AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 500,000 Max Cl/Cd: 102.15 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83150q-il-500000-n5.txt Download as CSV file: xf-ah83150q-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-150 Q
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1794 0.09174 0.08836 -0.0502 0.6774 0.0101
-10.250 -0.1754 0.08837 0.08499 -0.0515 0.6759 0.0103
-10.000 -0.1728 0.08466 0.08127 -0.0529 0.6745 0.0104
-9.750 -0.1710 0.08085 0.07746 -0.0544 0.6732 0.0108
-9.500 -0.1724 0.07624 0.07285 -0.0563 0.6721 0.0108
-9.250 -0.2445 0.07566 0.07211 -0.0677 0.6771 0.0098
-8.250 -0.2901 0.05507 0.05131 -0.0779 0.6704 0.0098
-7.750 -0.2946 0.05086 0.04701 -0.0767 0.6671 0.0094
-7.500 -0.2925 0.04808 0.04413 -0.0762 0.6652 0.0090
-7.250 -0.2901 0.04398 0.03984 -0.0754 0.6634 0.0089
-7.000 -0.2838 0.04020 0.03583 -0.0744 0.6615 0.0085
-6.750 -0.2748 0.03630 0.03166 -0.0731 0.6598 0.0084
-6.500 -0.2609 0.03320 0.02829 -0.0720 0.6582 0.0088
-6.250 -0.2454 0.02995 0.02471 -0.0707 0.6567 0.0091
-6.000 -0.2284 0.02708 0.02152 -0.0696 0.6552 0.0087
-5.750 -0.2123 0.02154 0.01510 -0.0670 0.6538 0.0074
-5.250 -0.1621 0.01919 0.01234 -0.0663 0.6502 0.0072
-5.000 -0.1367 0.01796 0.01094 -0.0660 0.6484 0.0072
-4.750 -0.1106 0.01691 0.00973 -0.0658 0.6467 0.0072
-4.500 -0.0842 0.01602 0.00871 -0.0656 0.6448 0.0072
-4.250 -0.0578 0.01527 0.00785 -0.0654 0.6430 0.0072
-4.000 -0.0316 0.01454 0.00704 -0.0651 0.6413 0.0072
-3.750 -0.0059 0.01381 0.00625 -0.0649 0.6398 0.0074
-3.500 0.0201 0.01326 0.00565 -0.0647 0.6382 0.0075
-3.250 0.0466 0.01280 0.00519 -0.0646 0.6364 0.0077
-3.000 0.0735 0.01242 0.00480 -0.0646 0.6344 0.0080
-2.750 0.1006 0.01207 0.00444 -0.0646 0.6325 0.0085
-2.500 0.1280 0.01178 0.00412 -0.0647 0.6306 0.0090
-2.250 0.1557 0.01154 0.00384 -0.0647 0.6288 0.0097
-2.000 0.1833 0.01128 0.00355 -0.0648 0.6269 0.0104
-1.750 0.2112 0.01111 0.00334 -0.0650 0.6251 0.0119
-1.500 0.2392 0.01096 0.00315 -0.0652 0.6234 0.0144
-1.250 0.2674 0.01078 0.00300 -0.0653 0.6215 0.0202
-1.000 0.2933 0.01015 0.00285 -0.0655 0.6193 0.1554
-0.750 0.3094 0.00807 0.00276 -0.0647 0.6169 0.7128
-0.500 0.3346 0.00848 0.00332 -0.0635 0.6145 0.8011
-0.250 0.3597 0.00890 0.00373 -0.0624 0.6121 0.8211
0.000 0.3871 0.00911 0.00388 -0.0621 0.6099 0.8316
0.250 0.4146 0.00919 0.00392 -0.0619 0.6077 0.8346
0.500 0.4432 0.00922 0.00393 -0.0622 0.6051 0.8365
0.750 0.4724 0.00922 0.00390 -0.0626 0.6022 0.8376
1.000 0.5016 0.00922 0.00387 -0.0630 0.5994 0.8388
1.250 0.5308 0.00923 0.00383 -0.0635 0.5967 0.8401
1.500 0.5600 0.00925 0.00379 -0.0639 0.5941 0.8411
1.750 0.5892 0.00926 0.00379 -0.0644 0.5911 0.8421
2.000 0.6185 0.00928 0.00381 -0.0649 0.5876 0.8434
2.250 0.6477 0.00930 0.00380 -0.0655 0.5839 0.8445
2.500 0.6769 0.00932 0.00379 -0.0660 0.5805 0.8454
2.750 0.7055 0.00934 0.00380 -0.0663 0.5770 0.8460
3.000 0.7341 0.00936 0.00384 -0.0667 0.5728 0.8466
3.250 0.7624 0.00938 0.00388 -0.0670 0.5686 0.8474
3.500 0.7905 0.00942 0.00389 -0.0673 0.5646 0.8482
3.750 0.8188 0.00946 0.00396 -0.0676 0.5600 0.8490
4.000 0.8470 0.00951 0.00402 -0.0679 0.5549 0.8498
4.250 0.8750 0.00956 0.00407 -0.0682 0.5500 0.8505
4.500 0.9031 0.00962 0.00416 -0.0685 0.5443 0.8512
4.750 0.9308 0.00969 0.00423 -0.0688 0.5377 0.8520
5.000 0.9583 0.00976 0.00432 -0.0690 0.5305 0.8529
5.250 0.9848 0.00987 0.00440 -0.0691 0.5194 0.8539
5.500 1.0107 0.01001 0.00451 -0.0691 0.5039 0.8550
5.750 1.0360 0.01020 0.00465 -0.0690 0.4870 0.8559
6.000 1.0612 0.01040 0.00483 -0.0689 0.4739 0.8568
6.250 1.0859 0.01063 0.00503 -0.0687 0.4601 0.8576
6.500 1.1096 0.01091 0.00527 -0.0685 0.4437 0.8584
6.750 1.1326 0.01122 0.00554 -0.0681 0.4274 0.8593
7.250 1.1745 0.01194 0.00619 -0.0666 0.3939 0.8611
7.500 1.1929 0.01237 0.00658 -0.0655 0.3761 0.8621
7.750 1.2105 0.01281 0.00699 -0.0642 0.3600 0.8631
8.000 1.2260 0.01330 0.00745 -0.0627 0.3436 0.8641
8.500 1.2413 0.01454 0.00859 -0.0570 0.3079 0.8668
8.750 1.2432 0.01549 0.00947 -0.0538 0.2866 0.8685
9.000 1.2419 0.01678 0.01065 -0.0506 0.2625 0.8702
9.250 1.2418 0.01822 0.01198 -0.0480 0.2389 0.8721
9.500 1.2447 0.01963 0.01332 -0.0459 0.2192 0.8737
9.750 1.2483 0.02106 0.01469 -0.0441 0.2006 0.8750
10.000 1.2529 0.02247 0.01606 -0.0424 0.1844 0.8762
10.250 1.2586 0.02385 0.01741 -0.0409 0.1706 0.8775
10.500 1.2645 0.02526 0.01879 -0.0395 0.1581 0.8787
10.750 1.2712 0.02665 0.02017 -0.0382 0.1479 0.8800
11.000 1.2778 0.02809 0.02160 -0.0370 0.1379 0.8812
11.250 1.2863 0.02941 0.02294 -0.0361 0.1296 0.8825
11.500 1.2930 0.03090 0.02442 -0.0350 0.1214 0.8838
11.750 1.3003 0.03238 0.02591 -0.0341 0.1132 0.8851
12.000 1.3085 0.03382 0.02737 -0.0333 0.1063 0.8865
12.250 1.3133 0.03557 0.02910 -0.0324 0.0967 0.8879
12.500 1.3232 0.03696 0.03053 -0.0318 0.0912 0.8891
12.750 1.3286 0.03876 0.03234 -0.0310 0.0824 0.8904
13.000 1.3334 0.04065 0.03420 -0.0303 0.0729 0.8917
13.250 1.3391 0.04251 0.03608 -0.0298 0.0650 0.8930
13.500 1.3447 0.04443 0.03801 -0.0293 0.0580 0.8944
13.750 1.3490 0.04654 0.04012 -0.0288 0.0518 0.8959
14.000 1.3551 0.04852 0.04214 -0.0285 0.0472 0.8974
14.250 1.3590 0.05076 0.04441 -0.0282 0.0426 0.8990
14.500 1.3653 0.05282 0.04653 -0.0280 0.0392 0.9006
14.750 1.3701 0.05510 0.04886 -0.0279 0.0368 0.9022
15.250 1.3814 0.05959 0.05348 -0.0279 0.0321 0.9062
15.500 1.3860 0.06203 0.05600 -0.0281 0.0302 0.9085
15.750 1.3904 0.06460 0.05863 -0.0284 0.0288 0.9111
16.000 1.3954 0.06712 0.06125 -0.0287 0.0273 0.9141
16.500 1.4025 0.07265 0.06694 -0.0297 0.0234 0.9233
17.000 1.4113 0.07854 0.07306 -0.0317 0.0205 0.9648
17.250 1.4116 0.08156 0.07616 -0.0320 0.0189 1.0000
17.500 1.4120 0.08492 0.07957 -0.0329 0.0170 1.0000
17.750 1.4129 0.08826 0.08300 -0.0338 0.0152 1.0000
18.000 1.4116 0.09196 0.08676 -0.0348 0.0132 1.0000
18.250 1.4085 0.09598 0.09082 -0.0360 0.0102 1.0000
18.500 1.4029 0.10044 0.09534 -0.0375 0.0076 1.0000
18.750 1.3961 0.10518 0.10015 -0.0391 0.0060 1.0000
19.000 1.3928 0.10945 0.10451 -0.0407 0.0055 1.0000
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