AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 50,000 Max Cl/Cd: 22.97 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah63k127-il-50000-n5.txt Download as CSV file: xf-ah63k127-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 63-K-127/24
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2988 0.12176 0.11548 -0.0582 0.9670 0.1063
-10.250 -0.3066 0.11955 0.11332 -0.0650 0.9615 0.1106
-10.000 -0.3017 0.11564 0.10941 -0.0683 0.9567 0.1114
-9.750 -0.2832 0.11073 0.10445 -0.0689 0.9538 0.1128
-9.500 -0.2725 0.10671 0.10041 -0.0718 0.9506 0.1134
-9.250 -0.2682 0.09740 0.09099 -0.0809 0.9463 0.0546
-9.000 -0.2563 0.09384 0.08740 -0.0812 0.9428 0.0517
-8.750 -0.2507 0.08974 0.08331 -0.0844 0.9387 0.0494
-8.500 -0.2475 0.08485 0.07842 -0.0892 0.9348 0.0470
-8.250 -0.2588 0.07984 0.07344 -0.0942 0.9282 0.0448
-8.000 -0.2728 0.07506 0.06853 -0.0990 0.9217 0.0422
-7.750 -0.2716 0.07197 0.06535 -0.0994 0.9176 0.0417
-7.500 -0.2762 0.06933 0.06266 -0.0987 0.9124 0.0411
-7.250 -0.2755 0.06615 0.05937 -0.0993 0.9083 0.0406
-7.000 -0.2747 0.06298 0.05603 -0.0995 0.9044 0.0401
-6.750 -0.2803 0.06071 0.05361 -0.0975 0.8990 0.0398
-6.500 -0.2770 0.05762 0.05024 -0.0971 0.8950 0.0399
-6.250 -0.2660 0.05431 0.04656 -0.0976 0.8919 0.0401
-6.000 -0.2677 0.05235 0.04431 -0.0947 0.8866 0.0406
-5.750 -0.2579 0.04982 0.04137 -0.0936 0.8827 0.0411
-5.500 -0.2399 0.04710 0.03813 -0.0935 0.8796 0.0417
-5.250 -0.2190 0.04457 0.03508 -0.0934 0.8768 0.0421
-5.000 -0.2109 0.04295 0.03312 -0.0908 0.8721 0.0422
-4.750 -0.1907 0.04099 0.03072 -0.0900 0.8687 0.0424
-4.500 -0.1639 0.03883 0.02818 -0.0901 0.8660 0.0431
-4.250 -0.1337 0.03690 0.02594 -0.0907 0.8638 0.0445
-4.000 -0.1218 0.03606 0.02496 -0.0882 0.8593 0.0461
-3.750 -0.0998 0.03518 0.02389 -0.0873 0.8556 0.0509
-3.500 -0.0710 0.03423 0.02266 -0.0870 0.8528 0.0562
-3.250 -0.0413 0.03319 0.02154 -0.0872 0.8504 0.0620
-3.000 -0.0298 0.03289 0.02105 -0.0845 0.8453 0.0692
-2.750 -0.0092 0.03219 0.02035 -0.0837 0.8412 0.0868
-2.500 0.0164 0.03094 0.01951 -0.0839 0.8382 0.1491
-2.250 0.0180 0.02874 0.01988 -0.0787 0.8347 0.6134
-2.000 0.0081 0.02940 0.02087 -0.0691 0.8284 0.8167
-1.750 0.2195 0.02936 0.01957 -0.0980 0.8374 0.9923
-1.500 0.2422 0.02968 0.01965 -0.0985 0.8326 1.0000
-1.250 0.2475 0.03007 0.01989 -0.0955 0.8263 1.0000
-1.000 0.2699 0.03027 0.01985 -0.0952 0.8226 1.0000
-0.750 0.2572 0.03092 0.02044 -0.0892 0.8140 1.0000
-0.500 0.2774 0.03119 0.02052 -0.0885 0.8098 1.0000
-0.250 0.2672 0.03180 0.02107 -0.0829 0.8014 1.0000
0.000 0.2865 0.03213 0.02123 -0.0819 0.7969 1.0000
0.250 0.2761 0.03275 0.02177 -0.0763 0.7882 1.0000
0.500 0.3003 0.03311 0.02197 -0.0762 0.7840 1.0000
0.750 0.2976 0.03378 0.02255 -0.0720 0.7755 1.0000
1.000 0.3241 0.03420 0.02283 -0.0723 0.7712 1.0000
1.250 0.3291 0.03492 0.02347 -0.0695 0.7634 1.0000
1.500 0.3543 0.03542 0.02385 -0.0697 0.7586 1.0000
1.750 0.3656 0.03613 0.02449 -0.0680 0.7514 1.0000
2.000 0.3882 0.03670 0.02499 -0.0678 0.7460 1.0000
2.250 0.4060 0.03737 0.02559 -0.0670 0.7399 1.0000
2.500 0.4240 0.03804 0.02622 -0.0663 0.7334 1.0000
2.750 0.4557 0.03850 0.02665 -0.0673 0.7300 1.0000
3.000 0.4610 0.03941 0.02754 -0.0651 0.7209 1.0000
3.250 0.4914 0.03990 0.02802 -0.0659 0.7172 1.0000
3.500 0.4988 0.04084 0.02896 -0.0641 0.7084 1.0000
3.750 0.5283 0.04133 0.02947 -0.0647 0.7043 1.0000
4.000 0.5374 0.04230 0.03048 -0.0632 0.6959 1.0000
4.250 0.5656 0.04282 0.03104 -0.0637 0.6915 1.0000
4.500 0.5762 0.04381 0.03207 -0.0624 0.6834 1.0000
4.750 0.6034 0.04436 0.03268 -0.0628 0.6786 1.0000
5.000 0.6152 0.04537 0.03375 -0.0617 0.6706 1.0000
5.250 0.6410 0.04596 0.03447 -0.0619 0.6655 1.0000
5.500 0.6538 0.04700 0.03559 -0.0609 0.6576 1.0000
5.750 0.6787 0.04761 0.03632 -0.0610 0.6522 1.0000
6.000 0.6920 0.04866 0.03748 -0.0602 0.6441 1.0000
6.250 0.7171 0.04926 0.03827 -0.0602 0.6385 1.0000
6.500 0.7298 0.05036 0.03950 -0.0593 0.6299 1.0000
6.750 0.7566 0.05086 0.04018 -0.0595 0.6244 1.0000
7.000 0.7676 0.05206 0.04153 -0.0585 0.6150 1.0000
7.250 0.7977 0.05234 0.04203 -0.0588 0.6099 1.0000
7.500 0.8077 0.05358 0.04344 -0.0576 0.5993 1.0000
7.750 0.8274 0.05415 0.04427 -0.0570 0.5897 1.0000
8.000 0.8551 0.05336 0.04373 -0.0559 0.5756 1.0000
8.250 0.8877 0.05148 0.04212 -0.0543 0.5577 1.0000
8.500 0.9224 0.04931 0.04027 -0.0526 0.5409 1.0000
8.750 0.9501 0.04801 0.03933 -0.0510 0.5256 1.0000
9.000 0.9617 0.04819 0.03977 -0.0489 0.5053 1.0000
9.250 0.9890 0.04644 0.03834 -0.0467 0.4825 1.0000
9.500 0.9965 0.04688 0.03902 -0.0443 0.4505 1.0000
9.750 1.0087 0.04668 0.03896 -0.0418 0.4007 1.0000
10.000 1.0314 0.04490 0.03642 -0.0378 0.2733 1.0000
10.250 1.0238 0.04758 0.03845 -0.0353 0.2134 1.0000
10.500 1.0176 0.05056 0.04107 -0.0335 0.1786 1.0000
10.750 1.0142 0.05345 0.04376 -0.0321 0.1523 1.0000
11.000 1.0133 0.05623 0.04637 -0.0308 0.1316 1.0000
11.250 1.0152 0.05886 0.04895 -0.0298 0.1120 1.0000
11.500 1.0189 0.06138 0.05141 -0.0287 0.0962 1.0000
11.750 1.0242 0.06380 0.05382 -0.0279 0.0822 1.0000
12.000 1.0342 0.06589 0.05599 -0.0268 0.0703 1.0000
12.250 1.0456 0.06796 0.05818 -0.0258 0.0600 1.0000
12.500 1.0657 0.06952 0.05989 -0.0245 0.0518 1.0000
12.750 1.0782 0.07163 0.06205 -0.0239 0.0457 1.0000
13.000 1.1076 0.07363 0.06454 -0.0225 0.0405 1.0000
13.250 1.1193 0.07663 0.06786 -0.0219 0.0375 1.0000
13.500 1.1230 0.07978 0.07114 -0.0216 0.0352 1.0000
13.750 1.1260 0.08354 0.07506 -0.0215 0.0335 1.0000
14.000 1.1185 0.08822 0.08018 -0.0217 0.0326 1.0000
14.250 1.1079 0.09334 0.08567 -0.0223 0.0319 1.0000
14.500 1.0950 0.09889 0.09154 -0.0235 0.0316 1.0000
14.750 1.0798 0.10492 0.09786 -0.0254 0.0315 1.0000
15.000 1.0627 0.11158 0.10477 -0.0281 0.0315 1.0000
15.250 1.0447 0.11879 0.11220 -0.0316 0.0317 1.0000
15.500 1.0256 0.12681 0.12040 -0.0360 0.0319 1.0000
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Polar data table (+)
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