AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 100,000 Max Cl/Cd: 44.82 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah63k127-il-100000-n5.txt Download as CSV file: xf-ah63k127-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2148 0.10176 0.09628 -0.0900 0.8558 0.0550
-10.000 -0.2136 0.09819 0.09274 -0.0935 0.8541 0.0552
-9.750 -0.2173 0.09428 0.08891 -0.0983 0.8523 0.0555
-9.250 -0.1387 0.07150 0.06641 -0.0968 0.8440 0.0423
-9.000 -0.1382 0.06484 0.05973 -0.0981 0.8427 0.0304
-8.750 -0.1358 0.06119 0.05610 -0.0986 0.8411 0.0295
-8.500 -0.1945 0.06909 0.06371 -0.1087 0.8435 0.0298
-8.250 -0.1980 0.06551 0.06014 -0.1103 0.8414 0.0290
-8.000 -0.2049 0.06212 0.05669 -0.1113 0.8391 0.0283
-7.750 -0.2081 0.05848 0.05295 -0.1123 0.8368 0.0275
-7.500 -0.2102 0.05482 0.04916 -0.1129 0.8345 0.0266
-7.250 -0.2100 0.05125 0.04541 -0.1129 0.8322 0.0257
-7.000 -0.2079 0.04750 0.04138 -0.1124 0.8297 0.0248
-6.750 -0.2023 0.04377 0.03729 -0.1116 0.8272 0.0238
-6.500 -0.1938 0.03996 0.03292 -0.1104 0.8249 0.0228
-6.250 -0.1792 0.03718 0.02964 -0.1093 0.8230 0.0223
-6.000 -0.1626 0.03489 0.02694 -0.1083 0.8209 0.0221
-5.750 -0.1450 0.03291 0.02459 -0.1073 0.8183 0.0220
-5.500 -0.1254 0.03103 0.02237 -0.1064 0.8159 0.0221
-5.250 -0.1039 0.02935 0.02038 -0.1057 0.8136 0.0224
-5.000 -0.0808 0.02788 0.01866 -0.1051 0.8114 0.0229
-4.750 -0.0568 0.02680 0.01736 -0.1047 0.8095 0.0245
-4.500 -0.0338 0.02601 0.01642 -0.1041 0.8072 0.0271
-4.250 -0.0121 0.02523 0.01551 -0.1031 0.8042 0.0290
-4.000 0.0104 0.02443 0.01459 -0.1022 0.8014 0.0303
-3.750 0.0323 0.02352 0.01361 -0.1013 0.7989 0.0322
-3.500 0.0556 0.02288 0.01290 -0.1006 0.7967 0.0355
-3.250 0.0771 0.02257 0.01248 -0.0997 0.7937 0.0431
-3.000 0.0966 0.02217 0.01206 -0.0985 0.7900 0.0553
-2.750 0.1157 0.02120 0.01170 -0.0975 0.7869 0.1604
-2.500 0.1290 0.01968 0.01164 -0.0957 0.7843 0.4965
-2.250 0.1316 0.01987 0.01277 -0.0884 0.7810 0.7652
-2.000 0.1414 0.02043 0.01329 -0.0841 0.7762 0.8191
-1.750 0.1580 0.02075 0.01346 -0.0811 0.7730 0.8489
-1.500 0.1775 0.02095 0.01350 -0.0784 0.7705 0.8750
-1.250 0.1925 0.02121 0.01369 -0.0757 0.7658 0.8945
-1.000 0.2144 0.02137 0.01373 -0.0744 0.7616 0.9124
-0.750 0.2450 0.02143 0.01363 -0.0746 0.7590 0.9298
-0.500 0.2844 0.02147 0.01350 -0.0767 0.7571 0.9415
-0.250 0.3108 0.02175 0.01370 -0.0774 0.7518 0.9503
0.000 0.3406 0.02190 0.01375 -0.0784 0.7478 0.9577
0.250 0.3782 0.02195 0.01369 -0.0806 0.7453 0.9622
0.500 0.4157 0.02199 0.01362 -0.0828 0.7434 0.9668
0.750 0.4405 0.02242 0.01405 -0.0836 0.7364 0.9748
1.000 0.4769 0.02251 0.01409 -0.0858 0.7332 0.9799
1.250 0.5134 0.02255 0.01408 -0.0879 0.7309 0.9853
1.500 0.5418 0.02297 0.01453 -0.0894 0.7246 0.9937
1.750 0.5670 0.02316 0.01471 -0.0896 0.7203 1.0000
2.000 0.5862 0.02318 0.01470 -0.0882 0.7174 1.0000
2.250 0.5773 0.02378 0.01533 -0.0827 0.7082 1.0000
2.500 0.5988 0.02382 0.01535 -0.0817 0.7050 1.0000
2.750 0.6042 0.02439 0.01593 -0.0788 0.6970 1.0000
3.000 0.6279 0.02450 0.01607 -0.0784 0.6930 1.0000
3.250 0.6572 0.02446 0.01604 -0.0787 0.6907 1.0000
3.500 0.6646 0.02520 0.01683 -0.0765 0.6813 1.0000
3.750 0.6938 0.02518 0.01684 -0.0768 0.6785 1.0000
4.250 0.7321 0.02594 0.01774 -0.0752 0.6663 1.0000
4.500 0.7634 0.02581 0.01767 -0.0757 0.6641 1.0000
5.000 0.8015 0.02660 0.01862 -0.0740 0.6515 1.0000
5.500 0.8382 0.02740 0.01964 -0.0719 0.6389 1.0000
5.750 0.8598 0.02766 0.02000 -0.0712 0.6336 1.0000
6.250 0.9169 0.02681 0.01946 -0.0706 0.6231 1.0000
6.500 0.9339 0.02665 0.01941 -0.0688 0.6110 1.0000
6.750 0.9567 0.02609 0.01896 -0.0674 0.5984 1.0000
7.000 0.9806 0.02556 0.01856 -0.0662 0.5849 1.0000
7.250 1.0075 0.02484 0.01796 -0.0653 0.5694 1.0000
7.500 1.0323 0.02441 0.01768 -0.0642 0.5511 1.0000
7.750 1.0523 0.02436 0.01772 -0.0627 0.5283 1.0000
8.000 1.0748 0.02407 0.01743 -0.0612 0.4953 1.0000
8.250 1.0901 0.02432 0.01757 -0.0592 0.4483 1.0000
8.500 1.0975 0.02513 0.01802 -0.0564 0.3743 1.0000
8.750 1.0892 0.02712 0.01938 -0.0525 0.2837 1.0000
9.000 1.0779 0.02963 0.02137 -0.0491 0.2131 1.0000
9.250 1.0735 0.03186 0.02328 -0.0465 0.1685 1.0000
9.500 1.0736 0.03386 0.02514 -0.0444 0.1380 1.0000
9.750 1.0765 0.03572 0.02689 -0.0426 0.1144 1.0000
10.000 1.0800 0.03756 0.02865 -0.0410 0.0951 1.0000
10.250 1.0852 0.03934 0.03041 -0.0395 0.0778 1.0000
10.500 1.0906 0.04114 0.03219 -0.0382 0.0629 1.0000
10.750 1.0955 0.04304 0.03407 -0.0368 0.0508 1.0000
11.000 1.0997 0.04507 0.03607 -0.0354 0.0421 1.0000
11.250 1.1048 0.04708 0.03815 -0.0342 0.0360 1.0000
11.500 1.1090 0.04926 0.04040 -0.0329 0.0313 1.0000
11.750 1.1160 0.05121 0.04245 -0.0319 0.0270 1.0000
12.000 1.1187 0.05368 0.04493 -0.0308 0.0242 1.0000
12.250 1.1282 0.05568 0.04718 -0.0296 0.0224 1.0000
12.500 1.1379 0.05773 0.04941 -0.0287 0.0206 1.0000
12.750 1.1451 0.05994 0.05175 -0.0280 0.0187 1.0000
13.000 1.1492 0.06252 0.05439 -0.0275 0.0172 1.0000
13.250 1.1574 0.06506 0.05712 -0.0267 0.0162 1.0000
13.500 1.1661 0.06773 0.06006 -0.0259 0.0154 1.0000
13.750 1.1721 0.07073 0.06335 -0.0253 0.0150 1.0000
14.000 1.1744 0.07421 0.06712 -0.0248 0.0145 1.0000
14.250 1.1728 0.07813 0.07134 -0.0246 0.0142 1.0000
14.500 1.1675 0.08248 0.07599 -0.0248 0.0139 1.0000
14.750 1.1592 0.08725 0.08105 -0.0253 0.0138 1.0000
15.000 1.1478 0.09257 0.08665 -0.0263 0.0137 1.0000
15.250 1.1345 0.09836 0.09272 -0.0280 0.0136 1.0000
15.500 1.1189 0.10477 0.09939 -0.0303 0.0136 1.0000
15.750 1.1017 0.11177 0.10664 -0.0334 0.0137 1.0000
16.000 1.0828 0.11957 0.11468 -0.0373 0.0138 1.0000
16.250 1.0622 0.12834 0.12367 -0.0423 0.0139 1.0000
16.500 1.0403 0.13828 0.13379 -0.0485 0.0141 1.0000
16.750 1.0164 0.15010 0.14575 -0.0561 0.0145 1.0000
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Polar data table (+)
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