AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 50,000 Max Cl/Cd: 20.22 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150a-il-50000-n5.txt Download as CSV file: xf-ah82150a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 A
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3575 0.12577 0.11929 -0.0560 1.0000 0.0669
-11.250 -0.3607 0.12414 0.11773 -0.0527 1.0000 0.0650
-11.000 -0.3714 0.12245 0.11612 -0.0502 1.0000 0.0635
-10.750 -0.3726 0.11863 0.11234 -0.0516 0.9970 0.0615
-10.250 -0.3859 0.10302 0.09678 -0.0669 0.9834 0.0543
-10.000 -0.3812 0.09808 0.09183 -0.0701 0.9772 0.0539
-9.750 -0.3775 0.09241 0.08614 -0.0750 0.9719 0.0534
-9.500 -0.3825 0.08693 0.08065 -0.0793 0.9646 0.0530
-9.250 -0.3901 0.08135 0.07499 -0.0842 0.9581 0.0527
-9.000 -0.4066 0.07721 0.07078 -0.0861 0.9490 0.0526
-8.750 -0.4184 0.07307 0.06649 -0.0882 0.9417 0.0524
-8.500 -0.4316 0.06966 0.06291 -0.0877 0.9326 0.0524
-8.250 -0.4419 0.06587 0.05881 -0.0878 0.9256 0.0529
-8.000 -0.4500 0.06278 0.05540 -0.0864 0.9181 0.0534
-7.750 -0.4484 0.05905 0.05115 -0.0864 0.9130 0.0542
-7.500 -0.4529 0.05654 0.04839 -0.0836 0.9057 0.0549
-7.250 -0.4405 0.05342 0.04498 -0.0836 0.9015 0.0558
-7.000 -0.4285 0.05082 0.04208 -0.0829 0.8972 0.0568
-6.750 -0.4215 0.04883 0.03982 -0.0808 0.8913 0.0578
-6.500 -0.4024 0.04672 0.03738 -0.0807 0.8875 0.0607
-6.250 -0.3773 0.04437 0.03449 -0.0814 0.8847 0.0648
-6.000 -0.3713 0.04300 0.03269 -0.0782 0.8785 0.0666
-5.750 -0.3487 0.04107 0.03035 -0.0777 0.8748 0.0685
-5.500 -0.3211 0.03958 0.02877 -0.0783 0.8719 0.0730
-5.250 -0.2968 0.03850 0.02739 -0.0779 0.8685 0.0790
-5.000 -0.2810 0.03765 0.02632 -0.0757 0.8635 0.0822
-4.750 -0.2548 0.03670 0.02537 -0.0752 0.8603 0.0868
-4.500 -0.2246 0.03602 0.02445 -0.0753 0.8575 0.0963
-4.250 -0.2004 0.03537 0.02379 -0.0748 0.8544 0.1049
-4.000 -0.1924 0.03510 0.02342 -0.0715 0.8487 0.1108
-3.750 -0.1722 0.03453 0.02285 -0.0706 0.8449 0.1251
-3.500 -0.1482 0.03374 0.02220 -0.0706 0.8419 0.1489
-3.250 -0.1423 0.03325 0.02188 -0.0677 0.8364 0.1772
-3.000 -0.1328 0.03190 0.02138 -0.0661 0.8317 0.2976
-2.500 -0.1272 0.03278 0.02380 -0.0530 0.8229 0.7357
-2.250 -0.1229 0.03364 0.02454 -0.0472 0.8176 0.7802
-2.000 -0.1141 0.03452 0.02532 -0.0405 0.8139 0.8318
-1.750 -0.0396 0.03598 0.02645 -0.0428 0.8140 0.9145
-1.500 0.0236 0.03616 0.02623 -0.0495 0.8125 0.9296
-1.250 0.0462 0.03637 0.02625 -0.0500 0.8069 0.9353
-1.000 0.0679 0.03649 0.02618 -0.0499 0.8021 0.9411
-0.750 0.0998 0.03652 0.02601 -0.0516 0.7988 0.9450
-0.500 0.1202 0.03678 0.02612 -0.0516 0.7934 0.9494
-0.250 0.1385 0.03699 0.02621 -0.0512 0.7878 0.9541
0.000 0.1668 0.03707 0.02615 -0.0521 0.7841 0.9577
0.250 0.1855 0.03742 0.02641 -0.0519 0.7779 0.9615
0.500 0.2084 0.03767 0.02655 -0.0523 0.7725 0.9650
0.750 0.2407 0.03778 0.02656 -0.0538 0.7691 0.9678
1.000 0.2498 0.03827 0.02701 -0.0522 0.7613 0.9726
1.250 0.2792 0.03848 0.02715 -0.0534 0.7565 0.9754
1.500 0.3061 0.03875 0.02736 -0.0543 0.7517 0.9788
1.750 0.3200 0.03923 0.02783 -0.0534 0.7441 0.9838
2.000 0.3544 0.03936 0.02791 -0.0552 0.7402 0.9863
2.250 0.3649 0.03999 0.02855 -0.0540 0.7316 0.9922
2.500 0.3955 0.04018 0.02873 -0.0553 0.7268 0.9965
2.750 0.3979 0.04071 0.02925 -0.0524 0.7183 1.0000
3.000 0.4129 0.04083 0.02937 -0.0508 0.7125 1.0000
3.250 0.4058 0.04126 0.02980 -0.0462 0.7034 1.0000
3.500 0.4238 0.04135 0.02990 -0.0450 0.6978 1.0000
3.750 0.4226 0.04186 0.03042 -0.0416 0.6884 1.0000
4.000 0.4482 0.04201 0.03057 -0.0416 0.6833 1.0000
4.250 0.4547 0.04272 0.03131 -0.0398 0.6737 1.0000
4.500 0.4845 0.04291 0.03155 -0.0405 0.6688 1.0000
4.750 0.4946 0.04374 0.03241 -0.0394 0.6589 1.0000
5.000 0.5271 0.04389 0.03262 -0.0404 0.6542 1.0000
5.250 0.5381 0.04483 0.03362 -0.0396 0.6437 1.0000
5.500 0.5728 0.04490 0.03379 -0.0408 0.6394 1.0000
5.750 0.5838 0.04596 0.03492 -0.0401 0.6284 1.0000
6.250 0.6304 0.04708 0.03623 -0.0406 0.6129 1.0000
6.500 0.6455 0.04809 0.03734 -0.0403 0.6027 1.0000
6.750 0.6785 0.04814 0.03755 -0.0411 0.5974 1.0000
7.000 0.6905 0.04936 0.03887 -0.0406 0.5861 1.0000
7.500 0.7377 0.05045 0.04025 -0.0409 0.5699 1.0000
7.750 0.7511 0.05165 0.04163 -0.0405 0.5588 1.0000
8.000 0.7866 0.05131 0.04149 -0.0412 0.5540 1.0000
8.250 0.7976 0.05270 0.04302 -0.0406 0.5419 1.0000
8.500 0.8117 0.05387 0.04436 -0.0401 0.5306 1.0000
8.750 0.8475 0.05326 0.04403 -0.0404 0.5254 1.0000
9.000 0.8587 0.05463 0.04557 -0.0398 0.5130 1.0000
9.250 0.8724 0.05581 0.04694 -0.0392 0.5012 1.0000
9.500 0.9094 0.05470 0.04613 -0.0391 0.4956 1.0000
10.500 0.9998 0.05260 0.04514 -0.0342 0.4356 1.0000
10.750 1.0130 0.05010 0.04249 -0.0301 0.3739 1.0000
11.000 1.0155 0.05081 0.04282 -0.0276 0.3041 1.0000
11.250 1.0139 0.05285 0.04443 -0.0258 0.2312 1.0000
11.500 1.0012 0.05649 0.04747 -0.0243 0.1574 1.0000
11.750 0.9868 0.06089 0.05138 -0.0236 0.1094 1.0000
12.000 0.9756 0.06529 0.05548 -0.0233 0.0830 1.0000
12.250 0.9694 0.06930 0.05938 -0.0232 0.0692 1.0000
12.500 0.9656 0.07310 0.06314 -0.0232 0.0612 1.0000
12.750 0.9652 0.07657 0.06669 -0.0233 0.0554 1.0000
13.000 0.9640 0.08015 0.07024 -0.0234 0.0519 1.0000
13.250 0.9693 0.08292 0.07321 -0.0233 0.0484 1.0000
13.500 0.9743 0.08574 0.07614 -0.0233 0.0448 1.0000
13.750 0.9791 0.08854 0.07897 -0.0234 0.0421 1.0000
14.000 0.9893 0.09068 0.08125 -0.0231 0.0396 1.0000
14.250 1.0039 0.09232 0.08312 -0.0223 0.0375 1.0000
14.500 1.0212 0.09374 0.08475 -0.0214 0.0359 1.0000
14.750 1.0394 0.09528 0.08656 -0.0205 0.0346 1.0000
15.000 1.0556 0.09727 0.08876 -0.0200 0.0336 1.0000
15.250 1.0676 0.09988 0.09152 -0.0199 0.0325 1.0000
15.500 1.0751 0.10331 0.09511 -0.0202 0.0315 1.0000
15.750 1.0701 0.10817 0.10030 -0.0218 0.0311 1.0000
16.000 1.0618 0.11360 0.10605 -0.0239 0.0308 1.0000
16.250 1.0514 0.11956 0.11229 -0.0266 0.0306 1.0000
16.500 1.0396 0.12599 0.11897 -0.0299 0.0306 1.0000
16.750 1.0264 0.13301 0.12622 -0.0338 0.0306 1.0000
17.000 1.0120 0.14068 0.13408 -0.0384 0.0307 1.0000
17.250 0.9983 0.14869 0.14225 -0.0434 0.0309 1.0000
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