SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 200,000 Max Cl/Cd: 64.17 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8000-il-200000.txt Download as CSV file: xf-sd8000-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD8000-089-88
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 -0.5121 0.10357 0.09995 -0.0210 1.0000 0.0555
-9.750 -0.5171 0.09868 0.09511 -0.0252 1.0000 0.0557
-9.500 -0.5202 0.09368 0.09015 -0.0289 1.0000 0.0558
-9.250 -0.5174 0.08852 0.08501 -0.0271 1.0000 0.0570
-9.000 -0.5092 0.08576 0.08227 -0.0262 1.0000 0.0580
-8.750 -0.5052 0.08259 0.07912 -0.0267 1.0000 0.0590
-8.500 -0.5060 0.07880 0.07537 -0.0283 1.0000 0.0599
-8.250 -0.5919 0.05172 0.04797 -0.0489 1.0000 0.0339
-8.000 -0.5989 0.04653 0.04257 -0.0491 1.0000 0.0329
-7.750 -0.6065 0.04070 0.03636 -0.0484 1.0000 0.0318
-7.500 -0.6106 0.03483 0.02993 -0.0467 1.0000 0.0310
-7.250 -0.6055 0.03059 0.02515 -0.0448 1.0000 0.0310
-7.000 -0.5929 0.02818 0.02233 -0.0430 1.0000 0.0327
-6.750 -0.5776 0.02629 0.01997 -0.0412 1.0000 0.0345
-6.500 -0.5626 0.02335 0.01657 -0.0396 1.0000 0.0359
-6.250 -0.5444 0.02165 0.01478 -0.0383 1.0000 0.0381
-6.000 -0.5244 0.02055 0.01353 -0.0370 1.0000 0.0411
-5.750 -0.5037 0.01961 0.01230 -0.0357 1.0000 0.0452
-5.500 -0.4834 0.01830 0.01099 -0.0347 1.0000 0.0498
-5.250 -0.4616 0.01779 0.01029 -0.0335 1.0000 0.0554
-5.000 -0.4406 0.01662 0.00914 -0.0326 1.0000 0.0617
-4.750 -0.4184 0.01611 0.00849 -0.0315 1.0000 0.0688
-4.500 -0.3965 0.01532 0.00776 -0.0307 1.0000 0.0772
-4.250 -0.3741 0.01469 0.00712 -0.0299 1.0000 0.0869
-4.000 -0.3516 0.01419 0.00659 -0.0290 1.0000 0.0978
-3.750 -0.3291 0.01379 0.00620 -0.0283 1.0000 0.1111
-3.500 -0.3068 0.01337 0.00585 -0.0276 1.0000 0.1267
-3.250 -0.2838 0.01301 0.00556 -0.0270 0.9998 0.1464
-3.000 -0.2441 0.01259 0.00531 -0.0298 0.9951 0.1840
-2.750 -0.2059 0.01210 0.00513 -0.0324 0.9898 0.2457
-2.500 -0.1667 0.01159 0.00507 -0.0352 0.9848 0.3490
-2.250 -0.1308 0.01112 0.00507 -0.0372 0.9786 0.4663
-2.000 -0.0928 0.01076 0.00514 -0.0393 0.9727 0.5820
-1.750 -0.0588 0.01049 0.00520 -0.0402 0.9657 0.6760
-1.500 -0.0224 0.01027 0.00525 -0.0414 0.9593 0.7611
-1.250 0.0103 0.01010 0.00528 -0.0415 0.9518 0.8318
-1.000 0.0501 0.00998 0.00525 -0.0430 0.9459 0.8987
-0.750 0.1094 0.00988 0.00514 -0.0486 0.9441 0.9525
-0.500 0.1750 0.00972 0.00492 -0.0559 0.9426 0.9835
-0.250 0.2272 0.00954 0.00469 -0.0607 0.9353 1.0000
0.000 0.2668 0.00932 0.00442 -0.0628 0.9265 1.0000
0.250 0.2964 0.00915 0.00420 -0.0627 0.9138 1.0000
0.500 0.3214 0.00901 0.00401 -0.0617 0.8995 1.0000
0.750 0.3450 0.00889 0.00385 -0.0604 0.8845 1.0000
1.000 0.3682 0.00879 0.00369 -0.0589 0.8690 1.0000
1.250 0.3907 0.00872 0.00358 -0.0573 0.8510 1.0000
1.500 0.4139 0.00867 0.00348 -0.0558 0.8315 1.0000
1.750 0.4382 0.00862 0.00337 -0.0545 0.8114 1.0000
2.000 0.4624 0.00862 0.00331 -0.0532 0.7877 1.0000
2.250 0.4870 0.00864 0.00325 -0.0520 0.7626 1.0000
2.500 0.5116 0.00872 0.00322 -0.0509 0.7343 1.0000
2.750 0.5361 0.00884 0.00324 -0.0498 0.7024 1.0000
3.000 0.5604 0.00901 0.00328 -0.0487 0.6672 1.0000
3.250 0.5846 0.00924 0.00336 -0.0477 0.6295 1.0000
3.500 0.6084 0.00953 0.00348 -0.0466 0.5889 1.0000
3.750 0.6321 0.00985 0.00363 -0.0456 0.5459 1.0000
4.000 0.6555 0.01022 0.00382 -0.0446 0.5016 1.0000
4.250 0.6787 0.01065 0.00404 -0.0437 0.4565 1.0000
4.500 0.7017 0.01111 0.00432 -0.0428 0.4117 1.0000
4.750 0.7247 0.01160 0.00463 -0.0419 0.3684 1.0000
5.000 0.7478 0.01211 0.00497 -0.0411 0.3271 1.0000
5.250 0.7708 0.01266 0.00535 -0.0404 0.2897 1.0000
5.500 0.7939 0.01322 0.00578 -0.0397 0.2558 1.0000
5.750 0.8169 0.01381 0.00625 -0.0389 0.2264 1.0000
6.000 0.8399 0.01442 0.00675 -0.0382 0.2006 1.0000
6.250 0.8625 0.01509 0.00729 -0.0375 0.1788 1.0000
6.500 0.8857 0.01571 0.00789 -0.0368 0.1593 1.0000
6.750 0.9086 0.01634 0.00850 -0.0360 0.1418 1.0000
7.000 0.9311 0.01701 0.00913 -0.0353 0.1262 1.0000
7.250 0.9535 0.01768 0.00977 -0.0346 0.1117 1.0000
7.500 0.9757 0.01838 0.01049 -0.0338 0.0986 1.0000
7.750 0.9974 0.01915 0.01127 -0.0329 0.0868 1.0000
8.000 1.0182 0.02003 0.01217 -0.0320 0.0758 1.0000
8.250 1.0382 0.02103 0.01318 -0.0309 0.0658 1.0000
8.500 1.0564 0.02235 0.01445 -0.0297 0.0574 1.0000
8.750 1.0772 0.02327 0.01553 -0.0286 0.0510 1.0000
9.000 1.0944 0.02498 0.01721 -0.0273 0.0462 1.0000
9.250 1.1144 0.02600 0.01842 -0.0262 0.0422 1.0000
9.500 1.1331 0.02730 0.01977 -0.0251 0.0395 1.0000
9.750 1.1500 0.03013 0.02267 -0.0240 0.0371 1.0000
10.000 1.1677 0.03164 0.02448 -0.0226 0.0357 1.0000
10.250 1.1836 0.03327 0.02637 -0.0212 0.0339 1.0000
10.500 1.1980 0.03484 0.02811 -0.0198 0.0322 1.0000
10.750 1.2110 0.03668 0.03010 -0.0183 0.0310 1.0000
11.000 1.2220 0.03902 0.03259 -0.0169 0.0300 1.0000
11.250 1.2268 0.04258 0.03641 -0.0151 0.0293 1.0000
11.500 1.2218 0.04699 0.04119 -0.0127 0.0290 1.0000
11.750 1.2106 0.04996 0.04447 -0.0094 0.0287 1.0000
12.000 1.1980 0.05281 0.04760 -0.0066 0.0286 1.0000
12.250 1.1833 0.05575 0.05080 -0.0047 0.0284 1.0000
12.500 1.1653 0.05977 0.05507 -0.0039 0.0284 1.0000
12.750 1.1461 0.06445 0.05998 -0.0044 0.0284 1.0000
13.000 1.1245 0.06996 0.06570 -0.0063 0.0285 1.0000
13.250 1.1014 0.07651 0.07244 -0.0095 0.0286 1.0000
13.500 1.0761 0.08443 0.08053 -0.0141 0.0288 1.0000
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Polar data table (+)
Polar graphs
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