Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 200,000 Max Cl/Cd: 81.41 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-apex16-il-200000.txt Download as CSV file: xf-apex16-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Apex 16 (normalized using XFOIL date021206)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4588 0.09649 0.09326 -0.0391 1.0000 0.0378
-8.750 -0.4763 0.09304 0.08987 -0.0398 1.0000 0.0380
-8.500 -0.4960 0.08978 0.08665 -0.0399 1.0000 0.0380
-8.250 -0.5048 0.08468 0.08148 -0.0470 0.9952 0.0381
-8.000 -0.5111 0.08065 0.07717 -0.0540 0.9864 0.0388
-7.750 -0.5081 0.07768 0.07389 -0.0574 0.9786 0.0392
-7.500 -0.4963 0.07449 0.07041 -0.0599 0.9733 0.0393
-7.250 -0.4868 0.06518 0.06119 -0.0632 0.9713 0.0405
-7.000 -0.4795 0.06166 0.05766 -0.0628 0.9649 0.0414
-6.750 -0.4614 0.05810 0.05402 -0.0647 0.9607 0.0428
-6.500 -0.4375 0.05476 0.05048 -0.0675 0.9578 0.0454
-6.250 -0.4212 0.05654 0.05164 -0.0652 0.9486 0.0508
-6.000 -0.4050 0.05024 0.04510 -0.0671 0.9453 0.0522
-5.750 -0.3796 0.04596 0.04085 -0.0696 0.9435 0.0541
-5.500 -0.3710 0.04391 0.03871 -0.0676 0.9360 0.0559
-5.250 -0.3446 0.04182 0.03640 -0.0685 0.9324 0.0602
-5.000 -0.3132 0.03976 0.03381 -0.0698 0.9298 0.0667
-4.750 -0.3006 0.03737 0.03143 -0.0684 0.9234 0.0690
-4.500 -0.2698 0.03886 0.03245 -0.0681 0.9187 0.0789
-4.250 -0.2442 0.03354 0.02713 -0.0701 0.9167 0.0836
-4.000 -0.2102 0.03196 0.02526 -0.0719 0.9149 0.0971
-3.750 -0.2002 0.03120 0.02433 -0.0692 0.9066 0.1112
-3.500 -0.1715 0.02880 0.02188 -0.0705 0.9038 0.1280
-2.750 -0.0637 0.02461 0.01667 -0.0687 0.8939 0.0515
-2.500 -0.0320 0.02293 0.01499 -0.0692 0.8908 0.0498
-2.250 0.0045 0.02219 0.01417 -0.0707 0.8884 0.0512
-2.000 0.0416 0.02093 0.01290 -0.0724 0.8869 0.0513
-1.750 0.0558 0.02026 0.01224 -0.0699 0.8792 0.0517
-1.500 0.0854 0.01925 0.01125 -0.0703 0.8756 0.0536
-1.250 0.1215 0.01847 0.01046 -0.0721 0.8735 0.0577
-1.000 0.1608 0.01787 0.00975 -0.0744 0.8720 0.0659
-0.750 0.1736 0.01776 0.00958 -0.0716 0.8626 0.0749
-0.500 0.1967 0.01564 0.00917 -0.0711 0.8599 0.5764
-0.250 0.2324 0.01526 0.00906 -0.0721 0.8582 0.6666
0.000 0.2453 0.01539 0.00933 -0.0688 0.8495 0.7111
0.250 0.2776 0.01517 0.00926 -0.0689 0.8465 0.7565
0.500 0.3186 0.01485 0.00893 -0.0712 0.8446 0.7747
0.750 0.3604 0.01448 0.00857 -0.0738 0.8430 0.7907
1.000 0.3753 0.01455 0.00868 -0.0711 0.8335 0.8070
1.250 0.4140 0.01419 0.00835 -0.0729 0.8307 0.8236
1.500 0.4552 0.01379 0.00797 -0.0752 0.8285 0.8405
1.750 0.4710 0.01379 0.00803 -0.0726 0.8190 0.8598
2.000 0.5096 0.01339 0.00767 -0.0744 0.8156 0.8785
2.250 0.5390 0.01321 0.00756 -0.0745 0.8090 0.8987
2.500 0.5777 0.01296 0.00737 -0.0765 0.8031 0.9192
2.750 0.6302 0.01263 0.00708 -0.0813 0.7995 0.9366
3.000 0.6741 0.01261 0.00713 -0.0848 0.7906 0.9567
3.250 0.7281 0.01234 0.00690 -0.0901 0.7850 0.9702
3.500 0.7744 0.01228 0.00690 -0.0942 0.7748 0.9871
3.750 0.8144 0.01212 0.00676 -0.0969 0.7642 1.0000
4.000 0.8324 0.01194 0.00653 -0.0949 0.7503 1.0000
4.250 0.8520 0.01181 0.00639 -0.0931 0.7352 1.0000
4.500 0.8744 0.01178 0.00635 -0.0920 0.7216 1.0000
4.750 0.8973 0.01178 0.00636 -0.0909 0.7082 1.0000
5.000 0.9188 0.01182 0.00641 -0.0895 0.6934 1.0000
5.250 0.9388 0.01188 0.00650 -0.0879 0.6764 1.0000
5.500 0.9589 0.01192 0.00652 -0.0861 0.6550 1.0000
5.750 0.9763 0.01201 0.00655 -0.0838 0.6278 1.0000
6.000 0.9924 0.01219 0.00662 -0.0812 0.5965 1.0000
6.250 1.0062 0.01247 0.00680 -0.0783 0.5614 1.0000
6.500 1.0163 0.01284 0.00702 -0.0747 0.5198 1.0000
6.750 1.0229 0.01332 0.00729 -0.0706 0.4719 1.0000
7.000 1.0257 0.01391 0.00764 -0.0658 0.4244 1.0000
7.250 1.0270 0.01463 0.00812 -0.0609 0.3756 1.0000
7.500 1.0281 0.01549 0.00872 -0.0562 0.3250 1.0000
7.750 1.0301 0.01645 0.00943 -0.0520 0.2724 1.0000
8.000 1.0310 0.01760 0.01026 -0.0478 0.2156 1.0000
8.500 1.0243 0.02092 0.01265 -0.0390 0.0850 1.0000
8.750 1.0258 0.02248 0.01399 -0.0354 0.0618 1.0000
9.000 1.0341 0.02363 0.01518 -0.0329 0.0544 1.0000
9.250 1.0380 0.02509 0.01664 -0.0298 0.0499 1.0000
9.500 1.0480 0.02622 0.01789 -0.0277 0.0463 1.0000
9.750 1.0565 0.02749 0.01919 -0.0255 0.0431 1.0000
10.000 1.0611 0.02929 0.02098 -0.0230 0.0409 1.0000
10.250 1.0733 0.03066 0.02245 -0.0213 0.0390 1.0000
10.500 1.0869 0.03189 0.02378 -0.0198 0.0367 1.0000
10.750 1.1009 0.03327 0.02523 -0.0184 0.0346 1.0000
11.000 1.1192 0.03490 0.02685 -0.0176 0.0329 1.0000
11.250 1.1518 0.03746 0.02952 -0.0182 0.0309 1.0000
11.500 1.1656 0.03894 0.03123 -0.0167 0.0296 1.0000
11.750 1.1814 0.04082 0.03332 -0.0156 0.0284 1.0000
12.000 1.1975 0.04313 0.03588 -0.0146 0.0276 1.0000
12.250 1.2096 0.04574 0.03877 -0.0132 0.0272 1.0000
12.500 1.2157 0.04861 0.04193 -0.0114 0.0269 1.0000
12.750 1.2154 0.05175 0.04538 -0.0092 0.0268 1.0000
13.000 1.2116 0.05477 0.04865 -0.0070 0.0265 1.0000
13.250 1.2014 0.05827 0.05245 -0.0046 0.0266 1.0000
13.500 1.1830 0.06263 0.05718 -0.0023 0.0271 1.0000
13.750 1.1805 0.06511 0.05974 -0.0013 0.0261 1.0000
14.000 1.1569 0.06990 0.06486 0.0000 0.0265 1.0000
14.250 1.1451 0.07367 0.06879 0.0004 0.0260 1.0000
14.500 1.0987 0.08233 0.07792 -0.0002 0.0281 1.0000
14.750 1.0735 0.08860 0.08441 -0.0019 0.0285 1.0000
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Polar data table (+)
Polar graphs
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