NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il) Reynolds number: 500,000 Max Cl/Cd: 91.95 at α=-2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21006-il-500000-n5.txt Download as CSV file: xf-sc21006-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5394 0.09235 0.09006 -0.0229 0.9999 0.0066
-11.500 -0.5455 0.08920 0.08695 -0.0225 0.9999 0.0067
-11.250 -0.5540 0.08622 0.08401 -0.0217 0.9999 0.0067
-11.000 -0.5503 0.08116 0.07896 -0.0260 0.9979 0.0068
-10.750 -0.5408 0.07503 0.07284 -0.0331 0.9950 0.0070
-10.500 -0.5284 0.06672 0.06454 -0.0443 0.9918 0.0071
-10.250 -0.4955 0.03920 0.03649 -0.0840 0.9863 0.0070
-10.000 -0.4605 0.03004 0.02669 -0.0945 0.9855 0.0075
-9.750 -0.4251 0.02531 0.02144 -0.1000 0.9851 0.0082
-9.500 -0.3872 0.02057 0.01602 -0.1051 0.9850 0.0086
-9.250 -0.3521 0.01799 0.01301 -0.1081 0.9848 0.0090
-9.000 -0.3185 0.01641 0.01114 -0.1101 0.9846 0.0095
-8.750 -0.2858 0.01535 0.00984 -0.1118 0.9843 0.0099
-8.500 -0.2527 0.01415 0.00844 -0.1136 0.9841 0.0102
-8.250 -0.2188 0.01282 0.00694 -0.1157 0.9840 0.0110
-8.000 -0.1864 0.01230 0.00636 -0.1171 0.9837 0.0121
-7.750 -0.1533 0.01171 0.00569 -0.1187 0.9835 0.0128
-7.500 -0.1201 0.01116 0.00502 -0.1203 0.9833 0.0135
-7.250 -0.0893 0.01073 0.00452 -0.1212 0.9825 0.0148
-7.000 -0.0595 0.01042 0.00415 -0.1219 0.9814 0.0162
-6.750 -0.0281 0.01004 0.00371 -0.1229 0.9807 0.0203
-6.500 0.0021 0.00983 0.00348 -0.1237 0.9798 0.0250
-6.250 0.0329 0.00960 0.00326 -0.1246 0.9790 0.0365
-6.000 0.0648 0.00928 0.00309 -0.1259 0.9785 0.0738
-5.750 0.0965 0.00901 0.00297 -0.1271 0.9780 0.1178
-5.500 0.1284 0.00875 0.00287 -0.1283 0.9774 0.1680
-5.250 0.1617 0.00838 0.00279 -0.1300 0.9771 0.2613
-5.000 0.1950 0.00804 0.00278 -0.1317 0.9769 0.3660
-4.750 0.2267 0.00789 0.00278 -0.1328 0.9763 0.4159
-4.500 0.2579 0.00780 0.00280 -0.1337 0.9756 0.4514
-4.250 0.2892 0.00772 0.00283 -0.1347 0.9750 0.4944
-4.000 0.3204 0.00766 0.00288 -0.1355 0.9744 0.5298
-3.750 0.3520 0.00760 0.00293 -0.1364 0.9737 0.5622
-3.500 0.3861 0.00749 0.00294 -0.1379 0.9727 0.5942
-3.250 0.4263 0.00726 0.00281 -0.1405 0.9710 0.6198
-3.000 0.4593 0.00705 0.00270 -0.1414 0.9650 0.6436
-2.750 0.4986 0.00669 0.00244 -0.1436 0.9583 0.6668
-2.500 0.5309 0.00633 0.00215 -0.1439 0.9388 0.6858
-2.250 0.5609 0.00610 0.00188 -0.1435 0.8965 0.7014
-2.000 0.5797 0.00685 0.00177 -0.1406 0.6901 0.7134
-1.500 0.6166 0.00941 0.00258 -0.1372 0.2728 0.7334
-1.250 0.6396 0.01031 0.00295 -0.1365 0.1298 0.7446
-1.000 0.6644 0.01093 0.00325 -0.1360 0.0525 0.7557
-0.750 0.6906 0.01128 0.00353 -0.1356 0.0306 0.7649
-0.500 0.7172 0.01155 0.00382 -0.1352 0.0240 0.7745
-0.250 0.7434 0.01195 0.00425 -0.1347 0.0187 0.7840
0.000 0.7698 0.01224 0.00464 -0.1343 0.0167 0.7922
0.250 0.7960 0.01256 0.00499 -0.1339 0.0142 0.8001
0.500 0.8217 0.01301 0.00549 -0.1333 0.0126 0.8088
0.750 0.8455 0.01384 0.00643 -0.1323 0.0114 0.8173
1.000 0.8707 0.01432 0.00700 -0.1316 0.0109 0.8270
1.250 0.8955 0.01495 0.00775 -0.1308 0.0104 0.8366
1.500 0.9197 0.01570 0.00862 -0.1298 0.0098 0.8442
1.750 0.9440 0.01663 0.00967 -0.1289 0.0094 0.8513
2.000 0.9678 0.01772 0.01091 -0.1278 0.0091 0.8577
2.500 1.0163 0.02012 0.01365 -0.1259 0.0084 0.8712
2.750 1.0408 0.02081 0.01445 -0.1252 0.0079 0.8788
3.000 1.0643 0.02167 0.01548 -0.1243 0.0075 0.8869
3.250 1.0867 0.02316 0.01720 -0.1231 0.0072 0.8963
3.500 1.1052 0.02626 0.02075 -0.1211 0.0069 0.9075
3.750 1.1216 0.02930 0.02429 -0.1186 0.0066 0.9232
4.000 1.1350 0.03246 0.02794 -0.1153 0.0064 1.0001
4.250 1.1415 0.03992 0.03612 -0.1109 0.0061 1.0001
4.500 1.1436 0.04813 0.04491 -0.1063 0.0058 1.0001
4.750 1.1462 0.05501 0.05218 -0.1028 0.0054 1.0001
5.000 1.1479 0.06094 0.05840 -0.1000 0.0050 1.0001
5.250 1.1452 0.06707 0.06478 -0.0974 0.0049 1.0001
5.500 1.1383 0.07326 0.07119 -0.0952 0.0049 1.0001
5.750 1.1278 0.07930 0.07741 -0.0935 0.0048 1.0001
6.000 1.1136 0.08505 0.08329 -0.0923 0.0048 1.0001
6.250 1.0900 0.09057 0.08890 -0.0910 0.0049 1.0001
6.500 1.0688 0.09707 0.09548 -0.0931 0.0049 1.0001
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Polar data table (+)
Polar graphs
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