Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 50,000 Max Cl/Cd: 32.57 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-apex16-il-50000-n5.txt Download as CSV file: xf-apex16-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4101 0.11564 0.10869 -0.0429 1.0000 0.1206
-9.750 -0.4312 0.11340 0.10660 -0.0442 1.0000 0.1251
-9.500 -0.4642 0.11121 0.10460 -0.0462 1.0000 0.1262
-9.250 -0.4320 0.10699 0.10032 -0.0417 1.0000 0.1310
-9.000 -0.4382 0.10434 0.09775 -0.0407 1.0000 0.1351
-8.750 -0.4710 0.10202 0.09561 -0.0415 1.0000 0.1398
-8.250 -0.4766 0.09618 0.08991 -0.0375 1.0000 0.1479
-8.000 -0.5006 0.09366 0.08752 -0.0365 1.0000 0.1511
-6.000 -0.5683 0.06555 0.05832 -0.0353 0.9962 0.0973
-5.750 -0.5415 0.06065 0.05299 -0.0368 0.9919 0.0721
-5.500 -0.5170 0.05729 0.04895 -0.0386 0.9866 0.0671
-5.250 -0.4935 0.05412 0.04550 -0.0395 0.9819 0.0638
-5.000 -0.4677 0.05101 0.04205 -0.0408 0.9775 0.0610
-4.750 -0.4424 0.04836 0.03890 -0.0413 0.9726 0.0582
-4.250 -0.3847 0.04439 0.03378 -0.0422 0.9631 0.0541
-4.000 -0.3565 0.04230 0.03141 -0.0428 0.9587 0.0536
-3.750 -0.3260 0.04049 0.02929 -0.0436 0.9548 0.0534
-3.500 -0.2990 0.03907 0.02756 -0.0436 0.9496 0.0538
-3.250 -0.2683 0.03755 0.02586 -0.0445 0.9457 0.0561
-3.000 -0.2405 0.03637 0.02462 -0.0448 0.9410 0.0587
-2.750 -0.2117 0.03532 0.02347 -0.0447 0.9361 0.0596
-2.500 -0.1793 0.03442 0.02249 -0.0451 0.9324 0.0603
-2.250 -0.1548 0.03369 0.02166 -0.0442 0.9269 0.0615
-2.000 -0.1280 0.03305 0.02090 -0.0439 0.9216 0.0631
-1.750 -0.0968 0.03246 0.02012 -0.0447 0.9176 0.0652
-1.500 -0.0763 0.03189 0.01948 -0.0440 0.9104 0.0689
-1.250 -0.0457 0.03144 0.01886 -0.0452 0.9054 0.0773
-1.000 -0.0208 0.03100 0.01827 -0.0453 0.8991 0.0847
-0.750 0.0080 0.03056 0.01767 -0.0461 0.8931 0.0953
-0.500 0.0437 0.02962 0.01688 -0.0483 0.8892 0.1564
-0.250 0.0487 0.02822 0.01761 -0.0438 0.8815 0.6469
0.000 0.0551 0.02825 0.01828 -0.0367 0.8756 0.7929
0.250 0.0649 0.02826 0.01843 -0.0317 0.8677 0.8669
0.500 0.1033 0.02833 0.01832 -0.0342 0.8624 0.8920
0.750 0.1482 0.02849 0.01832 -0.0382 0.8570 0.9206
1.000 0.1982 0.02869 0.01838 -0.0436 0.8505 0.9584
1.250 0.2439 0.02883 0.01834 -0.0481 0.8458 1.0000
1.750 0.2937 0.02924 0.01843 -0.0490 0.8297 1.0000
2.000 0.3158 0.02953 0.01862 -0.0488 0.8204 1.0000
2.250 0.3427 0.02981 0.01879 -0.0493 0.8125 1.0000
2.500 0.3720 0.03004 0.01896 -0.0501 0.8049 1.0000
2.750 0.3948 0.03039 0.01925 -0.0499 0.7956 1.0000
3.000 0.4292 0.03052 0.01936 -0.0513 0.7891 1.0000
3.250 0.4494 0.03092 0.01974 -0.0505 0.7785 1.0000
3.500 0.4877 0.03090 0.01974 -0.0524 0.7731 1.0000
3.750 0.5061 0.03133 0.02019 -0.0513 0.7615 1.0000
4.000 0.5289 0.03167 0.02058 -0.0508 0.7511 1.0000
4.250 0.5654 0.03156 0.02054 -0.0521 0.7445 1.0000
4.500 0.5850 0.03196 0.02100 -0.0511 0.7326 1.0000
4.750 0.6084 0.03223 0.02138 -0.0505 0.7216 1.0000
5.000 0.6466 0.03187 0.02115 -0.0517 0.7149 1.0000
5.500 0.6901 0.03233 0.02183 -0.0498 0.6897 1.0000
5.750 0.7156 0.03233 0.02202 -0.0492 0.6774 1.0000
6.000 0.7441 0.03213 0.02198 -0.0487 0.6651 1.0000
6.250 0.7737 0.03176 0.02179 -0.0483 0.6517 1.0000
6.500 0.8016 0.03135 0.02156 -0.0474 0.6358 1.0000
6.750 0.8309 0.03075 0.02120 -0.0465 0.6180 1.0000
7.000 0.8652 0.02988 0.02052 -0.0460 0.5990 1.0000
7.250 0.8854 0.02981 0.02062 -0.0442 0.5760 1.0000
7.500 0.9135 0.02939 0.02036 -0.0431 0.5519 1.0000
7.750 0.9348 0.02936 0.02053 -0.0413 0.5242 1.0000
8.000 0.9524 0.02953 0.02082 -0.0392 0.4922 1.0000
8.250 0.9693 0.02976 0.02108 -0.0369 0.4549 1.0000
8.500 0.9792 0.03024 0.02135 -0.0336 0.4031 1.0000
8.750 0.9788 0.03139 0.02209 -0.0296 0.3400 1.0000
9.000 0.9755 0.03303 0.02330 -0.0260 0.2796 1.0000
9.250 0.9737 0.03490 0.02483 -0.0231 0.2305 1.0000
9.500 0.9733 0.03690 0.02660 -0.0206 0.1894 1.0000
9.750 0.9725 0.03913 0.02867 -0.0183 0.1521 1.0000
10.000 0.9716 0.04155 0.03088 -0.0163 0.1221 1.0000
10.250 0.9719 0.04402 0.03320 -0.0145 0.1005 1.0000
10.500 0.9749 0.04637 0.03551 -0.0128 0.0878 1.0000
10.750 0.9802 0.04859 0.03774 -0.0113 0.0794 1.0000
11.000 0.9903 0.05058 0.03986 -0.0100 0.0724 1.0000
11.250 0.9982 0.05267 0.04195 -0.0089 0.0666 1.0000
11.500 1.0123 0.05452 0.04402 -0.0078 0.0606 1.0000
11.750 1.0273 0.05638 0.04598 -0.0069 0.0566 1.0000
12.000 1.0520 0.05821 0.04798 -0.0060 0.0535 1.0000
12.250 1.0735 0.06061 0.05080 -0.0052 0.0508 1.0000
12.500 1.0818 0.06336 0.05383 -0.0044 0.0480 1.0000
12.750 1.0865 0.06613 0.05677 -0.0036 0.0458 1.0000
13.000 1.0949 0.06912 0.05975 -0.0031 0.0436 1.0000
13.250 1.0910 0.07298 0.06403 -0.0024 0.0430 1.0000
13.500 1.0831 0.07725 0.06866 -0.0019 0.0426 1.0000
13.750 1.0710 0.08191 0.07365 -0.0020 0.0423 1.0000
14.000 1.0555 0.08704 0.07909 -0.0027 0.0421 1.0000
14.250 1.0381 0.09262 0.08492 -0.0040 0.0421 1.0000
14.500 1.0179 0.09888 0.09142 -0.0063 0.0422 1.0000
14.750 0.9964 0.10585 0.09860 -0.0095 0.0423 1.0000
15.000 0.9748 0.11349 0.10640 -0.0136 0.0426 1.0000
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Polar data table (+)
Polar graphs
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