SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Reynolds number: 100,000 Max Cl/Cd: 28.15 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-100000.txt Download as CSV file: xf-nasasc2-0714-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6153 0.09243 0.08654 -0.0515 1.0000 0.1227
-11.250 -0.6001 0.09024 0.08437 -0.0492 1.0000 0.1207
-11.000 -0.7412 0.07131 0.06525 -0.0552 1.0000 0.1036
-10.750 -0.8739 0.06162 0.05471 -0.0533 1.0000 0.0962
-10.500 -0.8757 0.05818 0.05096 -0.0526 1.0000 0.0956
-10.250 -0.8731 0.05414 0.04665 -0.0522 1.0000 0.0954
-10.000 -0.8680 0.05030 0.04243 -0.0524 1.0000 0.0960
-9.750 -0.8555 0.04684 0.03893 -0.0521 1.0000 0.0977
-9.500 -0.8386 0.04502 0.03713 -0.0514 1.0000 0.0997
-9.250 -0.8221 0.04254 0.03442 -0.0515 1.0000 0.1012
-9.000 -0.8034 0.03999 0.03157 -0.0518 1.0000 0.1026
-8.750 -0.7824 0.03779 0.02906 -0.0522 1.0000 0.1048
-8.500 -0.7590 0.03594 0.02679 -0.0528 1.0000 0.1078
-8.250 -0.7354 0.03388 0.02445 -0.0532 1.0000 0.1103
-8.000 -0.7132 0.03228 0.02287 -0.0528 1.0000 0.1130
-7.750 -0.6894 0.03111 0.02165 -0.0526 1.0000 0.1166
-7.500 -0.6641 0.03005 0.02040 -0.0527 1.0000 0.1212
-7.250 -0.6395 0.02880 0.01903 -0.0524 1.0000 0.1253
-7.000 -0.6168 0.02777 0.01813 -0.0516 1.0000 0.1298
-6.750 -0.5919 0.02700 0.01728 -0.0514 1.0000 0.1362
-6.500 -0.5686 0.02607 0.01642 -0.0507 1.0000 0.1428
-6.250 -0.5446 0.02536 0.01579 -0.0502 1.0000 0.1510
-6.000 -0.5209 0.02458 0.01514 -0.0495 1.0000 0.1609
-5.750 -0.4960 0.02389 0.01460 -0.0492 1.0000 0.1752
-5.500 -0.4700 0.02319 0.01415 -0.0493 1.0000 0.1949
-5.250 -0.4406 0.02236 0.01370 -0.0503 1.0000 0.2311
-5.000 -0.4007 0.02069 0.01398 -0.0541 1.0000 0.4602
-4.750 -0.3972 0.02241 0.01607 -0.0467 1.0000 0.5660
-4.500 -0.3818 0.02386 0.01744 -0.0428 1.0000 0.6025
-4.250 -0.3712 0.02529 0.01883 -0.0376 1.0000 0.6218
-4.000 -0.3604 0.02658 0.02008 -0.0327 1.0000 0.6382
-3.750 -0.3485 0.02772 0.02118 -0.0282 1.0000 0.6537
-3.500 -0.3349 0.02869 0.02212 -0.0243 1.0000 0.6691
-3.250 -0.3296 0.02964 0.02307 -0.0180 1.0000 0.6790
-3.000 -0.3177 0.03031 0.02371 -0.0139 1.0000 0.6915
-2.750 -0.3011 0.03081 0.02417 -0.0113 1.0000 0.7055
-2.500 -0.2857 0.03126 0.02459 -0.0085 1.0000 0.7184
-2.250 -0.2769 0.03153 0.02486 -0.0039 1.0000 0.7279
-2.000 -0.2627 0.03182 0.02514 -0.0010 1.0000 0.7419
-1.750 -0.2535 0.03215 0.02547 0.0034 1.0000 0.7585
-1.500 -0.2471 0.03234 0.02568 0.0085 1.0000 0.7762
-1.250 -0.2403 0.03237 0.02573 0.0132 1.0000 0.7943
-1.000 -0.2292 0.03226 0.02562 0.0165 1.0000 0.8101
-0.750 -0.2097 0.03218 0.02552 0.0172 1.0000 0.8218
-0.500 -0.1916 0.03201 0.02535 0.0181 1.0000 0.8302
-0.250 -0.1656 0.03205 0.02537 0.0167 1.0000 0.8363
0.000 -0.1224 0.03224 0.02554 0.0129 0.9915 0.8414
0.250 -0.0746 0.03263 0.02592 0.0077 0.9824 0.8464
0.500 -0.0294 0.03283 0.02611 0.0032 0.9712 0.8508
0.750 0.0098 0.03275 0.02606 0.0005 0.9584 0.8559
1.000 0.0560 0.03284 0.02618 -0.0038 0.9450 0.8609
1.250 0.1069 0.03290 0.02627 -0.0090 0.9311 0.8638
1.500 0.1531 0.03249 0.02592 -0.0125 0.9161 0.8658
1.750 0.2046 0.03174 0.02522 -0.0163 0.8977 0.8684
2.000 0.2611 0.03060 0.02417 -0.0203 0.8785 0.8712
2.250 0.3109 0.02962 0.02328 -0.0235 0.8622 0.8732
2.500 0.3605 0.02847 0.02224 -0.0264 0.8458 0.8747
2.750 0.4150 0.02668 0.02057 -0.0292 0.8262 0.8762
3.000 0.4713 0.02451 0.01853 -0.0316 0.8050 0.8776
3.250 0.5004 0.02330 0.01743 -0.0304 0.7729 0.8793
3.500 0.5342 0.02196 0.01614 -0.0296 0.7226 0.8814
3.750 0.6018 0.02138 0.01409 -0.0332 0.4463 0.8835
4.000 0.6081 0.02308 0.01462 -0.0300 0.2883 0.8848
4.250 0.6256 0.02430 0.01529 -0.0288 0.2268 0.8870
4.500 0.6498 0.02532 0.01601 -0.0288 0.1959 0.8892
4.750 0.6783 0.02626 0.01677 -0.0295 0.1757 0.8909
5.000 0.7106 0.02727 0.01766 -0.0309 0.1615 0.8919
5.250 0.7443 0.02838 0.01859 -0.0326 0.1506 0.8930
5.500 0.7735 0.02908 0.01934 -0.0330 0.1421 0.8947
5.750 0.8066 0.03029 0.02045 -0.0344 0.1346 0.8964
6.000 0.8377 0.03123 0.02153 -0.0353 0.1281 0.8975
6.250 0.8725 0.03272 0.02286 -0.0372 0.1223 0.8987
6.500 0.9018 0.03397 0.02438 -0.0378 0.1174 0.8998
6.750 0.9319 0.03532 0.02589 -0.0386 0.1131 0.9011
7.000 0.9623 0.03685 0.02745 -0.0397 0.1093 0.9024
7.250 0.9902 0.03911 0.02990 -0.0405 0.1060 0.9037
7.500 1.0126 0.04085 0.03208 -0.0400 0.1030 0.9053
7.750 1.0344 0.04306 0.03464 -0.0396 0.1010 0.9071
8.000 1.0524 0.04521 0.03711 -0.0385 0.0993 0.9089
8.250 1.0725 0.04727 0.03935 -0.0381 0.0973 0.9105
8.500 1.0969 0.04963 0.04169 -0.0387 0.0950 0.9121
8.750 1.1085 0.05341 0.04578 -0.0376 0.0937 0.9135
9.000 1.1145 0.05676 0.04957 -0.0356 0.0934 0.9149
9.250 1.1195 0.06071 0.05390 -0.0339 0.0935 0.9163
9.500 1.1250 0.06530 0.05877 -0.0328 0.0939 0.9177
9.750 1.0314 0.07286 0.06767 -0.0220 0.1010 0.9176
10.000 1.0037 0.07877 0.07387 -0.0202 0.1036 0.9185
10.250 0.9944 0.08425 0.07947 -0.0203 0.1055 0.9196
10.500 0.6452 0.12656 0.12257 -0.0260 0.1860 0.9124
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Polar data table (+)
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