AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 200,000 Max Cl/Cd: 58.22 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150f-il-200000.txt Download as CSV file: xf-ah82150f-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 F
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1230 0.11872 0.11477 -0.1216 0.9230 0.0422
-12.750 -0.1263 0.11576 0.11183 -0.1249 0.9211 0.0433
-12.500 -0.1295 0.11256 0.10866 -0.1281 0.9190 0.0437
-12.250 -0.1281 0.10906 0.10515 -0.1303 0.9173 0.0439
-12.000 -0.1275 0.10531 0.10141 -0.1327 0.9157 0.0440
-11.750 -0.1194 0.09966 0.09577 -0.1319 0.9151 0.0454
-11.500 -0.1081 0.09716 0.09326 -0.1317 0.9141 0.0466
-11.250 -0.1026 0.09443 0.09052 -0.1324 0.9129 0.0475
-11.000 -0.0988 0.09157 0.08767 -0.1333 0.9115 0.0491
-10.750 -0.0979 0.08838 0.08450 -0.1347 0.9101 0.0506
-10.500 -0.0990 0.08501 0.08116 -0.1364 0.9086 0.0520
-10.250 -0.1085 0.08068 0.07688 -0.1398 0.9069 0.0549
-10.000 -0.1233 0.07542 0.07166 -0.1452 0.9046 0.0558
-9.750 -0.1447 0.07076 0.06696 -0.1488 0.9021 0.0560
-9.500 -0.1683 0.06816 0.06429 -0.1485 0.9001 0.0563
-9.250 -0.1984 0.06720 0.06327 -0.1448 0.8974 0.0565
-9.000 -0.2214 0.06660 0.06261 -0.1401 0.8949 0.0566
-8.750 -0.2433 0.06608 0.06198 -0.1351 0.8921 0.0567
-8.500 -0.2630 0.06553 0.06130 -0.1299 0.8901 0.0568
-8.250 -0.2799 0.06471 0.06033 -0.1248 0.8885 0.0569
-7.500 -0.5762 0.08384 0.08082 -0.0526 0.9605 0.0456
-7.250 -0.5674 0.08095 0.07791 -0.0530 0.9578 0.0466
-7.000 -0.5735 0.07802 0.07490 -0.0507 0.9518 0.0471
-6.750 -0.5681 0.07467 0.07145 -0.0505 0.9461 0.0485
-6.500 -0.5556 0.07105 0.06763 -0.0519 0.9431 0.0511
-6.250 -0.5629 0.06791 0.06433 -0.0481 0.9347 0.0523
-6.000 -0.5439 0.06685 0.06233 -0.0479 0.9296 0.0569
-5.750 -0.5543 0.05945 0.05493 -0.0449 0.9236 0.0585
-5.500 -0.5377 0.05653 0.05200 -0.0449 0.9192 0.0602
-5.250 -0.5150 0.04943 0.04401 -0.0428 0.9169 0.0421
-5.000 -0.4885 0.04548 0.03957 -0.0433 0.9153 0.0399
-4.750 -0.3894 0.03795 0.03084 -0.0527 0.8727 0.0395
-4.500 -0.3716 0.03670 0.02927 -0.0511 0.8738 0.0402
-4.250 -0.3683 0.03596 0.02831 -0.0470 0.8714 0.0420
-4.000 -0.3541 0.03605 0.02817 -0.0449 0.8712 0.0440
-3.750 -0.3108 0.03345 0.02548 -0.0471 0.8554 0.0507
-3.500 -0.2892 0.03290 0.02479 -0.0461 0.8512 0.0547
-3.250 -0.2397 0.03179 0.02363 -0.0498 0.8469 0.0631
-2.750 -0.2064 0.03094 0.02273 -0.0463 0.8359 0.0748
-2.500 -0.1633 0.03045 0.02220 -0.0489 0.8329 0.0854
-2.250 -0.1583 0.03020 0.02201 -0.0454 0.8253 0.0935
-2.000 -0.1291 0.02976 0.02163 -0.0459 0.8213 0.1167
-1.750 -0.1086 0.02719 0.02121 -0.0454 0.8191 0.5583
-1.500 -0.1274 0.02742 0.02245 -0.0346 0.8102 0.8255
-1.250 -0.1134 0.02807 0.02303 -0.0297 0.8063 0.8802
-1.000 -0.0937 0.02854 0.02340 -0.0259 0.8031 0.9092
-0.500 0.2194 0.03163 0.02598 -0.0748 0.8070 0.9846
-0.250 0.2998 0.03150 0.02572 -0.0857 0.8063 0.9929
0.000 0.3776 0.03120 0.02532 -0.0962 0.8057 0.9997
0.250 0.4207 0.03097 0.02502 -0.0994 0.8044 1.0000
0.500 0.4016 0.03144 0.02549 -0.0915 0.7931 1.0000
0.750 0.4405 0.03119 0.02518 -0.0937 0.7914 1.0000
1.000 0.4838 0.03088 0.02483 -0.0967 0.7902 1.0000
1.250 0.4663 0.03129 0.02524 -0.0891 0.7785 1.0000
1.500 0.4673 0.03158 0.02552 -0.0848 0.7699 1.0000
1.750 0.4937 0.03140 0.02532 -0.0847 0.7660 1.0000
2.000 0.5303 0.03105 0.02496 -0.0863 0.7641 1.0000
2.250 0.5709 0.03064 0.02454 -0.0885 0.7629 1.0000
2.500 0.5581 0.03104 0.02495 -0.0818 0.7514 1.0000
2.750 0.5957 0.03060 0.02452 -0.0835 0.7499 1.0000
3.000 0.6359 0.03010 0.02405 -0.0856 0.7488 1.0000
3.250 0.6238 0.03045 0.02442 -0.0790 0.7372 1.0000
3.500 0.6254 0.03062 0.02460 -0.0747 0.7283 1.0000
3.750 0.6541 0.03021 0.02422 -0.0748 0.7249 1.0000
4.000 0.6898 0.02960 0.02366 -0.0759 0.7232 1.0000
4.250 0.7284 0.02893 0.02305 -0.0775 0.7220 1.0000
4.750 0.7268 0.02911 0.02329 -0.0680 0.7023 1.0000
5.000 0.7530 0.02856 0.02281 -0.0675 0.6984 1.0000
5.250 0.7875 0.02777 0.02210 -0.0682 0.6965 1.0000
5.500 0.8251 0.02683 0.02127 -0.0694 0.6952 1.0000
5.750 0.8205 0.02691 0.02139 -0.0640 0.6838 1.0000
6.000 0.8562 0.02591 0.02049 -0.0647 0.6824 1.0000
6.250 0.8914 0.02484 0.01955 -0.0653 0.6809 1.0000
6.750 0.9275 0.02321 0.01812 -0.0609 0.6679 1.0000
7.000 0.9391 0.02199 0.01695 -0.0570 0.6547 1.0000
7.250 0.9396 0.02135 0.01633 -0.0517 0.6352 1.0000
7.500 0.9840 0.01930 0.01429 -0.0526 0.6110 1.0000
7.750 1.0282 0.01766 0.01227 -0.0533 0.5392 1.0000
8.000 1.0123 0.01820 0.01245 -0.0457 0.4863 1.0000
8.250 0.9915 0.01908 0.01302 -0.0380 0.4397 1.0000
8.500 0.9729 0.02051 0.01408 -0.0315 0.3800 1.0000
8.750 0.9544 0.02249 0.01557 -0.0259 0.3028 1.0000
9.000 0.9282 0.02537 0.01764 -0.0200 0.1809 1.0000
9.250 0.9063 0.02849 0.01991 -0.0151 0.0593 1.0000
9.500 0.9067 0.03038 0.02163 -0.0126 0.0363 1.0000
9.750 0.9165 0.03168 0.02306 -0.0111 0.0324 1.0000
10.000 0.9228 0.03327 0.02474 -0.0094 0.0295 1.0000
10.250 0.9231 0.03536 0.02695 -0.0073 0.0272 1.0000
10.500 0.9320 0.03683 0.02853 -0.0060 0.0259 1.0000
10.750 0.9380 0.03859 0.03039 -0.0046 0.0248 1.0000
11.000 0.9444 0.04038 0.03225 -0.0032 0.0239 1.0000
11.250 0.9523 0.04209 0.03406 -0.0018 0.0232 1.0000
11.500 0.9633 0.04365 0.03567 -0.0006 0.0225 1.0000
11.750 0.9796 0.04494 0.03701 0.0004 0.0223 1.0000
12.000 1.0047 0.04593 0.03805 0.0010 0.0221 1.0000
12.250 1.0323 0.04705 0.03924 0.0013 0.0212 1.0000
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Polar data table (+)
Polar graphs
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