NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il) Reynolds number: 200,000 Max Cl/Cd: 39.45 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20010-il-200000.txt Download as CSV file: xf-sc20010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0010 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5702 0.08888 0.08535 -0.0097 1.0000 0.0779
-9.750 -0.5908 0.08117 0.07766 -0.0141 1.0000 0.0795
-9.500 -0.6295 0.07062 0.06711 -0.0217 1.0000 0.0798
-9.250 -0.8600 0.05430 0.04943 -0.0183 1.0000 0.0480
-9.000 -0.8590 0.04971 0.04461 -0.0171 1.0000 0.0471
-8.750 -0.8575 0.04482 0.03935 -0.0155 1.0000 0.0460
-8.500 -0.8565 0.03884 0.03276 -0.0133 1.0000 0.0441
-8.250 -0.8484 0.03384 0.02708 -0.0111 1.0000 0.0432
-8.000 -0.8307 0.03117 0.02407 -0.0099 1.0000 0.0436
-7.750 -0.8105 0.02902 0.02164 -0.0090 1.0000 0.0444
-7.500 -0.7889 0.02710 0.01945 -0.0081 1.0000 0.0456
-7.250 -0.7660 0.02558 0.01766 -0.0073 1.0000 0.0474
-7.000 -0.7428 0.02420 0.01597 -0.0065 1.0000 0.0495
-6.750 -0.7191 0.02242 0.01422 -0.0061 1.0000 0.0520
-6.500 -0.6947 0.02138 0.01311 -0.0055 1.0000 0.0549
-6.250 -0.6699 0.02047 0.01204 -0.0049 1.0000 0.0583
-6.000 -0.6466 0.01908 0.01070 -0.0043 1.0000 0.0628
-5.750 -0.6224 0.01849 0.01006 -0.0036 1.0000 0.0684
-5.500 -0.5996 0.01742 0.00902 -0.0028 1.0000 0.0740
-5.250 -0.5762 0.01689 0.00849 -0.0021 1.0000 0.0807
-5.000 -0.5544 0.01608 0.00773 -0.0011 1.0000 0.0873
-4.750 -0.5324 0.01562 0.00728 -0.0001 1.0000 0.0947
-4.500 -0.5125 0.01495 0.00669 0.0012 1.0000 0.1024
-4.250 -0.4924 0.01459 0.00631 0.0025 1.0000 0.1110
-4.000 -0.4754 0.01402 0.00585 0.0042 1.0000 0.1222
-3.750 -0.4589 0.01355 0.00549 0.0059 1.0000 0.1374
-3.500 -0.4423 0.01300 0.00515 0.0073 1.0000 0.1685
-3.250 -0.4258 0.01190 0.00478 0.0084 1.0000 0.2917
-3.000 -0.4036 0.01023 0.00473 0.0086 0.9975 0.6194
-2.750 -0.3681 0.01022 0.00491 0.0073 0.9925 0.7139
-2.500 -0.3320 0.01026 0.00499 0.0059 0.9868 0.7551
-2.250 -0.2954 0.01033 0.00509 0.0044 0.9824 0.7837
-2.000 -0.2623 0.01039 0.00516 0.0036 0.9762 0.8069
-1.750 -0.2263 0.01046 0.00525 0.0024 0.9720 0.8267
-1.500 -0.1934 0.01056 0.00538 0.0018 0.9669 0.8469
-1.250 -0.1625 0.01069 0.00553 0.0019 0.9611 0.8673
-1.000 -0.1302 0.01082 0.00569 0.0017 0.9571 0.8855
-0.750 -0.1013 0.01098 0.00586 0.0022 0.9515 0.9016
-0.500 -0.0699 0.01110 0.00598 0.0021 0.9454 0.9147
-0.250 -0.0342 0.01115 0.00603 0.0010 0.9408 0.9255
0.000 0.0000 0.01123 0.00612 0.0000 0.9341 0.9341
0.250 0.0342 0.01115 0.00603 -0.0010 0.9255 0.9408
0.500 0.0699 0.01110 0.00598 -0.0021 0.9147 0.9454
0.750 0.1013 0.01098 0.00586 -0.0022 0.9016 0.9515
1.000 0.1302 0.01082 0.00569 -0.0017 0.8855 0.9571
1.250 0.1625 0.01069 0.00553 -0.0019 0.8673 0.9611
1.500 0.1933 0.01056 0.00538 -0.0018 0.8469 0.9669
1.750 0.2263 0.01046 0.00525 -0.0024 0.8267 0.9721
2.000 0.2623 0.01039 0.00516 -0.0036 0.8069 0.9762
2.250 0.2954 0.01033 0.00509 -0.0044 0.7838 0.9824
2.500 0.3321 0.01026 0.00499 -0.0059 0.7551 0.9868
2.750 0.3681 0.01022 0.00491 -0.0073 0.7139 0.9926
3.000 0.4036 0.01023 0.00473 -0.0086 0.6195 0.9975
3.250 0.4257 0.01190 0.00478 -0.0083 0.2920 1.0000
3.500 0.4422 0.01300 0.00515 -0.0073 0.1685 1.0000
3.750 0.4588 0.01355 0.00549 -0.0058 0.1375 1.0000
4.000 0.4753 0.01402 0.00585 -0.0042 0.1222 1.0000
4.250 0.4924 0.01458 0.00631 -0.0025 0.1110 1.0000
4.500 0.5125 0.01495 0.00669 -0.0012 0.1025 1.0000
4.750 0.5324 0.01562 0.00728 0.0001 0.0947 1.0000
5.000 0.5544 0.01608 0.00772 0.0011 0.0873 1.0000
5.250 0.5762 0.01689 0.00849 0.0021 0.0807 1.0000
5.500 0.5996 0.01742 0.00902 0.0028 0.0740 1.0000
5.750 0.6224 0.01849 0.01006 0.0036 0.0684 1.0000
6.000 0.6466 0.01908 0.01070 0.0043 0.0628 1.0000
6.250 0.6699 0.02047 0.01204 0.0049 0.0583 1.0000
6.500 0.6947 0.02138 0.01312 0.0055 0.0549 1.0000
6.750 0.7191 0.02242 0.01422 0.0061 0.0520 1.0000
7.000 0.7428 0.02420 0.01598 0.0065 0.0495 1.0000
7.250 0.7660 0.02558 0.01766 0.0073 0.0475 1.0000
7.500 0.7889 0.02710 0.01945 0.0081 0.0456 1.0000
7.750 0.8105 0.02902 0.02163 0.0090 0.0444 1.0000
8.000 0.8308 0.03117 0.02406 0.0099 0.0436 1.0000
8.250 0.8484 0.03387 0.02711 0.0111 0.0432 1.0000
8.500 0.8566 0.03883 0.03275 0.0133 0.0441 1.0000
8.750 0.8575 0.04482 0.03935 0.0155 0.0459 1.0000
9.000 0.8591 0.04972 0.04461 0.0171 0.0471 1.0000
9.250 0.8602 0.05431 0.04943 0.0183 0.0480 1.0000
10.250 0.5593 0.09454 0.09098 0.0074 0.0763 1.0000
10.500 0.5544 0.09929 0.09572 0.0059 0.0748 1.0000
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Polar data table (+)
Polar graphs
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