S1012 (s1012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 100,000 Max Cl/Cd: 31.12 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1012-il-100000-n5.txt Download as CSV file: xf-s1012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1012
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8402 0.08205 0.07636 -0.0381 1.0000 0.0423
-13.750 -0.8804 0.07207 0.06615 -0.0446 1.0000 0.0420
-13.500 -0.9114 0.06510 0.05894 -0.0479 1.0000 0.0419
-13.250 -0.9392 0.05951 0.05306 -0.0491 1.0000 0.0422
-13.000 -0.9605 0.05510 0.04834 -0.0490 1.0000 0.0425
-12.750 -0.9772 0.05142 0.04437 -0.0479 1.0000 0.0430
-12.500 -0.9750 0.04947 0.04239 -0.0469 1.0000 0.0438
-12.250 -0.9745 0.04754 0.04038 -0.0456 1.0000 0.0447
-12.000 -0.9748 0.04557 0.03827 -0.0440 1.0000 0.0456
-11.750 -0.9748 0.04360 0.03611 -0.0421 1.0000 0.0467
-11.500 -0.9742 0.04167 0.03397 -0.0399 1.0000 0.0481
-11.250 -0.9730 0.03975 0.03173 -0.0374 1.0000 0.0498
-11.000 -0.9697 0.03789 0.02954 -0.0349 1.0000 0.0516
-10.750 -0.9577 0.03672 0.02840 -0.0335 1.0000 0.0533
-10.500 -0.9459 0.03561 0.02723 -0.0319 1.0000 0.0552
-10.250 -0.9338 0.03436 0.02581 -0.0302 1.0000 0.0576
-10.000 -0.9215 0.03302 0.02418 -0.0284 1.0000 0.0605
-9.750 -0.9076 0.03185 0.02295 -0.0269 1.0000 0.0629
-9.500 -0.8952 0.03101 0.02210 -0.0249 1.0000 0.0653
-9.250 -0.8850 0.03022 0.02122 -0.0225 1.0000 0.0682
-9.000 -0.8768 0.02943 0.02024 -0.0195 1.0000 0.0712
-8.750 -0.8701 0.02866 0.01940 -0.0163 1.0000 0.0738
-8.500 -0.8646 0.02809 0.01884 -0.0129 1.0000 0.0762
-8.250 -0.8528 0.02746 0.01812 -0.0106 0.9989 0.0797
-8.000 -0.8256 0.02659 0.01703 -0.0111 0.9946 0.0849
-7.750 -0.8007 0.02573 0.01621 -0.0114 0.9903 0.0892
-7.500 -0.7742 0.02503 0.01540 -0.0118 0.9864 0.0952
-7.250 -0.7464 0.02424 0.01457 -0.0125 0.9832 0.1010
-7.000 -0.7210 0.02361 0.01390 -0.0127 0.9791 0.1074
-6.750 -0.6951 0.02296 0.01320 -0.0128 0.9753 0.1144
-6.500 -0.6682 0.02239 0.01259 -0.0133 0.9723 0.1224
-6.250 -0.6405 0.02178 0.01200 -0.0138 0.9699 0.1310
-6.000 -0.6187 0.02135 0.01150 -0.0131 0.9659 0.1407
-5.750 -0.5956 0.02083 0.01105 -0.0128 0.9625 0.1511
-5.500 -0.5694 0.02033 0.01058 -0.0130 0.9595 0.1643
-5.250 -0.5414 0.01985 0.01016 -0.0135 0.9571 0.1804
-5.000 -0.5183 0.01944 0.00980 -0.0131 0.9540 0.1986
-4.750 -0.4989 0.01905 0.00950 -0.0119 0.9502 0.2202
-4.250 -0.4522 0.01811 0.00894 -0.0111 0.9444 0.2922
-4.000 -0.4283 0.01753 0.00869 -0.0109 0.9419 0.3536
-3.750 -0.4160 0.01699 0.00853 -0.0083 0.9380 0.4281
-3.500 -0.4028 0.01645 0.00858 -0.0054 0.9339 0.5337
-3.250 -0.3715 0.01686 0.00966 -0.0042 0.9325 0.6586
-3.000 -0.3462 0.01725 0.01004 -0.0031 0.9299 0.7160
-2.750 -0.3221 0.01746 0.01017 -0.0021 0.9272 0.7484
-2.500 -0.3045 0.01771 0.01035 0.0001 0.9233 0.7707
-2.000 -0.2601 0.01832 0.01085 0.0032 0.9161 0.8036
-1.750 -0.2324 0.01861 0.01109 0.0037 0.9136 0.8179
-1.500 -0.2010 0.01892 0.01135 0.0036 0.9115 0.8311
-1.250 -0.1711 0.01932 0.01174 0.0039 0.9087 0.8428
-1.000 -0.1445 0.01974 0.01216 0.0049 0.9049 0.8567
-0.750 -0.1065 0.02020 0.01261 0.0039 0.9026 0.8709
-0.500 -0.0720 0.02042 0.01282 0.0030 0.8997 0.8818
-0.250 -0.0274 0.02055 0.01293 0.0000 0.8977 0.8866
0.000 -0.0001 0.02055 0.01292 0.0000 0.8931 0.8932
0.250 0.0275 0.02055 0.01293 0.0000 0.8866 0.8977
0.500 0.0720 0.02042 0.01282 -0.0030 0.8818 0.8997
0.750 0.1068 0.02019 0.01260 -0.0039 0.8707 0.9026
1.000 0.1445 0.01974 0.01215 -0.0049 0.8567 0.9049
1.250 0.1710 0.01932 0.01174 -0.0039 0.8426 0.9088
1.500 0.2008 0.01892 0.01135 -0.0035 0.8308 0.9115
1.750 0.2325 0.01860 0.01108 -0.0037 0.8178 0.9136
2.000 0.2601 0.01832 0.01085 -0.0032 0.8035 0.9161
2.250 0.2852 0.01802 0.01060 -0.0022 0.7879 0.9193
2.500 0.3045 0.01772 0.01035 -0.0001 0.7708 0.9233
2.750 0.3223 0.01746 0.01017 0.0021 0.7487 0.9272
3.000 0.3462 0.01724 0.01004 0.0030 0.7159 0.9299
3.250 0.3714 0.01686 0.00967 0.0042 0.6595 0.9325
3.500 0.4029 0.01644 0.00858 0.0054 0.5347 0.9339
3.750 0.4159 0.01699 0.00852 0.0083 0.4280 0.9380
4.000 0.4283 0.01753 0.00868 0.0109 0.3536 0.9419
4.250 0.4522 0.01811 0.00894 0.0111 0.2920 0.9444
4.750 0.4989 0.01905 0.00950 0.0119 0.2199 0.9503
5.000 0.5183 0.01944 0.00980 0.0131 0.1985 0.9540
5.250 0.5414 0.01985 0.01015 0.0135 0.1803 0.9571
5.500 0.5694 0.02033 0.01058 0.0130 0.1641 0.9595
5.750 0.5956 0.02082 0.01103 0.0128 0.1511 0.9625
6.000 0.6188 0.02135 0.01150 0.0131 0.1406 0.9660
6.250 0.6405 0.02178 0.01200 0.0138 0.1310 0.9699
6.500 0.6683 0.02238 0.01259 0.0133 0.1224 0.9723
6.750 0.6952 0.02296 0.01320 0.0128 0.1144 0.9753
7.000 0.7210 0.02361 0.01389 0.0126 0.1074 0.9792
7.250 0.7464 0.02424 0.01457 0.0125 0.1009 0.9832
7.500 0.7743 0.02502 0.01540 0.0118 0.0951 0.9864
7.750 0.8008 0.02573 0.01621 0.0114 0.0892 0.9904
8.000 0.8257 0.02659 0.01702 0.0111 0.0848 0.9946
8.250 0.8530 0.02746 0.01811 0.0106 0.0797 0.9989
8.500 0.8645 0.02809 0.01883 0.0129 0.0762 1.0000
8.750 0.8701 0.02866 0.01941 0.0163 0.0738 1.0000
9.000 0.8769 0.02944 0.02024 0.0195 0.0713 1.0000
9.250 0.8850 0.03022 0.02122 0.0225 0.0682 1.0000
9.500 0.8952 0.03101 0.02210 0.0249 0.0653 1.0000
9.750 0.9077 0.03185 0.02294 0.0268 0.0629 1.0000
10.000 0.9215 0.03302 0.02417 0.0284 0.0605 1.0000
10.250 0.9341 0.03437 0.02583 0.0302 0.0576 1.0000
10.500 0.9461 0.03561 0.02723 0.0318 0.0552 1.0000
10.750 0.9579 0.03673 0.02842 0.0334 0.0533 1.0000
11.000 0.9700 0.03790 0.02955 0.0348 0.0516 1.0000
11.250 0.9737 0.03976 0.03174 0.0373 0.0498 1.0000
11.500 0.9745 0.04169 0.03398 0.0398 0.0480 1.0000
11.750 0.9752 0.04362 0.03614 0.0420 0.0467 1.0000
12.000 0.9751 0.04562 0.03832 0.0439 0.0456 1.0000
12.250 0.9751 0.04754 0.04037 0.0455 0.0446 1.0000
12.500 0.9767 0.04933 0.04223 0.0468 0.0437 1.0000
12.750 0.9778 0.05145 0.04439 0.0478 0.0430 1.0000
13.000 0.9614 0.05510 0.04834 0.0489 0.0425 1.0000
13.250 0.9379 0.05969 0.05326 0.0490 0.0421 1.0000
13.500 0.9107 0.06526 0.05911 0.0477 0.0419 1.0000
13.750 0.8796 0.07228 0.06638 0.0443 0.0420 1.0000
14.000 0.8413 0.08202 0.07632 0.0380 0.0423 1.0000
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Polar data table (+)
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