NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.17 at α=-3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21006-il-1000000-n5.txt Download as CSV file: xf-sc21006-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1006 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5357 0.10534 0.10365 -0.0204 0.9999 0.0040
-12.500 -0.5396 0.10137 0.09970 -0.0208 0.9999 0.0040
-12.250 -0.5414 0.09731 0.09565 -0.0219 0.9997 0.0041
-12.000 -0.5378 0.09197 0.09033 -0.0258 0.9988 0.0042
-11.750 -0.5340 0.08636 0.08473 -0.0302 0.9975 0.0043
-11.250 -0.5408 0.02423 0.02140 -0.1059 0.9853 0.0050
-11.000 -0.5071 0.01991 0.01654 -0.1111 0.9850 0.0053
-10.750 -0.4741 0.01756 0.01383 -0.1143 0.9848 0.0055
-10.500 -0.4416 0.01608 0.01212 -0.1165 0.9846 0.0057
-10.250 -0.4099 0.01532 0.01120 -0.1182 0.9843 0.0059
-10.000 -0.3767 0.01386 0.00950 -0.1204 0.9841 0.0062
-9.750 -0.3423 0.01212 0.00750 -0.1230 0.9840 0.0068
-9.500 -0.3102 0.01155 0.00685 -0.1245 0.9837 0.0072
-9.250 -0.2783 0.01105 0.00628 -0.1259 0.9834 0.0076
-9.000 -0.2466 0.01054 0.00567 -0.1272 0.9830 0.0080
-8.750 -0.2169 0.01006 0.00512 -0.1280 0.9819 0.0083
-8.500 -0.1861 0.00959 0.00457 -0.1290 0.9809 0.0086
-8.250 -0.1550 0.00916 0.00407 -0.1301 0.9800 0.0089
-8.000 -0.1240 0.00882 0.00368 -0.1311 0.9792 0.0094
-7.750 -0.0930 0.00854 0.00334 -0.1321 0.9783 0.0098
-7.500 -0.0617 0.00825 0.00299 -0.1331 0.9776 0.0100
-7.250 -0.0293 0.00785 0.00252 -0.1343 0.9769 0.0122
-7.000 0.0019 0.00763 0.00231 -0.1353 0.9761 0.0150
-6.750 0.0329 0.00747 0.00213 -0.1361 0.9752 0.0172
-6.500 0.0643 0.00728 0.00195 -0.1371 0.9743 0.0230
-6.250 0.0953 0.00711 0.00180 -0.1379 0.9736 0.0307
-6.000 0.1266 0.00691 0.00168 -0.1389 0.9729 0.0500
-5.750 0.1585 0.00662 0.00156 -0.1401 0.9724 0.0955
-5.500 0.1899 0.00643 0.00146 -0.1412 0.9718 0.1308
-5.250 0.2215 0.00622 0.00138 -0.1422 0.9712 0.1711
-5.000 0.2538 0.00593 0.00132 -0.1436 0.9707 0.2444
-4.750 0.2860 0.00564 0.00130 -0.1449 0.9700 0.3297
-4.500 0.3146 0.00549 0.00128 -0.1451 0.9669 0.3773
-4.250 0.3439 0.00537 0.00123 -0.1455 0.9626 0.4016
-4.000 0.3744 0.00522 0.00116 -0.1460 0.9583 0.4300
-3.750 0.4034 0.00509 0.00115 -0.1462 0.9529 0.4708
-3.500 0.4320 0.00498 0.00110 -0.1462 0.9439 0.4992
-3.250 0.4596 0.00489 0.00106 -0.1459 0.9297 0.5286
-3.000 0.4858 0.00485 0.00100 -0.1453 0.8974 0.5533
-2.750 0.5022 0.00584 0.00109 -0.1423 0.6798 0.5686
-2.500 0.5224 0.00701 0.00143 -0.1410 0.4633 0.5867
-2.250 0.5470 0.00768 0.00164 -0.1406 0.3307 0.6068
-2.000 0.5727 0.00818 0.00184 -0.1403 0.2332 0.6282
-1.750 0.5983 0.00873 0.00207 -0.1401 0.1308 0.6504
-1.500 0.6243 0.00920 0.00229 -0.1398 0.0571 0.6703
-1.250 0.6515 0.00943 0.00248 -0.1396 0.0355 0.6850
-1.000 0.6788 0.00964 0.00266 -0.1395 0.0250 0.6969
-0.750 0.7061 0.00984 0.00287 -0.1393 0.0189 0.7075
-0.500 0.7334 0.01000 0.00306 -0.1391 0.0165 0.7178
-0.250 0.7604 0.01025 0.00330 -0.1389 0.0124 0.7286
0.000 0.7873 0.01050 0.00362 -0.1386 0.0110 0.7384
0.250 0.8142 0.01074 0.00391 -0.1383 0.0102 0.7479
0.500 0.8409 0.01101 0.00423 -0.1380 0.0095 0.7576
0.750 0.8674 0.01130 0.00456 -0.1376 0.0088 0.7666
1.000 0.8938 0.01162 0.00492 -0.1372 0.0081 0.7739
1.250 0.9195 0.01210 0.00548 -0.1366 0.0074 0.7817
1.500 0.9433 0.01301 0.00654 -0.1356 0.0067 0.7895
1.750 0.9685 0.01357 0.00718 -0.1349 0.0066 0.7983
2.000 0.9934 0.01421 0.00793 -0.1342 0.0066 0.8075
2.250 1.0186 0.01474 0.00855 -0.1336 0.0064 0.8155
2.500 1.0437 0.01533 0.00922 -0.1329 0.0061 0.8223
2.750 1.0680 0.01615 0.01019 -0.1321 0.0060 0.8279
3.000 1.0922 0.01708 0.01125 -0.1312 0.0058 0.8339
3.250 1.1163 0.01806 0.01239 -0.1303 0.0056 0.8393
3.500 1.1399 0.01916 0.01366 -0.1293 0.0054 0.8451
4.000 1.1868 0.02126 0.01608 -0.1274 0.0049 0.8570
4.250 1.2105 0.02192 0.01686 -0.1267 0.0047 0.8642
4.500 1.2343 0.02231 0.01733 -0.1260 0.0045 0.8727
4.750 1.2582 0.02260 0.01771 -0.1253 0.0043 0.8821
5.250 1.2924 0.02726 0.02307 -0.1214 0.0038 0.9040
5.750 1.3127 0.03397 0.03070 -0.1150 0.0036 1.0001
7.250 1.0765 0.11005 0.10896 -0.1066 0.0032 1.0001
7.500 1.0630 0.11876 0.11765 -0.1124 0.0032 1.0001
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Polar data table (+)
Polar graphs
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