AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 200,000 Max Cl/Cd: 81.84 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah63k127-il-200000-n5.txt Download as CSV file: xf-ah63k127-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2061 0.09700 0.09232 -0.0907 0.7964 0.0218
-10.250 -0.2010 0.09362 0.08895 -0.0916 0.7957 0.0222
-10.000 -0.1993 0.08968 0.08506 -0.0939 0.7949 0.0220
-9.750 -0.1959 0.08621 0.08159 -0.0950 0.7941 0.0223
-9.250 -0.1865 0.07904 0.07447 -0.1004 0.7918 0.0213
-8.750 -0.1989 0.06781 0.06336 -0.1039 0.7892 0.0137
-8.500 -0.2077 0.06231 0.05787 -0.1083 0.7877 0.0137
-8.250 -0.2204 0.05851 0.05404 -0.1094 0.7862 0.0135
-8.000 -0.2298 0.05480 0.05024 -0.1097 0.7847 0.0133
-7.750 -0.2341 0.05103 0.04632 -0.1097 0.7832 0.0131
-7.500 -0.2352 0.04689 0.04197 -0.1093 0.7819 0.0134
-7.250 -0.2319 0.04343 0.03831 -0.1086 0.7803 0.0133
-7.000 -0.2232 0.04011 0.03457 -0.1075 0.7785 0.0141
-6.250 -0.1852 0.03194 0.02536 -0.1045 0.7737 0.0142
-6.000 -0.1678 0.02945 0.02251 -0.1036 0.7722 0.0140
-5.750 -0.1479 0.02734 0.02004 -0.1028 0.7709 0.0139
-5.500 -0.1259 0.02555 0.01790 -0.1021 0.7698 0.0139
-5.250 -0.1032 0.02403 0.01613 -0.1015 0.7680 0.0140
-5.000 -0.0794 0.02275 0.01463 -0.1009 0.7660 0.0141
-4.750 -0.0551 0.02169 0.01338 -0.1004 0.7642 0.0142
-4.500 -0.0315 0.02035 0.01194 -0.0998 0.7623 0.0147
-4.250 -0.0078 0.01940 0.01092 -0.0993 0.7606 0.0152
-4.000 0.0163 0.01871 0.01018 -0.0988 0.7590 0.0162
-3.750 0.0410 0.01819 0.00960 -0.0985 0.7576 0.0179
-3.500 0.0664 0.01786 0.00917 -0.0982 0.7562 0.0206
-3.250 0.0895 0.01732 0.00861 -0.0977 0.7535 0.0236
-3.000 0.1142 0.01696 0.00818 -0.0973 0.7510 0.0280
-2.750 0.1391 0.01653 0.00779 -0.0969 0.7487 0.0454
-2.500 0.1620 0.01572 0.00751 -0.0967 0.7467 0.1698
-2.250 0.1822 0.01457 0.00728 -0.0963 0.7449 0.4167
-2.000 0.1952 0.01386 0.00773 -0.0927 0.7435 0.7263
-1.750 0.2166 0.01405 0.00796 -0.0911 0.7401 0.7705
-1.500 0.2397 0.01421 0.00809 -0.0900 0.7371 0.7953
-1.250 0.2634 0.01436 0.00817 -0.0888 0.7345 0.8190
-1.000 0.2879 0.01445 0.00817 -0.0879 0.7325 0.8336
-0.750 0.3129 0.01449 0.00813 -0.0871 0.7309 0.8444
-0.500 0.3361 0.01457 0.00818 -0.0861 0.7282 0.8547
-0.250 0.3574 0.01468 0.00828 -0.0848 0.7241 0.8660
0.000 0.3812 0.01470 0.00826 -0.0839 0.7213 0.8764
0.250 0.4063 0.01464 0.00817 -0.0833 0.7192 0.8827
0.500 0.4339 0.01458 0.00803 -0.0833 0.7175 0.8884
0.750 0.4572 0.01463 0.00810 -0.0826 0.7136 0.8931
1.000 0.4812 0.01467 0.00814 -0.0821 0.7096 0.8981
1.250 0.5080 0.01463 0.00807 -0.0821 0.7070 0.9033
1.500 0.5346 0.01451 0.00795 -0.0818 0.7050 0.9078
2.000 0.5826 0.01456 0.00806 -0.0808 0.6973 0.9194
2.250 0.6088 0.01448 0.00800 -0.0806 0.6942 0.9242
2.500 0.6369 0.01435 0.00787 -0.0807 0.6920 0.9290
2.750 0.6663 0.01419 0.00773 -0.0811 0.6903 0.9333
3.000 0.6885 0.01438 0.00801 -0.0805 0.6837 0.9393
3.250 0.7164 0.01428 0.00796 -0.0807 0.6805 0.9446
3.500 0.7473 0.01412 0.00783 -0.0814 0.6782 0.9491
3.750 0.7750 0.01418 0.00800 -0.0817 0.6733 0.9552
4.000 0.8048 0.01418 0.00808 -0.0825 0.6686 0.9610
4.250 0.8383 0.01405 0.00801 -0.0838 0.6656 0.9666
4.500 0.8713 0.01400 0.00807 -0.0852 0.6614 0.9743
4.750 0.9034 0.01396 0.00814 -0.0864 0.6540 0.9880
5.000 0.9319 0.01373 0.00797 -0.0867 0.6452 1.0000
5.250 0.9605 0.01339 0.00766 -0.0867 0.6355 1.0000
5.500 0.9870 0.01323 0.00757 -0.0865 0.6232 1.0000
5.750 1.0135 0.01311 0.00747 -0.0863 0.6094 1.0000
6.000 1.0387 0.01305 0.00743 -0.0858 0.5912 1.0000
6.250 1.0632 0.01303 0.00733 -0.0852 0.5664 1.0000
6.500 1.0836 0.01324 0.00743 -0.0838 0.5328 1.0000
6.750 1.1005 0.01365 0.00771 -0.0821 0.4965 1.0000
7.000 1.1136 0.01423 0.00814 -0.0797 0.4565 1.0000
7.250 1.1191 0.01507 0.00875 -0.0763 0.4049 1.0000
7.500 1.1112 0.01627 0.00961 -0.0708 0.3420 1.0000
7.750 1.0976 0.01794 0.01090 -0.0651 0.2768 1.0000
8.000 1.0856 0.01997 0.01256 -0.0607 0.2153 1.0000
8.250 1.0809 0.02194 0.01426 -0.0577 0.1677 1.0000
8.500 1.0825 0.02360 0.01574 -0.0554 0.1359 1.0000
8.750 1.0880 0.02503 0.01708 -0.0535 0.1136 1.0000
9.000 1.0942 0.02644 0.01840 -0.0518 0.0946 1.0000
9.250 1.1022 0.02775 0.01970 -0.0502 0.0779 1.0000
9.500 1.1102 0.02909 0.02100 -0.0487 0.0620 1.0000
9.750 1.1174 0.03051 0.02237 -0.0472 0.0484 1.0000
10.000 1.1248 0.03195 0.02379 -0.0457 0.0379 1.0000
10.250 1.1316 0.03348 0.02532 -0.0442 0.0292 1.0000
10.500 1.1377 0.03512 0.02695 -0.0427 0.0234 1.0000
10.750 1.1450 0.03669 0.02855 -0.0414 0.0183 1.0000
11.000 1.1507 0.03844 0.03037 -0.0400 0.0159 1.0000
11.250 1.1589 0.04002 0.03206 -0.0389 0.0138 1.0000
11.500 1.1651 0.04181 0.03394 -0.0377 0.0123 1.0000
11.750 1.1675 0.04401 0.03626 -0.0363 0.0112 1.0000
12.000 1.1720 0.04610 0.03848 -0.0352 0.0105 1.0000
12.250 1.1774 0.04816 0.04068 -0.0341 0.0101 1.0000
12.500 1.1829 0.05028 0.04294 -0.0332 0.0096 1.0000
12.750 1.1881 0.05250 0.04529 -0.0323 0.0092 1.0000
13.000 1.1937 0.05474 0.04767 -0.0314 0.0087 1.0000
13.250 1.1995 0.05702 0.05008 -0.0307 0.0084 1.0000
13.500 1.2048 0.05937 0.05254 -0.0302 0.0080 1.0000
13.750 1.2096 0.06182 0.05512 -0.0298 0.0077 1.0000
14.000 1.2114 0.06470 0.05812 -0.0295 0.0073 1.0000
14.250 1.2127 0.06786 0.06144 -0.0290 0.0070 1.0000
14.500 1.2158 0.07074 0.06454 -0.0289 0.0067 1.0000
14.750 1.2169 0.07400 0.06801 -0.0289 0.0065 1.0000
15.000 1.2159 0.07765 0.07193 -0.0290 0.0063 1.0000
15.250 1.2127 0.08168 0.07619 -0.0294 0.0062 1.0000
15.500 1.2070 0.08620 0.08095 -0.0302 0.0061 1.0000
15.750 1.1998 0.09105 0.08603 -0.0313 0.0060 1.0000
16.000 1.1904 0.09641 0.09164 -0.0328 0.0060 1.0000
16.250 1.1791 0.10229 0.09776 -0.0348 0.0059 1.0000
16.500 1.1662 0.10865 0.10435 -0.0374 0.0059 1.0000
16.750 1.1516 0.11563 0.11155 -0.0406 0.0059 1.0000
17.000 1.1362 0.12314 0.11928 -0.0445 0.0059 1.0000
17.250 1.1195 0.13134 0.12769 -0.0491 0.0060 1.0000
17.500 1.1017 0.14038 0.13693 -0.0546 0.0060 1.0000
17.750 1.0819 0.15071 0.14744 -0.0610 0.0061 1.0000
18.000 1.0612 0.16236 0.15924 -0.0684 0.0062 1.0000
18.250 1.0340 0.17783 0.17479 -0.0775 0.0065 1.0000
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