NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 500,000 Max Cl/Cd: 100.79 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21010-il-500000.txt Download as CSV file: xf-sc21010-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6108 0.06122 0.05858 -0.0617 0.9999 0.0234
-14.500 -0.7025 0.06691 0.06409 -0.0627 0.9999 0.0228
-14.250 -0.7397 0.05774 0.05479 -0.0688 0.9999 0.0226
-14.000 -0.7712 0.05204 0.04899 -0.0708 0.9999 0.0225
-13.750 -0.8031 0.04879 0.04569 -0.0688 0.9999 0.0224
-13.500 -0.8329 0.04586 0.04269 -0.0666 0.9999 0.0223
-13.250 -0.8508 0.04119 0.03776 -0.0693 0.9999 0.0223
-13.000 -0.8511 0.03650 0.03267 -0.0723 0.9997 0.0224
-12.750 -0.8242 0.03207 0.02772 -0.0784 0.9979 0.0228
-12.500 -0.7932 0.02914 0.02438 -0.0829 0.9965 0.0231
-12.250 -0.7642 0.02545 0.02039 -0.0868 0.9955 0.0238
-12.000 -0.7315 0.02431 0.01919 -0.0894 0.9946 0.0244
-11.750 -0.6981 0.02332 0.01809 -0.0919 0.9937 0.0252
-11.500 -0.6665 0.02219 0.01682 -0.0939 0.9921 0.0260
-11.250 -0.6338 0.02094 0.01541 -0.0960 0.9906 0.0267
-11.000 -0.6003 0.01993 0.01422 -0.0981 0.9893 0.0275
-10.750 -0.5667 0.01870 0.01283 -0.1003 0.9882 0.0283
-10.500 -0.5331 0.01749 0.01160 -0.1025 0.9873 0.0295
-10.250 -0.4986 0.01688 0.01096 -0.1046 0.9863 0.0307
-10.000 -0.4637 0.01638 0.01039 -0.1067 0.9854 0.0324
-9.750 -0.4283 0.01598 0.00991 -0.1087 0.9846 0.0337
-9.500 -0.3921 0.01484 0.00875 -0.1115 0.9841 0.0359
-9.250 -0.3560 0.01438 0.00829 -0.1138 0.9836 0.0382
-9.000 -0.3244 0.01401 0.00786 -0.1149 0.9813 0.0402
-8.750 -0.2897 0.01331 0.00716 -0.1171 0.9797 0.0436
-8.500 -0.2556 0.01299 0.00684 -0.1188 0.9780 0.0470
-8.250 -0.2195 0.01254 0.00635 -0.1210 0.9768 0.0507
-8.000 -0.1832 0.01216 0.00600 -0.1233 0.9756 0.0558
-7.750 -0.1463 0.01178 0.00561 -0.1256 0.9746 0.0624
-7.500 -0.1093 0.01146 0.00531 -0.1278 0.9737 0.0712
-7.250 -0.0713 0.01102 0.00498 -0.1305 0.9731 0.0905
-7.000 -0.0334 0.01063 0.00472 -0.1331 0.9725 0.1210
-6.750 0.0048 0.01020 0.00449 -0.1358 0.9720 0.1675
-6.500 0.0439 0.00968 0.00427 -0.1389 0.9717 0.2461
-6.250 0.0834 0.00919 0.00412 -0.1421 0.9714 0.3396
-6.000 0.1219 0.00890 0.00403 -0.1447 0.9710 0.4053
-5.750 0.1501 0.00880 0.00404 -0.1449 0.9666 0.4434
-5.500 0.1847 0.00868 0.00401 -0.1465 0.9648 0.4770
-5.250 0.2198 0.00858 0.00396 -0.1481 0.9633 0.5050
-5.000 0.2548 0.00848 0.00393 -0.1497 0.9619 0.5286
-4.750 0.2900 0.00839 0.00389 -0.1512 0.9605 0.5477
-4.500 0.3250 0.00831 0.00385 -0.1527 0.9593 0.5678
-4.250 0.3599 0.00823 0.00382 -0.1541 0.9580 0.5827
-4.000 0.3896 0.00823 0.00387 -0.1545 0.9546 0.5962
-3.750 0.4192 0.00821 0.00390 -0.1547 0.9505 0.6114
-3.500 0.4515 0.00813 0.00387 -0.1555 0.9474 0.6267
-3.250 0.4856 0.00792 0.00370 -0.1564 0.9435 0.6402
-3.000 0.5123 0.00774 0.00356 -0.1555 0.9336 0.6503
-2.750 0.5402 0.00753 0.00336 -0.1547 0.9228 0.6600
-2.500 0.5682 0.00739 0.00321 -0.1541 0.9126 0.6707
-2.250 0.5945 0.00730 0.00316 -0.1532 0.8997 0.6797
-1.750 0.6486 0.00723 0.00307 -0.1518 0.8685 0.6980
-1.500 0.6761 0.00725 0.00308 -0.1513 0.8516 0.7075
-1.250 0.7033 0.00727 0.00313 -0.1507 0.8333 0.7151
-1.000 0.7304 0.00735 0.00314 -0.1501 0.8071 0.7235
-0.750 0.7559 0.00750 0.00320 -0.1491 0.7648 0.7306
-0.500 0.7772 0.00809 0.00329 -0.1473 0.6520 0.7389
-0.250 0.7893 0.00973 0.00388 -0.1442 0.4323 0.7451
0.000 0.8073 0.01108 0.00442 -0.1426 0.2661 0.7527
0.250 0.8283 0.01206 0.00488 -0.1414 0.1564 0.7589
0.500 0.8515 0.01277 0.00530 -0.1405 0.0972 0.7652
0.750 0.8766 0.01330 0.00569 -0.1399 0.0728 0.7720
1.000 0.9016 0.01371 0.00608 -0.1391 0.0620 0.7774
1.250 0.9268 0.01417 0.00650 -0.1385 0.0550 0.7841
1.500 0.9522 0.01454 0.00688 -0.1378 0.0505 0.7901
1.750 0.9759 0.01512 0.00747 -0.1368 0.0463 0.7961
2.000 1.0017 0.01548 0.00786 -0.1363 0.0434 0.8027
2.250 1.0255 0.01593 0.00833 -0.1353 0.0405 0.8075
2.500 1.0481 0.01667 0.00909 -0.1342 0.0381 0.8130
2.750 1.0731 0.01710 0.00958 -0.1334 0.0362 0.8185
3.000 1.0967 0.01758 0.01009 -0.1324 0.0344 0.8231
3.250 1.1188 0.01835 0.01085 -0.1313 0.0326 0.8288
3.500 1.1413 0.01914 0.01171 -0.1301 0.0312 0.8341
3.750 1.1647 0.01962 0.01226 -0.1291 0.0298 0.8394
4.000 1.1882 0.02022 0.01290 -0.1281 0.0286 0.8457
4.250 1.2107 0.02083 0.01354 -0.1270 0.0276 0.8509
4.500 1.2315 0.02191 0.01464 -0.1256 0.0266 0.8563
4.750 1.2538 0.02316 0.01599 -0.1245 0.0259 0.8616
5.000 1.2763 0.02391 0.01686 -0.1234 0.0253 0.8662
5.250 1.2987 0.02482 0.01788 -0.1222 0.0246 0.8715
5.750 1.3423 0.02645 0.01970 -0.1199 0.0232 0.8821
6.000 1.3634 0.02723 0.02054 -0.1187 0.0226 0.8884
6.250 1.3835 0.02825 0.02162 -0.1173 0.0221 0.8945
6.500 1.4021 0.03075 0.02428 -0.1160 0.0215 0.9007
6.750 1.4196 0.03230 0.02608 -0.1141 0.0212 0.9073
7.000 1.4354 0.03373 0.02777 -0.1120 0.0209 0.9147
7.250 1.4490 0.03557 0.02989 -0.1096 0.0206 0.9231
7.750 1.4629 0.04005 0.03503 -0.1028 0.0201 1.0001
8.000 1.4662 0.04323 0.03856 -0.0995 0.0199 1.0001
8.250 1.4624 0.04675 0.04244 -0.0954 0.0197 1.0001
8.500 1.4512 0.05017 0.04620 -0.0903 0.0196 1.0001
8.750 1.4333 0.05349 0.04980 -0.0847 0.0194 1.0001
9.000 1.4080 0.05785 0.05446 -0.0793 0.0194 1.0001
9.250 1.3789 0.06283 0.05975 -0.0749 0.0194 1.0001
9.500 1.3382 0.06975 0.06701 -0.0718 0.0195 1.0001
9.750 1.2929 0.07820 0.07577 -0.0714 0.0198 1.0001
10.000 1.2520 0.08742 0.08523 -0.0742 0.0201 1.0001
10.250 1.2100 0.09930 0.09734 -0.0815 0.0203 1.0001
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