AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 50,000 Max Cl/Cd: 19.75 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k143-il-50000-n5.txt Download as CSV file: xf-ah79k143-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-143/18
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3696 0.10791 0.10140 -0.0609 0.9729 0.0540
-10.500 -0.3682 0.10270 0.09620 -0.0649 0.9691 0.0536
-10.000 -0.4038 0.08435 0.07783 -0.0821 0.9587 0.0486
-9.750 -0.4134 0.07920 0.07259 -0.0857 0.9545 0.0485
-9.500 -0.4237 0.07545 0.06875 -0.0869 0.9495 0.0482
-9.250 -0.4356 0.07179 0.06496 -0.0874 0.9447 0.0480
-9.000 -0.4471 0.06827 0.06128 -0.0870 0.9400 0.0478
-8.750 -0.4622 0.06544 0.05827 -0.0846 0.9345 0.0478
-8.500 -0.4689 0.06241 0.05501 -0.0831 0.9303 0.0477
-8.250 -0.4720 0.05879 0.05104 -0.0819 0.9268 0.0478
-8.000 -0.4833 0.05661 0.04858 -0.0778 0.9217 0.0479
-7.750 -0.4875 0.05406 0.04565 -0.0746 0.9174 0.0482
-7.500 -0.4839 0.05129 0.04247 -0.0726 0.9139 0.0490
-7.250 -0.4660 0.04954 0.04069 -0.0727 0.9114 0.0520
-7.000 -0.4668 0.04814 0.03906 -0.0689 0.9069 0.0537
-6.750 -0.4612 0.04619 0.03675 -0.0660 0.9029 0.0549
-6.500 -0.4469 0.04382 0.03389 -0.0644 0.8997 0.0565
-6.250 -0.4252 0.04153 0.03090 -0.0637 0.8970 0.0599
-6.000 -0.4018 0.03997 0.02930 -0.0638 0.8945 0.0643
-5.750 -0.3936 0.03899 0.02812 -0.0606 0.8901 0.0669
-5.500 -0.3707 0.03759 0.02632 -0.0597 0.8868 0.0716
-5.250 -0.3430 0.03642 0.02510 -0.0601 0.8840 0.0785
-5.000 -0.3054 0.03515 0.02355 -0.0615 0.8820 0.0876
-4.750 -0.2674 0.03418 0.02249 -0.0634 0.8802 0.1026
-4.500 -0.2575 0.03381 0.02210 -0.0604 0.8754 0.1138
-4.250 -0.2385 0.03325 0.02157 -0.0592 0.8714 0.1343
-4.000 -0.2148 0.03252 0.02096 -0.0589 0.8682 0.1666
-3.750 -0.1906 0.03162 0.02037 -0.0589 0.8654 0.2186
-3.500 -0.1926 0.03119 0.02030 -0.0542 0.8596 0.2743
-3.250 -0.1158 0.03111 0.02242 -0.0575 0.8613 0.7665
-3.000 -0.1212 0.03188 0.02302 -0.0510 0.8553 0.8192
-2.750 -0.0830 0.03305 0.02382 -0.0511 0.8527 0.8743
-2.500 0.0558 0.03371 0.02377 -0.0696 0.8558 0.9350
-2.250 0.1773 0.03294 0.02247 -0.0876 0.8579 0.9713
-2.000 0.2275 0.03268 0.02196 -0.0930 0.8550 0.9829
-1.750 0.2718 0.03250 0.02157 -0.0973 0.8522 0.9903
-1.500 0.3093 0.03248 0.02140 -0.1004 0.8484 0.9972
-1.250 0.3227 0.03291 0.02175 -0.0990 0.8422 1.0000
-1.000 0.3456 0.03318 0.02190 -0.0989 0.8379 1.0000
-0.750 0.3439 0.03390 0.02258 -0.0946 0.8297 1.0000
-0.500 0.3679 0.03419 0.02277 -0.0946 0.8253 1.0000
-0.250 0.3627 0.03496 0.02352 -0.0896 0.8164 1.0000
0.000 0.3670 0.03558 0.02409 -0.0862 0.8090 1.0000
0.250 0.3800 0.03605 0.02451 -0.0843 0.8026 1.0000
0.500 0.3750 0.03676 0.02520 -0.0794 0.7939 1.0000
0.750 0.3944 0.03713 0.02553 -0.0785 0.7885 1.0000
1.000 0.3842 0.03784 0.02622 -0.0727 0.7790 1.0000
1.250 0.4075 0.03816 0.02651 -0.0724 0.7741 1.0000
1.500 0.3932 0.03882 0.02716 -0.0659 0.7639 1.0000
1.750 0.4189 0.03910 0.02742 -0.0659 0.7593 1.0000
2.000 0.4046 0.03973 0.02804 -0.0595 0.7489 1.0000
2.250 0.4310 0.03998 0.02828 -0.0595 0.7444 1.0000
2.500 0.4194 0.04057 0.02886 -0.0538 0.7340 1.0000
2.750 0.4459 0.04080 0.02910 -0.0537 0.7297 1.0000
3.000 0.4360 0.04137 0.02967 -0.0483 0.7193 1.0000
3.250 0.4636 0.04156 0.02989 -0.0483 0.7152 1.0000
3.500 0.4544 0.04214 0.03048 -0.0431 0.7045 1.0000
3.750 0.4644 0.04251 0.03087 -0.0407 0.6973 1.0000
4.000 0.4742 0.04287 0.03125 -0.0382 0.6896 1.0000
4.250 0.4800 0.04330 0.03172 -0.0352 0.6813 1.0000
4.500 0.4951 0.04358 0.03207 -0.0334 0.6745 1.0000
4.750 0.4983 0.04409 0.03260 -0.0301 0.6655 1.0000
5.000 0.5172 0.04431 0.03289 -0.0289 0.6594 1.0000
5.250 0.5190 0.04489 0.03350 -0.0256 0.6497 1.0000
5.500 0.5418 0.04502 0.03371 -0.0247 0.6441 1.0000
5.750 0.5430 0.04568 0.03445 -0.0215 0.6338 1.0000
6.000 0.5697 0.04567 0.03454 -0.0211 0.6285 1.0000
6.250 0.5707 0.04650 0.03543 -0.0181 0.6175 1.0000
6.500 0.6003 0.04642 0.03548 -0.0179 0.6128 1.0000
6.750 0.6025 0.04735 0.03651 -0.0153 0.6012 1.0000
7.000 0.6169 0.04788 0.03715 -0.0139 0.5923 1.0000
7.250 0.6389 0.04807 0.03749 -0.0131 0.5846 1.0000
7.500 0.6483 0.04891 0.03845 -0.0114 0.5737 1.0000
7.750 0.6792 0.04860 0.03836 -0.0112 0.5679 1.0000
8.000 0.6875 0.04952 0.03940 -0.0095 0.5555 1.0000
8.250 0.7029 0.05006 0.04012 -0.0083 0.5449 1.0000
8.500 0.7334 0.04949 0.03979 -0.0078 0.5374 1.0000
8.750 0.7445 0.05023 0.04070 -0.0062 0.5243 1.0000
9.000 0.7604 0.05059 0.04128 -0.0049 0.5120 1.0000
9.250 0.7992 0.04893 0.03996 -0.0042 0.5052 1.0000
9.500 0.8176 0.04865 0.03991 -0.0025 0.4906 1.0000
9.750 0.8374 0.04671 0.03819 0.0006 0.4631 1.0000
10.250 0.8677 0.04426 0.03582 0.0067 0.3782 1.0000
10.500 0.8771 0.04440 0.03579 0.0094 0.3179 1.0000
10.750 0.8753 0.04579 0.03655 0.0121 0.2322 1.0000
11.000 0.8638 0.04872 0.03890 0.0142 0.1700 1.0000
11.250 0.8542 0.05198 0.04176 0.0156 0.1314 1.0000
11.500 0.8470 0.05524 0.04476 0.0167 0.1065 1.0000
11.750 0.8440 0.05820 0.04758 0.0175 0.0917 1.0000
12.000 0.8437 0.06096 0.05026 0.0183 0.0818 1.0000
12.250 0.8463 0.06345 0.05275 0.0189 0.0742 1.0000
12.500 0.8518 0.06568 0.05503 0.0197 0.0674 1.0000
12.750 0.8587 0.06779 0.05716 0.0204 0.0620 1.0000
13.000 0.8725 0.06921 0.05864 0.0214 0.0585 1.0000
13.250 0.8883 0.07062 0.06030 0.0224 0.0542 1.0000
13.500 0.9041 0.07206 0.06176 0.0232 0.0503 1.0000
13.750 0.9325 0.07284 0.06273 0.0244 0.0476 1.0000
14.000 0.9550 0.07466 0.06491 0.0253 0.0458 1.0000
14.250 0.9676 0.07736 0.06791 0.0257 0.0443 1.0000
14.500 0.9721 0.08056 0.07136 0.0257 0.0428 1.0000
14.750 0.9728 0.08392 0.07493 0.0255 0.0415 1.0000
15.000 0.9723 0.08754 0.07878 0.0251 0.0407 1.0000
15.250 0.9710 0.09135 0.08274 0.0246 0.0399 1.0000
15.500 0.9645 0.09585 0.08740 0.0236 0.0391 1.0000
15.750 0.9521 0.10111 0.09291 0.0220 0.0391 1.0000
16.000 0.9362 0.10697 0.09902 0.0197 0.0391 1.0000
16.250 0.9207 0.11312 0.10538 0.0169 0.0391 1.0000
16.500 0.8998 0.12058 0.11304 0.0129 0.0391 1.0000
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Polar data table (+)
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