SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 100,000 Max Cl/Cd: 46.65 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8000-il-100000-n5.txt Download as CSV file: xf-sd8000-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5368 0.09226 0.08711 -0.0217 1.0000 0.0265
-9.750 -0.5434 0.08637 0.08128 -0.0247 1.0000 0.0265
-9.500 -0.5516 0.08026 0.07525 -0.0282 1.0000 0.0264
-9.250 -0.5642 0.07304 0.06813 -0.0327 1.0000 0.0261
-9.000 -0.5857 0.06307 0.05820 -0.0411 1.0000 0.0256
-8.750 -0.6078 0.05598 0.05099 -0.0461 1.0000 0.0251
-8.500 -0.6249 0.04936 0.04405 -0.0486 1.0000 0.0251
-8.250 -0.6333 0.04365 0.03789 -0.0492 1.0000 0.0253
-8.000 -0.6339 0.03878 0.03248 -0.0486 1.0000 0.0258
-7.750 -0.6284 0.03463 0.02772 -0.0475 1.0000 0.0266
-7.500 -0.6172 0.03162 0.02427 -0.0462 1.0000 0.0278
-7.250 -0.6005 0.03055 0.02317 -0.0452 1.0000 0.0298
-7.000 -0.5840 0.02887 0.02117 -0.0439 1.0000 0.0325
-6.750 -0.5667 0.02670 0.01849 -0.0425 1.0000 0.0351
-6.500 -0.5489 0.02533 0.01709 -0.0414 1.0000 0.0379
-6.250 -0.5294 0.02432 0.01589 -0.0402 1.0000 0.0422
-6.000 -0.5096 0.02287 0.01416 -0.0389 1.0000 0.0461
-5.750 -0.4899 0.02206 0.01335 -0.0379 1.0000 0.0509
-5.500 -0.4689 0.02103 0.01205 -0.0366 1.0000 0.0559
-5.250 -0.4487 0.02016 0.01120 -0.0356 1.0000 0.0616
-5.000 -0.4273 0.01944 0.01029 -0.0345 1.0000 0.0686
-4.750 -0.4065 0.01868 0.00959 -0.0335 1.0000 0.0757
-4.500 -0.3850 0.01805 0.00887 -0.0325 1.0000 0.0846
-4.250 -0.3633 0.01754 0.00829 -0.0316 1.0000 0.0952
-4.000 -0.3416 0.01701 0.00778 -0.0307 1.0000 0.1070
-3.750 -0.3196 0.01654 0.00733 -0.0299 1.0000 0.1210
-3.500 -0.2916 0.01609 0.00692 -0.0304 0.9976 0.1400
-3.250 -0.2566 0.01565 0.00655 -0.0322 0.9922 0.1685
-3.000 -0.2217 0.01521 0.00626 -0.0340 0.9865 0.2067
-2.750 -0.1867 0.01478 0.00605 -0.0358 0.9808 0.2624
-2.500 -0.1525 0.01435 0.00588 -0.0375 0.9744 0.3355
-2.250 -0.1178 0.01393 0.00580 -0.0391 0.9684 0.4252
-2.000 -0.0853 0.01356 0.00578 -0.0400 0.9612 0.5200
-1.750 -0.0510 0.01328 0.00579 -0.0410 0.9550 0.6130
-1.500 -0.0202 0.01306 0.00581 -0.0411 0.9469 0.6942
-1.250 0.0133 0.01290 0.00584 -0.0414 0.9404 0.7710
-1.000 0.0449 0.01276 0.00581 -0.0413 0.9319 0.8410
-0.750 0.0889 0.01264 0.00574 -0.0437 0.9261 0.9085
-0.500 0.1419 0.01250 0.00556 -0.0484 0.9189 0.9672
-0.250 0.1930 0.01237 0.00534 -0.0529 0.9117 1.0000
0.000 0.2244 0.01231 0.00520 -0.0535 0.8992 1.0000
0.250 0.2535 0.01226 0.00508 -0.0536 0.8852 1.0000
0.500 0.2821 0.01221 0.00496 -0.0534 0.8706 1.0000
0.750 0.3103 0.01215 0.00486 -0.0531 0.8551 1.0000
1.000 0.3375 0.01211 0.00477 -0.0526 0.8379 1.0000
1.250 0.3634 0.01209 0.00470 -0.0518 0.8181 1.0000
1.500 0.3904 0.01205 0.00462 -0.0511 0.7979 1.0000
1.750 0.4167 0.01205 0.00458 -0.0503 0.7756 1.0000
2.000 0.4434 0.01206 0.00452 -0.0495 0.7517 1.0000
2.250 0.4692 0.01211 0.00450 -0.0486 0.7242 1.0000
2.500 0.4950 0.01220 0.00449 -0.0477 0.6941 1.0000
2.750 0.5203 0.01234 0.00454 -0.0467 0.6613 1.0000
3.000 0.5452 0.01253 0.00461 -0.0458 0.6255 1.0000
3.250 0.5698 0.01277 0.00471 -0.0448 0.5881 1.0000
3.500 0.5939 0.01307 0.00487 -0.0438 0.5481 1.0000
3.750 0.6177 0.01342 0.00506 -0.0428 0.5071 1.0000
4.000 0.6412 0.01382 0.00529 -0.0418 0.4658 1.0000
4.250 0.6644 0.01426 0.00557 -0.0409 0.4253 1.0000
4.500 0.6876 0.01474 0.00591 -0.0400 0.3858 1.0000
4.750 0.7108 0.01524 0.00628 -0.0392 0.3493 1.0000
5.000 0.7338 0.01577 0.00669 -0.0384 0.3147 1.0000
5.250 0.7569 0.01633 0.00715 -0.0376 0.2833 1.0000
5.500 0.7798 0.01691 0.00764 -0.0369 0.2540 1.0000
5.750 0.8027 0.01751 0.00817 -0.0362 0.2281 1.0000
6.000 0.8253 0.01815 0.00874 -0.0354 0.2046 1.0000
6.250 0.8480 0.01879 0.00935 -0.0347 0.1835 1.0000
6.500 0.8701 0.01949 0.01003 -0.0339 0.1653 1.0000
6.750 0.8923 0.02020 0.01073 -0.0331 0.1491 1.0000
7.000 0.9143 0.02094 0.01148 -0.0324 0.1342 1.0000
7.250 0.9358 0.02174 0.01229 -0.0315 0.1211 1.0000
7.500 0.9567 0.02257 0.01316 -0.0307 0.1086 1.0000
7.750 0.9776 0.02342 0.01407 -0.0298 0.0969 1.0000
8.000 0.9983 0.02429 0.01502 -0.0289 0.0856 1.0000
8.250 1.0182 0.02525 0.01606 -0.0279 0.0757 1.0000
8.500 1.0369 0.02630 0.01717 -0.0269 0.0671 1.0000
8.750 1.0549 0.02739 0.01832 -0.0258 0.0595 1.0000
9.000 1.0727 0.02864 0.01974 -0.0246 0.0532 1.0000
9.250 1.0885 0.02994 0.02108 -0.0233 0.0485 1.0000
9.500 1.1045 0.03139 0.02272 -0.0220 0.0439 1.0000
9.750 1.1194 0.03278 0.02423 -0.0206 0.0404 1.0000
10.000 1.1313 0.03449 0.02599 -0.0191 0.0381 1.0000
10.250 1.1444 0.03645 0.02822 -0.0176 0.0363 1.0000
10.500 1.1560 0.03846 0.03051 -0.0160 0.0344 1.0000
10.750 1.1652 0.04036 0.03262 -0.0144 0.0327 1.0000
11.000 1.1708 0.04208 0.03447 -0.0124 0.0312 1.0000
11.250 1.1743 0.04396 0.03643 -0.0105 0.0300 1.0000
11.500 1.1748 0.04651 0.03914 -0.0087 0.0291 1.0000
11.750 1.1724 0.04934 0.04229 -0.0070 0.0286 1.0000
12.000 1.1660 0.05257 0.04585 -0.0056 0.0280 1.0000
12.250 1.1563 0.05624 0.04981 -0.0049 0.0277 1.0000
12.500 1.1435 0.06042 0.05427 -0.0050 0.0274 1.0000
12.750 1.1276 0.06533 0.05945 -0.0062 0.0272 1.0000
13.000 1.1086 0.07117 0.06554 -0.0087 0.0272 1.0000
13.250 1.0866 0.07818 0.07279 -0.0128 0.0272 1.0000
13.500 1.0611 0.08674 0.08157 -0.0185 0.0274 1.0000
13.750 1.0312 0.09734 0.09236 -0.0259 0.0278 1.0000
14.000 0.9965 0.11037 0.10552 -0.0348 0.0284 1.0000
14.250 0.9576 0.12586 0.12106 -0.0444 0.0289 1.0000
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Polar data table (+)
Polar graphs
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