NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 200,000 Max Cl/Cd: 67.75 at α=-0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21010-il-200000-n5.txt Download as CSV file: xf-sc21010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1010 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7426 0.05697 0.05240 -0.0692 0.9999 0.0230
-13.750 -0.7696 0.05231 0.04764 -0.0703 0.9999 0.0230
-13.500 -0.7973 0.04914 0.04439 -0.0687 0.9999 0.0229
-13.250 -0.8161 0.04493 0.03994 -0.0703 0.9999 0.0230
-13.000 -0.8213 0.04094 0.03563 -0.0724 0.9999 0.0231
-12.750 -0.8137 0.03838 0.03290 -0.0732 0.9999 0.0234
-12.500 -0.8009 0.03628 0.03064 -0.0739 0.9999 0.0237
-12.250 -0.7786 0.03415 0.02830 -0.0762 0.9989 0.0242
-12.000 -0.7495 0.03192 0.02580 -0.0796 0.9970 0.0248
-11.750 -0.7191 0.02978 0.02336 -0.0827 0.9954 0.0255
-11.500 -0.6874 0.02791 0.02117 -0.0856 0.9940 0.0267
-11.250 -0.6564 0.02623 0.01911 -0.0880 0.9924 0.0279
-11.000 -0.6261 0.02485 0.01765 -0.0900 0.9906 0.0288
-10.750 -0.5945 0.02379 0.01651 -0.0919 0.9888 0.0298
-10.500 -0.5621 0.02274 0.01533 -0.0939 0.9872 0.0309
-10.250 -0.5293 0.02171 0.01415 -0.0959 0.9858 0.0323
-10.000 -0.4959 0.02083 0.01308 -0.0978 0.9846 0.0339
-9.750 -0.4621 0.01998 0.01226 -0.1001 0.9836 0.0358
-9.500 -0.4306 0.01933 0.01155 -0.1016 0.9815 0.0380
-9.250 -0.3987 0.01866 0.01076 -0.1030 0.9792 0.0401
-9.000 -0.3652 0.01790 0.01000 -0.1050 0.9774 0.0425
-8.750 -0.3315 0.01741 0.00948 -0.1069 0.9757 0.0459
-8.500 -0.2971 0.01692 0.00891 -0.1088 0.9743 0.0493
-8.250 -0.2618 0.01636 0.00838 -0.1111 0.9732 0.0537
-8.000 -0.2265 0.01598 0.00794 -0.1131 0.9720 0.0589
-7.750 -0.1902 0.01548 0.00746 -0.1156 0.9712 0.0659
-7.500 -0.1585 0.01511 0.00711 -0.1169 0.9687 0.0749
-7.250 -0.1259 0.01476 0.00680 -0.1184 0.9662 0.0874
-7.000 -0.0914 0.01440 0.00650 -0.1203 0.9641 0.1066
-6.750 -0.0556 0.01402 0.00622 -0.1225 0.9624 0.1338
-6.500 -0.0186 0.01359 0.00597 -0.1250 0.9610 0.1764
-6.250 0.0195 0.01309 0.00575 -0.1279 0.9601 0.2478
-6.000 0.0575 0.01264 0.00564 -0.1307 0.9592 0.3353
-5.750 0.0944 0.01236 0.00562 -0.1331 0.9583 0.4108
-5.500 0.1305 0.01223 0.00561 -0.1350 0.9574 0.4567
-5.250 0.1577 0.01223 0.00569 -0.1349 0.9529 0.4875
-5.000 0.1895 0.01219 0.00573 -0.1358 0.9500 0.5165
-4.750 0.2228 0.01217 0.00575 -0.1370 0.9478 0.5379
-4.500 0.2565 0.01214 0.00579 -0.1382 0.9461 0.5598
-4.250 0.2906 0.01212 0.00583 -0.1395 0.9446 0.5834
-4.000 0.3249 0.01210 0.00586 -0.1408 0.9431 0.6024
-3.750 0.3515 0.01218 0.00601 -0.1404 0.9385 0.6152
-3.500 0.3816 0.01222 0.00610 -0.1408 0.9351 0.6274
-3.250 0.4138 0.01223 0.00615 -0.1417 0.9325 0.6396
-3.000 0.4465 0.01223 0.00622 -0.1426 0.9305 0.6505
-2.750 0.4802 0.01221 0.00626 -0.1437 0.9287 0.6612
-2.500 0.5081 0.01230 0.00640 -0.1436 0.9238 0.6724
-2.250 0.5377 0.01227 0.00646 -0.1436 0.9183 0.6810
-2.000 0.5751 0.01191 0.00614 -0.1449 0.9113 0.6910
-1.750 0.6058 0.01144 0.00572 -0.1443 0.8929 0.6995
-1.500 0.6365 0.01109 0.00539 -0.1439 0.8713 0.7085
-1.250 0.6656 0.01090 0.00522 -0.1433 0.8494 0.7165
-1.000 0.6938 0.01076 0.00503 -0.1425 0.8139 0.7246
-0.750 0.7213 0.01075 0.00492 -0.1416 0.7667 0.7316
-0.500 0.7466 0.01102 0.00479 -0.1402 0.6653 0.7393
-0.250 0.7583 0.01238 0.00513 -0.1364 0.4747 0.7450
0.000 0.7734 0.01375 0.00572 -0.1341 0.3210 0.7527
0.250 0.7923 0.01479 0.00625 -0.1326 0.2145 0.7594
0.500 0.8135 0.01564 0.00675 -0.1314 0.1414 0.7667
0.750 0.8368 0.01628 0.00720 -0.1306 0.1045 0.7736
1.000 0.8602 0.01684 0.00766 -0.1297 0.0834 0.7798
1.250 0.8851 0.01736 0.00814 -0.1291 0.0703 0.7873
1.500 0.9086 0.01783 0.00863 -0.1280 0.0624 0.7929
1.750 0.9324 0.01840 0.00916 -0.1272 0.0562 0.8000
2.000 0.9563 0.01886 0.00969 -0.1263 0.0516 0.8059
2.250 0.9792 0.01947 0.01029 -0.1253 0.0478 0.8124
2.500 1.0027 0.02007 0.01094 -0.1244 0.0448 0.8190
2.750 1.0254 0.02061 0.01154 -0.1232 0.0418 0.8253
3.000 1.0483 0.02133 0.01226 -0.1223 0.0394 0.8327
3.250 1.0695 0.02207 0.01307 -0.1209 0.0377 0.8384
3.500 1.0925 0.02276 0.01384 -0.1200 0.0357 0.8449
3.750 1.1150 0.02342 0.01453 -0.1189 0.0338 0.8503
4.000 1.1362 0.02423 0.01536 -0.1177 0.0322 0.8561
4.250 1.1585 0.02514 0.01636 -0.1167 0.0310 0.8627
4.500 1.1797 0.02602 0.01737 -0.1153 0.0298 0.8690
4.750 1.2019 0.02698 0.01843 -0.1142 0.0287 0.8763
5.000 1.2225 0.02787 0.01941 -0.1129 0.0278 0.8827
5.250 1.2436 0.02879 0.02037 -0.1117 0.0269 0.8899
5.500 1.2632 0.02996 0.02159 -0.1104 0.0261 0.8966
5.750 1.2840 0.03108 0.02296 -0.1090 0.0251 0.9045
6.000 1.3029 0.03229 0.02440 -0.1074 0.0243 0.9131
6.250 1.3208 0.03359 0.02590 -0.1056 0.0236 0.9240
6.500 1.3364 0.03483 0.02734 -0.1035 0.0230 0.9436
6.750 1.3531 0.03617 0.02885 -0.1018 0.0226 1.0001
7.000 1.3708 0.03768 0.03049 -0.1005 0.0221 1.0001
7.250 1.3869 0.03932 0.03226 -0.0991 0.0218 1.0001
7.500 1.4004 0.04145 0.03455 -0.0973 0.0214 1.0001
7.750 1.4075 0.04415 0.03769 -0.0945 0.0211 1.0001
8.000 1.4087 0.04717 0.04116 -0.0911 0.0206 1.0001
8.250 1.4032 0.05025 0.04464 -0.0869 0.0202 1.0001
8.500 1.3932 0.05332 0.04804 -0.0824 0.0199 1.0001
8.750 1.3804 0.05668 0.05173 -0.0782 0.0196 1.0001
9.000 1.3647 0.06041 0.05576 -0.0746 0.0194 1.0001
9.250 1.3451 0.06473 0.06038 -0.0716 0.0192 1.0001
9.500 1.3201 0.07002 0.06597 -0.0695 0.0191 1.0001
9.750 1.2898 0.07655 0.07281 -0.0691 0.0191 1.0001
10.000 1.2514 0.08532 0.08190 -0.0713 0.0192 1.0001
10.250 1.1950 0.10027 0.09722 -0.0804 0.0195 1.0001
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