AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 500,000 Max Cl/Cd: 115.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah63k127-il-500000-n5.txt Download as CSV file: xf-ah63k127-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1415 0.08262 0.07926 -0.0826 0.7543 0.0088
-10.000 -0.1934 0.08627 0.08265 -0.0922 0.7560 0.0086
-9.750 -0.1930 0.08239 0.07881 -0.0939 0.7554 0.0081
-9.500 -0.1925 0.07859 0.07504 -0.0957 0.7547 0.0077
-9.250 -0.1973 0.07366 0.07017 -0.0981 0.7539 0.0073
-9.000 -0.2032 0.06864 0.06520 -0.1010 0.7530 0.0073
-8.750 -0.2453 0.05551 0.05211 -0.1100 0.7514 0.0062
-8.500 -0.2656 0.05098 0.04752 -0.1100 0.7499 0.0063
-8.250 -0.2772 0.04531 0.04170 -0.1098 0.7488 0.0062
-8.000 -0.2847 0.03989 0.03603 -0.1087 0.7478 0.0061
-7.750 -0.2932 0.03422 0.02999 -0.1069 0.7467 0.0062
-7.500 -0.2831 0.03212 0.02769 -0.1061 0.7458 0.0065
-7.250 -0.2750 0.02837 0.02354 -0.1045 0.7449 0.0066
-7.000 -0.2589 0.02631 0.02120 -0.1037 0.7442 0.0068
-6.750 -0.2412 0.02418 0.01876 -0.1028 0.7434 0.0069
-6.500 -0.2206 0.02269 0.01704 -0.1022 0.7424 0.0072
-6.250 -0.1989 0.02122 0.01533 -0.1016 0.7413 0.0074
-6.000 -0.1760 0.01991 0.01381 -0.1011 0.7400 0.0077
-5.750 -0.1518 0.01888 0.01260 -0.1007 0.7387 0.0082
-5.500 -0.1275 0.01766 0.01118 -0.1003 0.7374 0.0083
-5.250 -0.1028 0.01655 0.00990 -0.0998 0.7362 0.0083
-5.000 -0.0778 0.01560 0.00881 -0.0995 0.7351 0.0084
-4.750 -0.0526 0.01480 0.00789 -0.0991 0.7340 0.0085
-4.500 -0.0274 0.01409 0.00709 -0.0988 0.7329 0.0086
-4.250 -0.0018 0.01351 0.00644 -0.0985 0.7320 0.0088
-4.000 0.0241 0.01301 0.00586 -0.0983 0.7311 0.0091
-3.750 0.0502 0.01255 0.00532 -0.0982 0.7302 0.0096
-3.500 0.0760 0.01210 0.00483 -0.0980 0.7287 0.0106
-3.250 0.1025 0.01182 0.00454 -0.0979 0.7268 0.0118
-3.000 0.1294 0.01159 0.00427 -0.0979 0.7250 0.0136
-2.750 0.1564 0.01131 0.00400 -0.0979 0.7233 0.0187
-2.500 0.1834 0.01103 0.00376 -0.0979 0.7217 0.0349
-2.250 0.2097 0.01057 0.00353 -0.0980 0.7202 0.1013
-2.000 0.2352 0.00998 0.00334 -0.0981 0.7189 0.2251
-1.750 0.2582 0.00898 0.00312 -0.0980 0.7176 0.4635
-1.500 0.2803 0.00824 0.00310 -0.0972 0.7164 0.6753
-1.250 0.3063 0.00820 0.00317 -0.0968 0.7138 0.7231
-1.000 0.3332 0.00818 0.00320 -0.0966 0.7115 0.7523
-0.750 0.3604 0.00818 0.00322 -0.0965 0.7094 0.7764
-0.500 0.3882 0.00816 0.00318 -0.0965 0.7076 0.7887
-0.250 0.4161 0.00814 0.00314 -0.0965 0.7059 0.7973
0.000 0.4444 0.00812 0.00308 -0.0966 0.7044 0.8059
0.250 0.4721 0.00812 0.00308 -0.0966 0.7026 0.8138
0.500 0.4992 0.00816 0.00315 -0.0966 0.6994 0.8222
0.750 0.5267 0.00818 0.00318 -0.0966 0.6966 0.8294
1.000 0.5549 0.00816 0.00315 -0.0968 0.6941 0.8343
1.250 0.5828 0.00812 0.00311 -0.0968 0.6919 0.8377
1.500 0.6110 0.00808 0.00306 -0.0970 0.6897 0.8411
1.750 0.6387 0.00812 0.00313 -0.0972 0.6857 0.8446
2.000 0.6668 0.00811 0.00313 -0.0974 0.6821 0.8480
2.250 0.6943 0.00807 0.00311 -0.0974 0.6790 0.8511
2.500 0.7219 0.00805 0.00310 -0.0975 0.6758 0.8550
2.750 0.7494 0.00808 0.00318 -0.0976 0.6709 0.8590
3.000 0.7772 0.00807 0.00317 -0.0977 0.6666 0.8620
3.250 0.8045 0.00804 0.00319 -0.0978 0.6624 0.8645
3.500 0.8314 0.00805 0.00324 -0.0977 0.6551 0.8672
3.750 0.8583 0.00804 0.00323 -0.0976 0.6461 0.8700
4.000 0.8846 0.00804 0.00322 -0.0974 0.6335 0.8732
4.250 0.9104 0.00809 0.00326 -0.0972 0.6195 0.8762
4.500 0.9348 0.00818 0.00332 -0.0966 0.6019 0.8787
4.750 0.9589 0.00831 0.00343 -0.0960 0.5856 0.8816
5.000 0.9815 0.00853 0.00358 -0.0952 0.5638 0.8848
5.250 1.0027 0.00882 0.00380 -0.0941 0.5377 0.8885
5.500 1.0207 0.00922 0.00408 -0.0924 0.5026 0.8921
5.750 1.0368 0.00970 0.00442 -0.0904 0.4655 0.8961
6.000 1.0510 0.01028 0.00484 -0.0882 0.4231 0.9006
6.250 1.0605 0.01101 0.00536 -0.0852 0.3698 0.9057
6.500 1.0634 0.01195 0.00601 -0.0810 0.3063 0.9127
6.750 1.0586 0.01302 0.00678 -0.0756 0.2396 0.9231
7.000 1.0528 0.01411 0.00764 -0.0702 0.1823 0.9414
7.250 1.0629 0.01526 0.00860 -0.0685 0.1359 1.0000
7.500 1.0715 0.01616 0.00940 -0.0662 0.1142 1.0000
7.750 1.0808 0.01711 0.01027 -0.0643 0.0961 1.0000
8.000 1.0913 0.01809 0.01119 -0.0627 0.0802 1.0000
8.250 1.1025 0.01912 0.01216 -0.0613 0.0644 1.0000
8.500 1.1120 0.02025 0.01319 -0.0597 0.0478 1.0000
8.750 1.1217 0.02135 0.01423 -0.0581 0.0355 1.0000
9.000 1.1333 0.02234 0.01523 -0.0568 0.0279 1.0000
9.250 1.1451 0.02333 0.01621 -0.0554 0.0224 1.0000
9.500 1.1551 0.02444 0.01731 -0.0539 0.0165 1.0000
9.750 1.1664 0.02548 0.01837 -0.0526 0.0131 1.0000
10.000 1.1769 0.02660 0.01951 -0.0512 0.0103 1.0000
10.250 1.1870 0.02776 0.02070 -0.0498 0.0083 1.0000
10.500 1.1960 0.02902 0.02201 -0.0483 0.0071 1.0000
10.750 1.2060 0.03023 0.02330 -0.0470 0.0062 1.0000
11.000 1.2167 0.03141 0.02457 -0.0458 0.0058 1.0000
11.250 1.2267 0.03265 0.02585 -0.0446 0.0052 1.0000
11.500 1.2340 0.03415 0.02742 -0.0432 0.0047 1.0000
11.750 1.2413 0.03567 0.02902 -0.0420 0.0043 1.0000
12.000 1.2491 0.03720 0.03064 -0.0408 0.0042 1.0000
12.250 1.2576 0.03870 0.03223 -0.0397 0.0040 1.0000
12.500 1.2647 0.04037 0.03400 -0.0386 0.0039 1.0000
12.750 1.2725 0.04202 0.03574 -0.0377 0.0037 1.0000
13.000 1.2785 0.04390 0.03772 -0.0367 0.0035 1.0000
13.250 1.2849 0.04579 0.03972 -0.0359 0.0034 1.0000
13.500 1.2903 0.04785 0.04187 -0.0351 0.0033 1.0000
13.750 1.2963 0.04988 0.04400 -0.0345 0.0032 1.0000
14.000 1.3014 0.05207 0.04631 -0.0339 0.0031 1.0000
14.250 1.3046 0.05452 0.04888 -0.0333 0.0030 1.0000
14.500 1.3081 0.05701 0.05149 -0.0329 0.0029 1.0000
14.750 1.3104 0.05971 0.05429 -0.0326 0.0029 1.0000
15.000 1.3107 0.06271 0.05742 -0.0324 0.0028 1.0000
15.250 1.3106 0.06586 0.06069 -0.0323 0.0027 1.0000
15.500 1.3045 0.06989 0.06488 -0.0323 0.0026 1.0000
15.750 1.3020 0.07355 0.06869 -0.0326 0.0026 1.0000
16.000 1.2940 0.07809 0.07340 -0.0331 0.0025 1.0000
16.250 1.2911 0.08208 0.07755 -0.0338 0.0025 1.0000
16.500 1.2863 0.08645 0.08208 -0.0348 0.0025 1.0000
16.750 1.2805 0.09111 0.08691 -0.0360 0.0025 1.0000
17.000 1.2740 0.09600 0.09197 -0.0376 0.0024 1.0000
17.250 1.2657 0.10135 0.09748 -0.0395 0.0024 1.0000
17.500 1.2563 0.10706 0.10337 -0.0417 0.0024 1.0000
17.750 1.2451 0.11332 0.10981 -0.0444 0.0024 1.0000
18.000 1.2340 0.11972 0.11637 -0.0475 0.0024 1.0000
18.250 1.2211 0.12674 0.12357 -0.0511 0.0024 1.0000
18.500 1.2079 0.13407 0.13107 -0.0551 0.0024 1.0000
18.750 1.1936 0.14197 0.13913 -0.0597 0.0024 1.0000
19.000 1.1787 0.15037 0.14770 -0.0647 0.0024 1.0000
19.250 1.1649 0.15879 0.15626 -0.0699 0.0024 1.0000
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Polar data table (+)
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