AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 100,000 Max Cl/Cd: 42.51 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k130-il-100000.txt Download as CSV file: xf-ah88k130-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-130/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4484 0.11656 0.11256 -0.0393 0.9923 0.0756
-8.250 -0.4626 0.11397 0.11002 -0.0425 0.9894 0.0760
-8.000 -0.4852 0.11144 0.10754 -0.0457 0.9864 0.0762
-7.750 -0.4311 0.10502 0.10105 -0.0417 0.9851 0.0821
-7.500 -0.4375 0.10238 0.09844 -0.0420 0.9821 0.0841
-7.250 -0.4513 0.09986 0.09598 -0.0422 0.9789 0.0858
-7.000 -0.4674 0.09687 0.09303 -0.0441 0.9758 0.0871
-6.750 -0.4819 0.09282 0.08890 -0.0503 0.9728 0.0893
-6.500 -0.5038 0.09043 0.08619 -0.0540 0.9708 0.0904
-6.250 -0.4912 0.08509 0.08112 -0.0507 0.9677 0.0928
-6.000 -0.4845 0.08243 0.07848 -0.0492 0.9649 0.0965
-5.750 -0.5845 0.08641 0.08218 -0.0335 1.0000 0.0907
-5.500 -0.5785 0.08120 0.07731 -0.0300 1.0000 0.0926
-5.250 -0.5732 0.07844 0.07458 -0.0281 1.0000 0.0959
-5.000 -0.5640 0.07437 0.06999 -0.0335 1.0000 0.1054
-4.750 -0.5574 0.07070 0.06654 -0.0312 1.0000 0.1081
-4.500 -0.5427 0.06742 0.06285 -0.0341 1.0000 0.1200
-4.250 -0.5334 0.06431 0.05989 -0.0325 1.0000 0.1240
-4.000 -0.5177 0.06102 0.05639 -0.0340 1.0000 0.1368
-3.750 -0.5017 0.05816 0.05339 -0.0347 1.0000 0.1512
-3.500 -0.4855 0.05562 0.05073 -0.0350 1.0000 0.1671
-3.250 -0.2904 0.04440 0.03687 -0.0626 0.9460 0.0787
-3.000 -0.2671 0.04247 0.03460 -0.0620 0.9462 0.0725
-2.750 -0.2158 0.03984 0.03109 -0.0648 0.9330 0.0648
-2.500 -0.1895 0.03904 0.02993 -0.0643 0.9323 0.0629
-2.250 -0.1690 0.03795 0.02865 -0.0634 0.9327 0.0627
-2.000 -0.1076 0.03615 0.02672 -0.0685 0.9165 0.0679
-1.750 -0.0927 0.03586 0.02632 -0.0667 0.9131 0.0762
-1.500 -0.0970 0.03573 0.02632 -0.0627 0.9313 0.0795
-1.250 -0.0706 0.03551 0.02620 -0.0632 0.9305 0.0954
-1.000 -0.1429 0.03473 0.02539 -0.0478 0.9786 0.0805
-0.750 -0.1080 0.03474 0.02547 -0.0497 0.9746 0.1019
-0.500 -0.0118 0.03307 0.02677 -0.0520 0.9015 1.0000
0.000 -0.0613 0.03344 0.02714 -0.0390 0.9588 1.0000
0.250 -0.0386 0.03367 0.02711 -0.0394 0.9493 1.0000
0.500 0.0033 0.03549 0.02861 -0.0434 0.9442 1.0000
0.750 0.0217 0.03548 0.02844 -0.0430 0.9344 1.0000
1.000 0.0615 0.03726 0.02997 -0.0466 0.9296 1.0000
1.250 0.0829 0.03744 0.03002 -0.0467 0.9190 1.0000
1.500 0.1075 0.03826 0.03072 -0.0476 0.9115 1.0000
1.750 0.1481 0.03973 0.03201 -0.0510 0.9033 1.0000
2.000 0.1663 0.04009 0.03230 -0.0506 0.8932 1.0000
2.250 0.1943 0.04105 0.03317 -0.0519 0.8836 1.0000
2.500 0.2358 0.04251 0.03453 -0.0552 0.8741 1.0000
2.750 0.3174 0.04105 0.03288 -0.0604 0.8127 1.0000
3.000 0.3628 0.04178 0.03356 -0.0636 0.8060 1.0000
3.250 0.3745 0.04235 0.03412 -0.0623 0.7963 1.0000
3.500 0.4068 0.04303 0.03478 -0.0637 0.7887 1.0000
3.750 0.4326 0.04364 0.03540 -0.0642 0.7807 1.0000
4.000 0.4550 0.04432 0.03609 -0.0643 0.7717 1.0000
4.250 0.4925 0.04485 0.03665 -0.0662 0.7653 1.0000
4.500 0.5092 0.04553 0.03736 -0.0656 0.7552 1.0000
4.750 0.5536 0.04592 0.03780 -0.0682 0.7502 1.0000
5.000 0.5678 0.04656 0.03849 -0.0673 0.7392 1.0000
5.250 0.5909 0.04714 0.03916 -0.0673 0.7297 1.0000
5.500 0.6322 0.04725 0.03937 -0.0693 0.7238 1.0000
5.750 0.6490 0.04794 0.04013 -0.0686 0.7131 1.0000
6.000 0.6738 0.04843 0.04072 -0.0688 0.7039 1.0000
6.250 0.7153 0.04822 0.04069 -0.0705 0.6975 1.0000
6.500 0.7364 0.04862 0.04120 -0.0701 0.6862 1.0000
6.750 0.7635 0.04875 0.04148 -0.0701 0.6759 1.0000
7.000 0.8126 0.04763 0.04060 -0.0720 0.6700 1.0000
7.250 0.8389 0.04740 0.04055 -0.0715 0.6580 1.0000
7.500 0.8809 0.04554 0.03892 -0.0717 0.6455 1.0000
7.750 0.9400 0.04152 0.03523 -0.0721 0.6328 1.0000
8.000 1.0044 0.03635 0.03043 -0.0723 0.6206 1.0000
8.250 1.0567 0.03219 0.02664 -0.0718 0.6069 1.0000
8.500 1.1024 0.02743 0.02207 -0.0692 0.5554 1.0000
8.750 1.1164 0.02626 0.01998 -0.0641 0.3853 1.0000
9.000 1.0930 0.02933 0.02198 -0.0583 0.2501 1.0000
9.250 1.0700 0.03302 0.02466 -0.0535 0.1403 1.0000
9.500 1.0589 0.03624 0.02731 -0.0497 0.0916 1.0000
9.750 1.0570 0.03882 0.02973 -0.0469 0.0740 1.0000
10.000 1.0638 0.04089 0.03178 -0.0448 0.0639 1.0000
10.250 1.0783 0.04271 0.03358 -0.0432 0.0553 1.0000
10.500 1.1255 0.04451 0.03517 -0.0437 0.0476 1.0000
10.750 1.1657 0.04633 0.03728 -0.0441 0.0434 1.0000
11.000 1.2081 0.04899 0.04005 -0.0454 0.0390 1.0000
11.250 1.2735 0.05503 0.04654 -0.0491 0.0381 1.0000
11.500 1.2845 0.05817 0.05013 -0.0471 0.0386 1.0000
11.750 1.2824 0.06144 0.05397 -0.0437 0.0398 1.0000
12.000 1.2668 0.06556 0.05869 -0.0396 0.0416 1.0000
12.250 1.2544 0.07003 0.06360 -0.0366 0.0430 1.0000
12.500 1.2407 0.07442 0.06833 -0.0342 0.0440 1.0000
12.750 1.2262 0.07905 0.07324 -0.0322 0.0451 1.0000
13.000 1.2102 0.08377 0.07822 -0.0307 0.0458 1.0000
13.250 1.1949 0.08900 0.08365 -0.0298 0.0467 1.0000
13.500 1.0203 0.08646 0.08182 -0.0190 0.0450 1.0000
13.750 0.9873 0.09095 0.08655 -0.0193 0.0453 1.0000
14.000 0.9583 0.09596 0.09177 -0.0206 0.0458 1.0000
14.250 0.9294 0.10163 0.09763 -0.0229 0.0463 1.0000
14.500 0.9024 0.10772 0.10388 -0.0259 0.0468 1.0000
14.750 0.8796 0.11422 0.11049 -0.0293 0.0475 1.0000
15.000 0.8645 0.12021 0.11663 -0.0326 0.0491 1.0000
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Polar data table (+)
Polar graphs
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