AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 50,000 Max Cl/Cd: 23.9 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k130-il-50000-n5.txt Download as CSV file: xf-ah88k130-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3353 0.11374 0.10748 -0.0598 0.9688 0.1110
-8.750 -0.3365 0.11084 0.10461 -0.0611 0.9649 0.1144
-8.500 -0.3668 0.10917 0.10307 -0.0679 0.9590 0.1187
-8.250 -0.3386 0.10406 0.09793 -0.0661 0.9581 0.1216
-8.000 -0.3422 0.09657 0.09034 -0.0698 0.9528 0.0585
-7.750 -0.3685 0.09109 0.08482 -0.0767 0.9458 0.0497
-7.500 -0.3636 0.08780 0.08154 -0.0764 0.9424 0.0487
-7.250 -0.3693 0.08483 0.07857 -0.0755 0.9374 0.0477
-7.000 -0.3697 0.08104 0.07471 -0.0769 0.9328 0.0472
-6.750 -0.3687 0.07719 0.07075 -0.0781 0.9287 0.0465
-6.500 -0.3738 0.07409 0.06755 -0.0772 0.9232 0.0462
-6.250 -0.3682 0.07024 0.06351 -0.0782 0.9189 0.0457
-6.000 -0.3596 0.06646 0.05947 -0.0793 0.9150 0.0456
-5.750 -0.3571 0.06339 0.05617 -0.0781 0.9098 0.0452
-5.500 -0.3430 0.05980 0.05223 -0.0788 0.9058 0.0447
-5.250 -0.3218 0.05594 0.04791 -0.0803 0.9029 0.0437
-5.000 -0.3117 0.05314 0.04472 -0.0790 0.8980 0.0431
-4.750 -0.2915 0.05019 0.04128 -0.0790 0.8941 0.0425
-4.500 -0.2649 0.04733 0.03788 -0.0798 0.8912 0.0424
-4.250 -0.2340 0.04482 0.03478 -0.0810 0.8889 0.0428
-4.000 -0.2177 0.04315 0.03274 -0.0794 0.8842 0.0436
-3.750 -0.1921 0.04162 0.03076 -0.0792 0.8806 0.0469
-3.500 -0.1619 0.04034 0.02896 -0.0793 0.8777 0.0504
-3.250 -0.1315 0.03875 0.02726 -0.0798 0.8755 0.0539
-3.000 -0.1142 0.03801 0.02637 -0.0779 0.8710 0.0581
-2.750 -0.0920 0.03731 0.02547 -0.0767 0.8671 0.0656
-2.500 -0.0655 0.03655 0.02454 -0.0763 0.8640 0.0736
-2.250 -0.0357 0.03591 0.02375 -0.0769 0.8614 0.0903
-2.000 -0.0215 0.03541 0.02325 -0.0751 0.8562 0.1053
-1.750 0.0029 0.03403 0.02259 -0.0757 0.8526 0.2083
-1.500 0.0932 0.03351 0.02420 -0.0788 0.8563 1.0000
-1.250 0.1037 0.03365 0.02407 -0.0767 0.8509 1.0000
-1.000 0.1263 0.03383 0.02393 -0.0766 0.8474 1.0000
-0.750 0.1180 0.03400 0.02398 -0.0713 0.8396 1.0000
-0.500 0.1350 0.03422 0.02393 -0.0702 0.8354 1.0000
-0.250 0.1410 0.03446 0.02399 -0.0672 0.8295 1.0000
0.000 0.1523 0.03473 0.02409 -0.0653 0.8240 1.0000
0.250 0.1765 0.03508 0.02421 -0.0654 0.8205 1.0000
0.500 0.1859 0.03547 0.02446 -0.0633 0.8144 1.0000
0.750 0.2058 0.03590 0.02470 -0.0628 0.8096 1.0000
1.000 0.2341 0.03636 0.02499 -0.0637 0.8064 1.0000
1.250 0.2467 0.03689 0.02541 -0.0623 0.8003 1.0000
1.500 0.2694 0.03740 0.02581 -0.0624 0.7956 1.0000
1.750 0.2998 0.03791 0.02620 -0.0636 0.7923 1.0000
2.000 0.3124 0.03853 0.02674 -0.0622 0.7855 1.0000
2.250 0.3383 0.03907 0.02720 -0.0627 0.7808 1.0000
2.500 0.3710 0.03959 0.02765 -0.0642 0.7776 1.0000
2.750 0.3806 0.04030 0.02833 -0.0625 0.7697 1.0000
3.000 0.4097 0.04085 0.02886 -0.0635 0.7656 1.0000
3.250 0.4274 0.04155 0.02955 -0.0630 0.7593 1.0000
3.500 0.4504 0.04219 0.03018 -0.0631 0.7536 1.0000
3.750 0.4828 0.04271 0.03074 -0.0644 0.7501 1.0000
4.000 0.4936 0.04353 0.03159 -0.0630 0.7416 1.0000
4.250 0.5242 0.04404 0.03214 -0.0641 0.7372 1.0000
4.500 0.5384 0.04483 0.03298 -0.0631 0.7290 1.0000
4.750 0.5681 0.04533 0.03355 -0.0640 0.7241 1.0000
5.250 0.6139 0.04657 0.03501 -0.0641 0.7107 1.0000
5.500 0.6287 0.04739 0.03592 -0.0633 0.7015 1.0000
5.750 0.6620 0.04769 0.03636 -0.0644 0.6967 1.0000
6.000 0.6758 0.04851 0.03731 -0.0634 0.6865 1.0000
6.250 0.6983 0.04907 0.03807 -0.0632 0.6782 1.0000
6.500 0.7264 0.04937 0.03855 -0.0636 0.6708 1.0000
6.750 0.7434 0.05009 0.03944 -0.0629 0.6603 1.0000
7.000 0.7696 0.05041 0.03997 -0.0629 0.6520 1.0000
7.250 0.7969 0.05056 0.04041 -0.0630 0.6430 1.0000
7.500 0.8156 0.05105 0.04112 -0.0622 0.6310 1.0000
7.750 0.8370 0.05134 0.04165 -0.0615 0.6189 1.0000
8.000 0.8610 0.05137 0.04196 -0.0609 0.6067 1.0000
8.250 0.8861 0.05119 0.04208 -0.0602 0.5940 1.0000
8.500 0.9104 0.05080 0.04206 -0.0591 0.5790 1.0000
8.750 0.9379 0.04968 0.04129 -0.0577 0.5616 1.0000
9.000 0.9621 0.04781 0.03975 -0.0550 0.5350 1.0000
9.250 0.9760 0.04654 0.03870 -0.0516 0.4939 1.0000
9.500 0.9960 0.04515 0.03745 -0.0486 0.4365 1.0000
9.750 1.0271 0.04298 0.03478 -0.0452 0.3189 1.0000
10.000 1.0176 0.04571 0.03664 -0.0419 0.2199 1.0000
10.250 1.0048 0.04934 0.03960 -0.0396 0.1508 1.0000
10.500 0.9977 0.05280 0.04258 -0.0380 0.1088 1.0000
10.750 0.9955 0.05593 0.04546 -0.0366 0.0856 1.0000
11.000 0.9975 0.05875 0.04823 -0.0354 0.0713 1.0000
11.250 1.0029 0.06128 0.05081 -0.0342 0.0619 1.0000
11.500 1.0123 0.06347 0.05314 -0.0331 0.0534 1.0000
11.750 1.0242 0.06552 0.05517 -0.0320 0.0476 1.0000
12.000 1.0584 0.06616 0.05618 -0.0304 0.0424 1.0000
12.250 1.0895 0.06764 0.05770 -0.0298 0.0375 1.0000
12.500 1.1145 0.06997 0.06057 -0.0290 0.0342 1.0000
12.750 1.1358 0.07309 0.06411 -0.0284 0.0325 1.0000
13.000 1.1452 0.07679 0.06819 -0.0277 0.0316 1.0000
13.250 1.1463 0.08086 0.07262 -0.0271 0.0310 1.0000
13.500 1.1414 0.08518 0.07727 -0.0266 0.0306 1.0000
13.750 1.1324 0.08976 0.08217 -0.0265 0.0303 1.0000
14.000 1.1204 0.09461 0.08730 -0.0269 0.0300 1.0000
14.250 1.1060 0.09985 0.09281 -0.0278 0.0298 1.0000
14.500 1.0893 0.10564 0.09887 -0.0294 0.0298 1.0000
14.750 1.0694 0.11232 0.10582 -0.0319 0.0300 1.0000
15.000 1.0448 0.12043 0.11419 -0.0360 0.0307 1.0000
15.250 1.0199 0.12970 0.12367 -0.0415 0.0315 1.0000
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Polar data table (+)
Polar graphs
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