AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.82 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah63k127-il-1000000-n5.txt Download as CSV file: xf-ah63k127-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2090 0.09828 0.09528 -0.0858 0.7426 0.0053
-10.750 -0.2057 0.09467 0.09168 -0.0875 0.7422 0.0051
-10.500 -0.2033 0.09081 0.08784 -0.0893 0.7417 0.0050
-10.250 -0.2025 0.08668 0.08374 -0.0912 0.7411 0.0048
-10.000 -0.2016 0.08264 0.07972 -0.0932 0.7405 0.0046
-9.750 -0.2050 0.07767 0.07478 -0.0956 0.7399 0.0045
-9.500 -0.2106 0.07239 0.06953 -0.0984 0.7393 0.0042
-9.250 -0.2260 0.06512 0.06232 -0.1028 0.7385 0.0041
-9.000 -0.2397 0.05837 0.05561 -0.1093 0.7375 0.0042
-8.750 -0.2982 0.04774 0.04486 -0.1114 0.7362 0.0039
-8.500 -0.3091 0.04255 0.03952 -0.1109 0.7351 0.0039
-8.250 -0.3268 0.03495 0.03160 -0.1089 0.7341 0.0040
-8.000 -0.3347 0.02834 0.02455 -0.1063 0.7333 0.0042
-7.750 -0.3261 0.02486 0.02073 -0.1047 0.7326 0.0044
-7.500 -0.3090 0.02298 0.01861 -0.1039 0.7318 0.0047
-7.250 -0.2943 0.02013 0.01538 -0.1025 0.7311 0.0049
-7.000 -0.2740 0.01844 0.01343 -0.1017 0.7303 0.0051
-6.750 -0.2520 0.01702 0.01178 -0.1011 0.7295 0.0052
-6.500 -0.2285 0.01594 0.01054 -0.1007 0.7287 0.0053
-6.250 -0.2042 0.01498 0.00943 -0.1004 0.7278 0.0054
-6.000 -0.1798 0.01402 0.00833 -0.1000 0.7268 0.0055
-5.750 -0.1544 0.01339 0.00760 -0.0998 0.7257 0.0056
-5.500 -0.1281 0.01294 0.00709 -0.0997 0.7246 0.0058
-5.250 -0.1021 0.01245 0.00652 -0.0996 0.7235 0.0059
-5.000 -0.0766 0.01181 0.00581 -0.0994 0.7224 0.0060
-4.750 -0.0508 0.01127 0.00519 -0.0992 0.7213 0.0060
-4.500 -0.0249 0.01077 0.00462 -0.0990 0.7203 0.0060
-4.250 0.0016 0.01036 0.00415 -0.0989 0.7193 0.0060
-4.000 0.0276 0.00985 0.00356 -0.0987 0.7182 0.0063
-3.750 0.0542 0.00946 0.00311 -0.0987 0.7171 0.0069
-3.500 0.0816 0.00923 0.00286 -0.0987 0.7158 0.0074
-3.250 0.1091 0.00903 0.00265 -0.0988 0.7143 0.0082
-3.000 0.1368 0.00885 0.00246 -0.0990 0.7125 0.0092
-2.750 0.1645 0.00866 0.00227 -0.0991 0.7108 0.0117
-2.500 0.1924 0.00850 0.00212 -0.0992 0.7091 0.0153
-2.250 0.2201 0.00830 0.00196 -0.0994 0.7074 0.0289
-2.000 0.2469 0.00795 0.00181 -0.0995 0.7059 0.0872
-1.750 0.2735 0.00756 0.00167 -0.0996 0.7044 0.1720
-1.500 0.2997 0.00711 0.00157 -0.0998 0.7028 0.2873
-1.250 0.3235 0.00631 0.00147 -0.0997 0.7007 0.5148
-1.000 0.3502 0.00601 0.00142 -0.0997 0.6985 0.6015
-0.750 0.3767 0.00577 0.00143 -0.0996 0.6962 0.6834
-0.500 0.4041 0.00568 0.00143 -0.0996 0.6940 0.7267
-0.250 0.4320 0.00564 0.00142 -0.0997 0.6919 0.7503
0.000 0.4603 0.00563 0.00140 -0.0999 0.6898 0.7617
0.250 0.4887 0.00563 0.00143 -0.1001 0.6869 0.7714
0.500 0.5170 0.00563 0.00144 -0.1003 0.6837 0.7797
0.750 0.5453 0.00563 0.00144 -0.1005 0.6805 0.7877
1.000 0.5733 0.00563 0.00144 -0.1006 0.6774 0.7956
1.250 0.6016 0.00566 0.00147 -0.1009 0.6738 0.8036
1.500 0.6297 0.00567 0.00151 -0.1010 0.6697 0.8087
1.750 0.6577 0.00569 0.00152 -0.1012 0.6655 0.8132
2.000 0.6859 0.00572 0.00154 -0.1014 0.6609 0.8171
2.250 0.7140 0.00575 0.00158 -0.1016 0.6554 0.8200
2.500 0.7415 0.00579 0.00161 -0.1017 0.6499 0.8227
2.750 0.7692 0.00583 0.00167 -0.1018 0.6422 0.8259
3.000 0.7962 0.00590 0.00171 -0.1018 0.6306 0.8299
3.250 0.8223 0.00601 0.00178 -0.1016 0.6148 0.8337
3.500 0.8476 0.00615 0.00187 -0.1013 0.5979 0.8366
3.750 0.8723 0.00634 0.00200 -0.1008 0.5778 0.8394
4.000 0.8971 0.00654 0.00214 -0.1004 0.5583 0.8421
4.250 0.9212 0.00678 0.00232 -0.0999 0.5381 0.8449
4.750 0.9659 0.00742 0.00276 -0.0983 0.4824 0.8501
5.000 0.9846 0.00792 0.00308 -0.0968 0.4388 0.8528
5.250 1.0022 0.00846 0.00344 -0.0952 0.3921 0.8558
5.500 1.0129 0.00936 0.00398 -0.0924 0.3184 0.8593
5.750 1.0242 0.01017 0.00452 -0.0897 0.2586 0.8627
6.000 1.0329 0.01103 0.00510 -0.0866 0.1986 0.8662
6.250 1.0412 0.01184 0.00568 -0.0834 0.1481 0.8701
6.500 1.0523 0.01246 0.00615 -0.0807 0.1163 0.8739
6.750 1.0638 0.01290 0.00653 -0.0780 0.0997 0.8775
7.000 1.0713 0.01349 0.00705 -0.0746 0.0777 0.8819
7.250 1.0791 0.01411 0.00759 -0.0715 0.0588 0.8871
7.500 1.0915 0.01459 0.00807 -0.0692 0.0511 0.8920
7.750 1.1010 0.01520 0.00868 -0.0666 0.0414 0.8981
8.000 1.1104 0.01589 0.00936 -0.0642 0.0329 0.9050
8.250 1.1205 0.01659 0.01009 -0.0620 0.0267 0.9145
8.500 1.1320 0.01732 0.01088 -0.0603 0.0210 0.9306
8.750 1.1582 0.01822 0.01183 -0.0619 0.0146 0.9648
9.000 1.1705 0.01913 0.01274 -0.0606 0.0107 1.0000
9.250 1.1837 0.02000 0.01361 -0.0593 0.0084 1.0000
9.500 1.1965 0.02090 0.01452 -0.0581 0.0064 1.0000
9.750 1.2084 0.02185 0.01548 -0.0567 0.0050 1.0000
10.000 1.2211 0.02275 0.01641 -0.0554 0.0042 1.0000
10.250 1.2337 0.02367 0.01738 -0.0542 0.0037 1.0000
10.500 1.2465 0.02458 0.01833 -0.0530 0.0034 1.0000
10.750 1.2573 0.02565 0.01944 -0.0516 0.0030 1.0000
11.000 1.2692 0.02664 0.02049 -0.0504 0.0029 1.0000
11.250 1.2794 0.02777 0.02167 -0.0490 0.0027 1.0000
11.500 1.2877 0.02907 0.02304 -0.0475 0.0025 1.0000
11.750 1.2992 0.03015 0.02417 -0.0464 0.0024 1.0000
12.000 1.3088 0.03138 0.02547 -0.0451 0.0024 1.0000
12.250 1.3193 0.03256 0.02671 -0.0440 0.0023 1.0000
12.500 1.3287 0.03386 0.02807 -0.0429 0.0023 1.0000
12.750 1.3388 0.03513 0.02940 -0.0419 0.0021 1.0000
13.000 1.3465 0.03663 0.03098 -0.0407 0.0020 1.0000
13.250 1.3551 0.03810 0.03254 -0.0397 0.0020 1.0000
13.500 1.3625 0.03973 0.03424 -0.0387 0.0019 1.0000
13.750 1.3708 0.04130 0.03589 -0.0378 0.0019 1.0000
14.000 1.3780 0.04303 0.03769 -0.0370 0.0018 1.0000
14.250 1.3833 0.04500 0.03976 -0.0362 0.0018 1.0000
14.500 1.3897 0.04692 0.04175 -0.0355 0.0017 1.0000
14.750 1.3943 0.04907 0.04400 -0.0348 0.0017 1.0000
15.000 1.3994 0.05120 0.04621 -0.0342 0.0016 1.0000
15.250 1.4036 0.05350 0.04861 -0.0338 0.0016 1.0000
15.500 1.4049 0.05619 0.05140 -0.0333 0.0015 1.0000
15.750 1.4074 0.05881 0.05413 -0.0331 0.0015 1.0000
16.000 1.4076 0.06178 0.05720 -0.0329 0.0014 1.0000
16.250 1.4061 0.06505 0.06059 -0.0329 0.0014 1.0000
16.500 1.4046 0.06841 0.06409 -0.0330 0.0014 1.0000
16.750 1.3981 0.07257 0.06839 -0.0334 0.0014 1.0000
17.000 1.3905 0.07703 0.07299 -0.0340 0.0013 1.0000
17.250 1.3893 0.08065 0.07672 -0.0348 0.0013 1.0000
17.500 1.3800 0.08565 0.08187 -0.0359 0.0013 1.0000
17.750 1.3681 0.09122 0.08761 -0.0375 0.0013 1.0000
18.000 1.3622 0.09597 0.09249 -0.0391 0.0013 1.0000
18.250 1.3461 0.10262 0.09931 -0.0415 0.0013 1.0000
18.500 1.3364 0.10836 0.10519 -0.0439 0.0013 1.0000
18.750 1.3239 0.11482 0.11180 -0.0468 0.0013 1.0000
19.000 1.3091 0.12191 0.11905 -0.0502 0.0013 1.0000
19.250 1.3017 0.12769 0.12493 -0.0532 0.0013 1.0000
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Polar data table (+)
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