SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 50,000 Max Cl/Cd: 37.06 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2030-il-50000-n5.txt Download as CSV file: xf-sd2030-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4640 0.09110 0.08415 -0.0395 1.0000 0.0581
-8.250 -0.4682 0.08779 0.08091 -0.0394 1.0000 0.0577
-8.000 -0.4721 0.08440 0.07760 -0.0394 1.0000 0.0572
-7.750 -0.4757 0.08091 0.07416 -0.0394 1.0000 0.0566
-7.500 -0.4801 0.07734 0.07062 -0.0395 1.0000 0.0558
-7.250 -0.4844 0.07371 0.06701 -0.0395 1.0000 0.0550
-7.000 -0.4879 0.06998 0.06326 -0.0395 1.0000 0.0540
-6.750 -0.4904 0.06609 0.05930 -0.0394 1.0000 0.0529
-6.500 -0.4910 0.06205 0.05514 -0.0392 1.0000 0.0518
-6.250 -0.4892 0.05792 0.05082 -0.0390 1.0000 0.0507
-6.000 -0.4847 0.05370 0.04630 -0.0387 1.0000 0.0497
-5.750 -0.4768 0.04964 0.04189 -0.0382 1.0000 0.0489
-5.500 -0.4657 0.04584 0.03764 -0.0376 1.0000 0.0483
-5.250 -0.4517 0.04240 0.03375 -0.0368 1.0000 0.0481
-5.000 -0.4353 0.03938 0.03027 -0.0359 1.0000 0.0481
-4.750 -0.4170 0.03671 0.02717 -0.0351 1.0000 0.0485
-4.500 -0.3973 0.03438 0.02444 -0.0342 1.0000 0.0492
-4.250 -0.3768 0.03258 0.02228 -0.0333 1.0000 0.0518
-4.000 -0.3549 0.03088 0.02016 -0.0324 1.0000 0.0554
-3.750 -0.3318 0.02926 0.01808 -0.0314 1.0000 0.0580
-3.500 -0.3090 0.02764 0.01626 -0.0304 1.0000 0.0599
-3.250 -0.2865 0.02640 0.01492 -0.0294 1.0000 0.0630
-3.000 -0.2637 0.02536 0.01371 -0.0283 1.0000 0.0673
-2.750 -0.2406 0.02440 0.01257 -0.0272 1.0000 0.0742
-2.500 -0.2184 0.02363 0.01172 -0.0264 1.0000 0.0886
-2.250 -0.1957 0.02276 0.01089 -0.0258 1.0000 0.1158
-2.000 -0.1728 0.02155 0.01022 -0.0255 1.0000 0.1976
-1.750 -0.1558 0.01940 0.00993 -0.0241 1.0000 0.5316
-1.500 -0.1206 0.01852 0.00988 -0.0229 1.0000 1.0000
-1.250 -0.1015 0.01864 0.00962 -0.0219 1.0000 1.0000
-1.000 -0.0820 0.01880 0.00945 -0.0210 1.0000 1.0000
-0.750 -0.0463 0.01919 0.00949 -0.0232 0.9938 1.0000
-0.500 -0.0109 0.01956 0.00954 -0.0254 0.9865 1.0000
-0.250 0.0246 0.01997 0.00969 -0.0276 0.9794 1.0000
0.000 0.0607 0.02038 0.00990 -0.0298 0.9719 1.0000
0.250 0.0944 0.02073 0.01006 -0.0316 0.9634 1.0000
0.500 0.1326 0.02117 0.01035 -0.0341 0.9561 1.0000
0.750 0.1648 0.02147 0.01055 -0.0355 0.9462 1.0000
1.000 0.1988 0.02179 0.01078 -0.0372 0.9365 1.0000
1.250 0.2368 0.02213 0.01106 -0.0395 0.9273 1.0000
1.500 0.2714 0.02239 0.01129 -0.0412 0.9164 1.0000
1.750 0.3045 0.02261 0.01151 -0.0424 0.9045 1.0000
2.000 0.3386 0.02279 0.01171 -0.0438 0.8923 1.0000
2.250 0.3735 0.02293 0.01189 -0.0451 0.8795 1.0000
2.500 0.4090 0.02300 0.01202 -0.0465 0.8660 1.0000
2.750 0.4447 0.02300 0.01213 -0.0477 0.8518 1.0000
3.000 0.4811 0.02291 0.01214 -0.0488 0.8368 1.0000
3.250 0.5184 0.02271 0.01208 -0.0498 0.8210 1.0000
3.500 0.5559 0.02241 0.01196 -0.0507 0.8043 1.0000
3.750 0.5851 0.02221 0.01191 -0.0501 0.7833 1.0000
4.000 0.6196 0.02183 0.01169 -0.0501 0.7620 1.0000
4.250 0.6477 0.02157 0.01163 -0.0490 0.7354 1.0000
4.500 0.6778 0.02124 0.01145 -0.0482 0.7052 1.0000
4.750 0.7048 0.02105 0.01136 -0.0468 0.6672 1.0000
5.000 0.7352 0.02081 0.01115 -0.0458 0.6207 1.0000
5.250 0.7627 0.02083 0.01112 -0.0444 0.5620 1.0000
5.500 0.7860 0.02121 0.01125 -0.0427 0.4961 1.0000
5.750 0.8044 0.02193 0.01166 -0.0405 0.4318 1.0000
6.000 0.8206 0.02285 0.01230 -0.0384 0.3740 1.0000
6.250 0.8359 0.02388 0.01307 -0.0364 0.3234 1.0000
6.500 0.8517 0.02497 0.01398 -0.0346 0.2792 1.0000
6.750 0.8679 0.02612 0.01504 -0.0330 0.2407 1.0000
7.000 0.8850 0.02732 0.01612 -0.0316 0.2084 1.0000
7.250 0.9031 0.02859 0.01731 -0.0304 0.1819 1.0000
7.500 0.9227 0.02988 0.01863 -0.0293 0.1589 1.0000
7.750 0.9420 0.03123 0.01994 -0.0283 0.1403 1.0000
8.000 0.9644 0.03272 0.02152 -0.0276 0.1261 1.0000
8.250 0.9847 0.03421 0.02315 -0.0267 0.1128 1.0000
8.500 1.0055 0.03583 0.02487 -0.0259 0.1021 1.0000
8.750 1.0286 0.03779 0.02715 -0.0252 0.0927 1.0000
9.000 1.0464 0.03969 0.02923 -0.0241 0.0838 1.0000
9.250 1.0648 0.04179 0.03148 -0.0231 0.0769 1.0000
9.500 1.0780 0.04425 0.03436 -0.0215 0.0694 1.0000
9.750 1.0909 0.04638 0.03653 -0.0201 0.0635 1.0000
10.000 1.0970 0.04952 0.04022 -0.0179 0.0584 1.0000
10.250 1.1010 0.05169 0.04267 -0.0158 0.0533 1.0000
10.500 1.1047 0.05457 0.04568 -0.0140 0.0501 1.0000
10.750 1.0952 0.05813 0.04976 -0.0108 0.0482 1.0000
11.000 1.0832 0.06167 0.05369 -0.0082 0.0466 1.0000
11.250 1.0695 0.06524 0.05755 -0.0062 0.0450 1.0000
11.500 1.0547 0.06909 0.06163 -0.0051 0.0439 1.0000
11.750 1.0365 0.07361 0.06638 -0.0049 0.0434 1.0000
12.000 1.0099 0.07990 0.07293 -0.0065 0.0443 1.0000
12.250 0.9791 0.08790 0.08114 -0.0103 0.0461 1.0000
12.500 0.9528 0.09647 0.08976 -0.0155 0.0476 1.0000
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Polar data table (+)
Polar graphs
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