NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 200,000 Max Cl/Cd: 44.13 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20706-il-200000-n5.txt Download as CSV file: xf-sc20706-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5976 0.08878 0.08510 -0.0162 1.0000 0.0154
-9.500 -0.6023 0.08414 0.08050 -0.0183 1.0000 0.0157
-9.250 -0.6099 0.07969 0.07612 -0.0199 1.0000 0.0158
-9.000 -0.6164 0.07429 0.07078 -0.0236 1.0000 0.0157
-8.750 -0.6187 0.06705 0.06351 -0.0319 1.0000 0.0155
-8.500 -0.6174 0.06040 0.05673 -0.0373 1.0000 0.0156
-8.250 -0.6108 0.05405 0.05017 -0.0416 1.0000 0.0157
-8.000 -0.5990 0.04779 0.04362 -0.0453 1.0000 0.0154
-7.750 -0.5808 0.04149 0.03691 -0.0490 1.0000 0.0151
-7.500 -0.5560 0.03540 0.03029 -0.0526 1.0000 0.0149
-7.250 -0.5262 0.03005 0.02432 -0.0558 1.0000 0.0149
-7.000 -0.4944 0.02593 0.01957 -0.0582 1.0000 0.0152
-6.750 -0.4630 0.02297 0.01608 -0.0599 1.0000 0.0158
-6.500 -0.4328 0.02088 0.01359 -0.0608 1.0000 0.0165
-6.250 -0.4036 0.01943 0.01181 -0.0615 1.0000 0.0176
-6.000 -0.3742 0.01783 0.01009 -0.0625 1.0000 0.0197
-5.750 -0.3445 0.01663 0.00876 -0.0632 1.0000 0.0208
-5.500 -0.3142 0.01558 0.00761 -0.0640 1.0000 0.0222
-5.250 -0.2830 0.01468 0.00660 -0.0650 1.0000 0.0244
-5.000 -0.2519 0.01402 0.00579 -0.0660 1.0000 0.0268
-4.750 -0.2195 0.01330 0.00507 -0.0675 1.0000 0.0348
-4.500 -0.1877 0.01276 0.00450 -0.0687 1.0000 0.0438
-4.250 -0.1561 0.01231 0.00407 -0.0698 1.0000 0.0637
-4.000 -0.1220 0.01169 0.00370 -0.0718 1.0000 0.1221
-3.750 -0.0785 0.01042 0.00335 -0.0766 1.0000 0.3605
-3.500 -0.0427 0.00982 0.00344 -0.0788 1.0000 0.5510
-3.250 -0.0145 0.00974 0.00357 -0.0788 1.0000 0.6239
-2.750 0.0389 0.00981 0.00374 -0.0780 1.0000 0.6926
-2.500 0.0656 0.00987 0.00382 -0.0776 1.0000 0.7133
-2.250 0.0920 0.00993 0.00390 -0.0772 1.0000 0.7293
-2.000 0.1184 0.01000 0.00400 -0.0768 1.0000 0.7432
-1.750 0.1448 0.01006 0.00409 -0.0765 1.0000 0.7540
-1.500 0.1715 0.01012 0.00418 -0.0762 1.0000 0.7625
-1.250 0.1989 0.01018 0.00427 -0.0762 1.0000 0.7712
-1.000 0.2252 0.01025 0.00441 -0.0758 1.0000 0.7783
-0.750 0.2520 0.01033 0.00456 -0.0757 1.0000 0.7861
-0.500 0.2785 0.01042 0.00473 -0.0754 1.0000 0.7932
-0.250 0.3054 0.01051 0.00492 -0.0753 1.0000 0.8002
0.250 0.4054 0.00974 0.00443 -0.0841 0.9483 0.8119
0.500 0.4770 0.01081 0.00361 -0.0918 0.4426 0.8146
0.750 0.4954 0.01231 0.00404 -0.0904 0.1912 0.8211
1.000 0.5188 0.01324 0.00448 -0.0898 0.0770 0.8273
1.250 0.5440 0.01378 0.00495 -0.0891 0.0507 0.8337
1.500 0.5697 0.01428 0.00544 -0.0886 0.0377 0.8404
1.750 0.5949 0.01480 0.00605 -0.0879 0.0313 0.8470
2.000 0.6200 0.01553 0.00679 -0.0874 0.0248 0.8533
2.250 0.6444 0.01622 0.00764 -0.0864 0.0229 0.8593
2.500 0.6697 0.01711 0.00864 -0.0857 0.0210 0.8661
2.750 0.6934 0.01810 0.00975 -0.0846 0.0197 0.8722
3.000 0.7191 0.01930 0.01108 -0.0839 0.0188 0.8791
3.250 0.7431 0.02060 0.01256 -0.0827 0.0182 0.8852
3.750 0.7902 0.02397 0.01637 -0.0809 0.0157 0.9000
4.000 0.8143 0.02561 0.01838 -0.0798 0.0150 0.9078
4.250 0.8363 0.02784 0.02106 -0.0782 0.0145 0.9156
4.500 0.8564 0.03074 0.02448 -0.0762 0.0142 0.9240
4.750 0.8740 0.03428 0.02856 -0.0739 0.0139 0.9341
5.000 0.8883 0.03831 0.03311 -0.0713 0.0139 0.9474
5.250 0.9003 0.04271 0.03800 -0.0687 0.0140 0.9912
5.500 0.9146 0.04804 0.04378 -0.0674 0.0141 1.0000
5.750 0.9254 0.05348 0.04958 -0.0662 0.0144 1.0000
6.000 0.9340 0.05911 0.05553 -0.0654 0.0145 1.0000
6.250 0.9417 0.06501 0.06172 -0.0649 0.0141 1.0000
6.500 0.9463 0.07135 0.06831 -0.0652 0.0134 1.0000
6.750 0.9472 0.07743 0.07457 -0.0662 0.0130 1.0000
7.000 0.9443 0.08356 0.08083 -0.0679 0.0131 1.0000
7.250 0.9378 0.08959 0.08695 -0.0702 0.0132 1.0000
7.500 0.9272 0.09538 0.09278 -0.0731 0.0134 1.0000
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Polar data table (+)
Polar graphs
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