0589 0.0274 0.8152
10.250 1.1082 0.08376 0.08141 -0.0596 0.0273 0.8173
10.500 1.0860 0.09013 0.08788 -0.0627 0.0271 0.8191
10.750 0.8340 0.11667 0.11465 -0.0686 0.0265 0.8078
11.000 1.0436 0.07314 0.07070 -0.0432 0.0212 0.8186
11.250 1.0057 0.08236 0.08006 -0.0475 0.0214 0.8192
11.500 0.9625 0.09449 0.09231 -0.0549 0.0217 0.8192
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