AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 200,000 Max Cl/Cd: 83.15 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah63k127-il-200000.txt Download as CSV file: xf-ah63k127-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1605 0.09141 0.08740 -0.1009 0.8779 0.0404
-9.750 -0.1646 0.08781 0.08386 -0.1061 0.8761 0.0421
-9.500 -0.1653 0.08419 0.08028 -0.1096 0.8743 0.0423
-9.250 -0.1684 0.08002 0.07615 -0.1140 0.8719 0.0426
-9.000 -0.1774 0.07568 0.07180 -0.1184 0.8693 0.0427
-8.750 -0.1851 0.07262 0.06870 -0.1197 0.8671 0.0427
-8.500 -0.1592 0.06907 0.06527 -0.1147 0.8670 0.0457
-8.250 -0.1632 0.06545 0.06165 -0.1173 0.8647 0.0464
-8.000 -0.1721 0.06254 0.05874 -0.1181 0.8624 0.0471
-7.750 -0.1762 0.05963 0.05581 -0.1188 0.8603 0.0484
-7.500 -0.1790 0.05660 0.05270 -0.1195 0.8579 0.0508
-7.250 -0.1803 0.05354 0.04947 -0.1200 0.8553 0.0531
-7.000 -0.1893 0.05182 0.04713 -0.1191 0.8526 0.0559
-6.750 -0.1765 0.04690 0.04241 -0.1195 0.8510 0.0581
-6.500 -0.1617 0.04548 0.04100 -0.1190 0.8491 0.0640
-6.250 -0.1576 0.04272 0.03783 -0.1182 0.8466 0.0710
-6.000 -0.1410 0.04073 0.03592 -0.1178 0.8443 0.0746
-5.750 -0.1298 0.03882 0.03356 -0.1168 0.8416 0.0848
-5.500 -0.1109 0.03667 0.03145 -0.1164 0.8395 0.0888
-5.250 -0.0943 0.03491 0.02940 -0.1157 0.8373 0.1005
-5.000 -0.0682 0.02828 0.02147 -0.1122 0.8350 0.0452
-4.750 -0.0457 0.02616 0.01912 -0.1109 0.8323 0.0374
-4.500 -0.0217 0.02419 0.01664 -0.1095 0.8294 0.0327
-4.250 0.0035 0.02342 0.01567 -0.1087 0.8267 0.0317
-4.000 0.0290 0.02232 0.01443 -0.1081 0.8244 0.0316
-3.750 0.0536 0.02103 0.01307 -0.1073 0.8223 0.0328
-3.500 0.0716 0.02048 0.01254 -0.1060 0.8183 0.0346
-3.250 0.0929 0.02018 0.01225 -0.1051 0.8147 0.0396
-3.000 0.1159 0.01962 0.01164 -0.1043 0.8116 0.0449
-2.750 0.1408 0.01908 0.01108 -0.1037 0.8092 0.0625
-2.500 0.1432 0.01696 0.01108 -0.1010 0.8040 0.5368
-2.250 0.1532 0.01704 0.01188 -0.0962 0.7999 0.7585
-2.000 0.1689 0.01766 0.01249 -0.0922 0.7970 0.8211
-1.750 0.1728 0.01842 0.01328 -0.0864 0.7916 0.8576
-1.500 0.1835 0.01877 0.01359 -0.0822 0.7870 0.8800
-1.250 0.2019 0.01891 0.01363 -0.0793 0.7842 0.8981
-1.000 0.2064 0.01929 0.01401 -0.0747 0.7778 0.9180
-0.750 0.2266 0.01938 0.01401 -0.0725 0.7737 0.9361
-0.500 0.2628 0.01939 0.01390 -0.0736 0.7715 0.9482
-0.250 0.3067 0.01946 0.01384 -0.0764 0.7700 0.9582
0.000 0.3573 0.01985 0.01417 -0.0819 0.7639 0.9668
0.250 0.4019 0.01994 0.01418 -0.0856 0.7609 0.9730
0.500 0.4474 0.01992 0.01408 -0.0893 0.7587 0.9757
0.750 0.4893 0.01992 0.01399 -0.0922 0.7569 0.9790
1.000 0.5159 0.02035 0.01446 -0.0935 0.7493 0.9857
1.250 0.5557 0.02034 0.01441 -0.0962 0.7464 0.9888
1.500 0.5944 0.02027 0.01430 -0.0985 0.7443 0.9920
1.750 0.6241 0.02068 0.01475 -0.1003 0.7375 0.9977
2.000 0.6531 0.02072 0.01479 -0.1010 0.7337 1.0000
2.250 0.6756 0.02065 0.01472 -0.1000 0.7311 1.0000
2.500 0.6715 0.02122 0.01534 -0.0952 0.7223 1.0000
2.750 0.6910 0.02116 0.01527 -0.0938 0.7191 1.0000
3.000 0.7162 0.02097 0.01508 -0.0931 0.7172 1.0000
3.250 0.7061 0.02155 0.01572 -0.0873 0.7072 1.0000
3.500 0.7337 0.02135 0.01552 -0.0871 0.7050 1.0000
3.750 0.7649 0.02108 0.01530 -0.0875 0.7036 1.0000
4.000 0.7722 0.02172 0.01600 -0.0851 0.6936 1.0000
4.250 0.8053 0.02143 0.01574 -0.0859 0.6918 1.0000
4.500 0.8391 0.02109 0.01545 -0.0867 0.6904 1.0000
4.750 0.8520 0.02171 0.01619 -0.0852 0.6806 1.0000
5.000 0.8912 0.02075 0.01528 -0.0863 0.6786 1.0000
5.250 0.9168 0.02035 0.01496 -0.0858 0.6705 1.0000
5.500 0.9567 0.01898 0.01367 -0.0868 0.6669 1.0000
5.750 0.9984 0.01757 0.01235 -0.0881 0.6642 1.0000
6.000 1.0232 0.01712 0.01201 -0.0873 0.6542 1.0000
6.250 1.0565 0.01610 0.01108 -0.0875 0.6454 1.0000
6.500 1.0879 0.01518 0.01024 -0.0874 0.6328 1.0000
6.750 1.1151 0.01468 0.00985 -0.0869 0.6169 1.0000
7.000 1.1432 0.01424 0.00945 -0.0865 0.5976 1.0000
7.250 1.1665 0.01410 0.00929 -0.0853 0.5706 1.0000
7.500 1.1841 0.01424 0.00931 -0.0832 0.5302 1.0000
7.750 1.1923 0.01481 0.00963 -0.0797 0.4738 1.0000
8.000 1.1850 0.01590 0.01033 -0.0739 0.4019 1.0000
8.250 1.1647 0.01758 0.01154 -0.0668 0.3262 1.0000
8.500 1.1419 0.01998 0.01345 -0.0609 0.2516 1.0000
8.750 1.1254 0.02265 0.01568 -0.0567 0.1894 1.0000
9.000 1.1176 0.02491 0.01768 -0.0535 0.1489 1.0000
9.250 1.1157 0.02686 0.01944 -0.0510 0.1215 1.0000
9.500 1.1171 0.02865 0.02113 -0.0488 0.0979 1.0000
9.750 1.1184 0.03051 0.02288 -0.0467 0.0769 1.0000
10.000 1.1195 0.03246 0.02471 -0.0446 0.0589 1.0000
10.250 1.1183 0.03466 0.02682 -0.0424 0.0453 1.0000
10.500 1.1225 0.03653 0.02873 -0.0407 0.0369 1.0000
10.750 1.1247 0.03862 0.03086 -0.0388 0.0302 1.0000
11.000 1.1303 0.04048 0.03276 -0.0374 0.0267 1.0000
11.250 1.1330 0.04293 0.03521 -0.0352 0.0242 1.0000
11.500 1.1464 0.04445 0.03687 -0.0340 0.0225 1.0000
11.750 1.1623 0.04603 0.03858 -0.0328 0.0209 1.0000
12.000 1.1806 0.04769 0.04039 -0.0317 0.0197 1.0000
12.250 1.2006 0.04953 0.04238 -0.0308 0.0190 1.0000
12.500 1.2165 0.05162 0.04460 -0.0300 0.0181 1.0000
12.750 1.2350 0.05612 0.04942 -0.0292 0.0166 1.0000
13.000 1.2356 0.05875 0.05233 -0.0280 0.0163 1.0000
13.250 1.2359 0.06229 0.05617 -0.0268 0.0163 1.0000
13.500 1.2309 0.06627 0.06045 -0.0257 0.0163 1.0000
13.750 1.2226 0.07058 0.06504 -0.0248 0.0163 1.0000
14.000 1.2102 0.07522 0.06996 -0.0242 0.0164 1.0000
14.250 1.1950 0.08066 0.07566 -0.0240 0.0165 1.0000
14.500 1.1798 0.08663 0.08189 -0.0242 0.0168 1.0000
14.750 1.1684 0.09083 0.08628 -0.0247 0.0169 1.0000
15.000 1.1540 0.09578 0.09143 -0.0258 0.0170 1.0000
15.250 1.1408 0.10079 0.09663 -0.0274 0.0171 1.0000
15.500 1.1246 0.10666 0.10271 -0.0298 0.0172 1.0000
15.750 1.1074 0.11320 0.10948 -0.0329 0.0175 1.0000
16.000 1.0787 0.12290 0.11946 -0.0382 0.0181 1.0000
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Polar data table (+)
Polar graphs
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