NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 200,000 Max Cl/Cd: 69.32 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21010-il-200000.txt Download as CSV file: xf-sc21010-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5055 0.08878 0.08503 -0.0386 0.9999 0.0785
-11.250 -0.5298 0.08465 0.08100 -0.0391 0.9999 0.0806
-10.750 -0.6646 0.04461 0.03970 -0.0684 0.9999 0.0482
-10.500 -0.6469 0.03915 0.03387 -0.0717 0.9999 0.0472
-10.250 -0.6212 0.03428 0.02845 -0.0755 0.9999 0.0470
-10.000 -0.5920 0.03119 0.02480 -0.0782 0.9999 0.0482
-9.750 -0.5623 0.02910 0.02221 -0.0802 0.9999 0.0490
-9.500 -0.5308 0.02564 0.01846 -0.0828 0.9999 0.0502
-9.250 -0.5022 0.02418 0.01691 -0.0839 0.9999 0.0518
-9.000 -0.4736 0.02316 0.01577 -0.0848 0.9999 0.0540
-8.750 -0.4448 0.02237 0.01481 -0.0856 0.9999 0.0571
-8.500 -0.4139 0.02111 0.01338 -0.0868 0.9999 0.0599
-8.250 -0.3843 0.02015 0.01246 -0.0878 0.9999 0.0633
-8.000 -0.3555 0.01964 0.01188 -0.0885 0.9999 0.0677
-7.750 -0.3240 0.01881 0.01102 -0.0898 0.9999 0.0728
-7.500 -0.2937 0.01832 0.01058 -0.0909 0.9999 0.0787
-7.250 -0.2613 0.01774 0.01000 -0.0925 0.9999 0.0867
-7.000 -0.2302 0.01741 0.00966 -0.0937 0.9999 0.0964
-6.750 -0.1942 0.01683 0.00919 -0.0961 0.9999 0.1142
-6.500 -0.1548 0.01617 0.00876 -0.0994 0.9999 0.1520
-6.250 -0.1054 0.01514 0.00844 -0.1053 0.9999 0.2902
-6.000 -0.0673 0.01482 0.00860 -0.1083 0.9999 0.4224
-5.750 -0.0379 0.01491 0.00885 -0.1090 0.9999 0.4798
-5.500 -0.0105 0.01511 0.00911 -0.1092 0.9999 0.5198
-5.250 0.0173 0.01535 0.00941 -0.1095 0.9994 0.5536
-5.000 0.0513 0.01554 0.00967 -0.1109 0.9971 0.5817
-4.750 0.0862 0.01578 0.00991 -0.1125 0.9952 0.6063
-4.500 0.1194 0.01603 0.01023 -0.1136 0.9932 0.6268
-4.250 0.1504 0.01626 0.01049 -0.1143 0.9897 0.6439
-4.000 0.1852 0.01650 0.01077 -0.1158 0.9865 0.6611
-3.750 0.2210 0.01680 0.01111 -0.1173 0.9840 0.6793
-3.500 0.2492 0.01707 0.01143 -0.1174 0.9803 0.6944
-3.250 0.2805 0.01730 0.01168 -0.1182 0.9765 0.7078
-3.000 0.3157 0.01749 0.01192 -0.1197 0.9734 0.7192
-2.750 0.3547 0.01766 0.01215 -0.1218 0.9710 0.7295
-2.500 0.3818 0.01778 0.01231 -0.1218 0.9638 0.7405
-2.250 0.4187 0.01786 0.01246 -0.1234 0.9598 0.7502
-2.000 0.4574 0.01790 0.01257 -0.1255 0.9563 0.7600
-1.750 0.4882 0.01789 0.01261 -0.1259 0.9479 0.7705
-1.500 0.5345 0.01720 0.01202 -0.1284 0.9369 0.7781
-1.250 0.5991 0.01572 0.01061 -0.1338 0.9247 0.7880
-1.000 0.6470 0.01464 0.00965 -0.1361 0.9146 0.7954
-0.750 0.6890 0.01354 0.00862 -0.1371 0.8997 0.8043
-0.500 0.7201 0.01292 0.00809 -0.1363 0.8845 0.8120
-0.250 0.7496 0.01244 0.00768 -0.1354 0.8651 0.8201
0.000 0.7777 0.01201 0.00728 -0.1341 0.8380 0.8280
0.250 0.8034 0.01173 0.00699 -0.1324 0.7935 0.8361
0.500 0.8249 0.01190 0.00655 -0.1294 0.6404 0.8449
0.750 0.8232 0.01416 0.00718 -0.1233 0.3542 0.8526
1.000 0.8318 0.01632 0.00812 -0.1203 0.1494 0.8616
1.250 0.8481 0.01733 0.00882 -0.1180 0.1076 0.8692
1.500 0.8700 0.01808 0.00952 -0.1168 0.0919 0.8779
1.750 0.8894 0.01875 0.01015 -0.1150 0.0824 0.8866
2.000 0.9105 0.01938 0.01082 -0.1135 0.0756 0.8956
2.250 0.9325 0.02012 0.01152 -0.1123 0.0701 0.9051
2.500 0.9518 0.02096 0.01239 -0.1104 0.0657 0.9144
2.750 0.9737 0.02153 0.01301 -0.1091 0.0616 0.9244
3.000 0.9948 0.02234 0.01379 -0.1077 0.0585 0.9358
3.250 1.0161 0.02360 0.01508 -0.1062 0.0557 0.9491
3.500 1.0375 0.02417 0.01580 -0.1046 0.0529 0.9716
3.750 1.0671 0.02527 0.01696 -0.1051 0.0502 1.0001
4.000 1.0984 0.02688 0.01855 -0.1060 0.0482 1.0001
4.250 1.1306 0.02979 0.02161 -0.1070 0.0467 1.0001
4.500 1.1586 0.03130 0.02343 -0.1069 0.0454 1.0001
4.750 1.1852 0.03314 0.02557 -0.1066 0.0437 1.0001
5.000 1.2101 0.03558 0.02833 -0.1061 0.0428 1.0001
5.250 1.2320 0.03873 0.03189 -0.1051 0.0426 1.0001
5.500 1.2483 0.04288 0.03655 -0.1032 0.0432 1.0001
5.750 1.2594 0.04780 0.04195 -0.1008 0.0445 1.0001
6.000 1.2680 0.05278 0.04726 -0.0987 0.0458 1.0001
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Polar data table (+)
Polar graphs
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