AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 100,000 Max Cl/Cd: 67.1 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah6407-il-100000-n5.txt Download as CSV file: xf-ah6407-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-6-40-7 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2596 0.09208 0.08797 -0.0215 1.0000 0.0387
-7.250 -0.2549 0.08882 0.08473 -0.0225 0.9977 0.0394
-7.000 -0.3376 0.09943 0.09504 -0.0223 1.0000 0.0365
-6.750 -0.3367 0.09677 0.09243 -0.0202 1.0000 0.0373
-6.500 -0.3375 0.09453 0.09024 -0.0193 1.0000 0.0378
-6.250 -0.3266 0.09133 0.08706 -0.0215 0.9979 0.0386
-6.000 -0.3029 0.08717 0.08288 -0.0271 0.9934 0.0398
-5.750 -0.2768 0.08291 0.07859 -0.0336 0.9886 0.0411
-5.500 -0.2484 0.07850 0.07413 -0.0408 0.9835 0.0421
-5.250 -0.2153 0.07361 0.06920 -0.0491 0.9791 0.0417
-4.750 -0.1149 0.06002 0.05529 -0.0765 0.9700 0.0346
-4.500 -0.0818 0.05519 0.05037 -0.0824 0.9652 0.0337
-4.250 -0.0311 0.04895 0.04392 -0.0931 0.9621 0.0335
-4.000 0.0260 0.04246 0.03713 -0.1049 0.9603 0.0372
-3.750 0.0734 0.03751 0.03185 -0.1125 0.9566 0.0385
-3.500 0.1241 0.03277 0.02662 -0.1200 0.9539 0.0422
-3.250 0.1795 0.02760 0.02051 -0.1276 0.9525 0.0462
-3.000 0.2247 0.02486 0.01714 -0.1322 0.9505 0.0511
-2.750 0.2627 0.02332 0.01523 -0.1347 0.9466 0.0544
-2.500 0.3007 0.02192 0.01342 -0.1368 0.9422 0.0570
-2.250 0.3414 0.02099 0.01209 -0.1394 0.9389 0.0624
-2.000 0.3776 0.01994 0.01086 -0.1410 0.9325 0.0639
-1.750 0.4188 0.01896 0.00981 -0.1435 0.9271 0.0666
-1.500 0.4534 0.01830 0.00908 -0.1446 0.9182 0.0702
-1.250 0.4934 0.01761 0.00828 -0.1466 0.9122 0.0760
-1.000 0.5244 0.01717 0.00785 -0.1470 0.9020 0.0848
-0.750 0.5579 0.01668 0.00745 -0.1479 0.8934 0.1133
-0.500 0.5919 0.01619 0.00715 -0.1488 0.8847 0.1897
-0.250 0.6217 0.01592 0.00698 -0.1489 0.8737 0.2514
0.000 0.6526 0.01546 0.00685 -0.1494 0.8631 0.3628
0.250 0.6738 0.01400 0.00660 -0.1473 0.8516 1.0000
0.500 0.7042 0.01393 0.00633 -0.1473 0.8393 1.0000
0.750 0.7334 0.01390 0.00614 -0.1470 0.8252 1.0000
1.000 0.7621 0.01389 0.00600 -0.1467 0.8101 1.0000
1.250 0.7899 0.01391 0.00591 -0.1463 0.7930 1.0000
1.500 0.8178 0.01393 0.00584 -0.1459 0.7748 1.0000
1.750 0.8458 0.01397 0.00578 -0.1455 0.7556 1.0000
2.000 0.8736 0.01403 0.00573 -0.1450 0.7347 1.0000
2.250 0.9009 0.01413 0.00573 -0.1445 0.7111 1.0000
2.500 0.9278 0.01427 0.00578 -0.1439 0.6851 1.0000
2.750 0.9543 0.01445 0.00584 -0.1432 0.6565 1.0000
3.000 0.9802 0.01470 0.00594 -0.1425 0.6256 1.0000
3.250 1.0056 0.01500 0.00612 -0.1417 0.5938 1.0000
3.500 1.0306 0.01536 0.00633 -0.1409 0.5625 1.0000
3.750 1.0551 0.01578 0.00660 -0.1401 0.5320 1.0000
4.000 1.0793 0.01623 0.00692 -0.1393 0.5035 1.0000
4.250 1.1034 0.01671 0.00732 -0.1385 0.4783 1.0000
4.500 1.1275 0.01721 0.00774 -0.1378 0.4569 1.0000
4.750 1.1517 0.01772 0.00819 -0.1371 0.4387 1.0000
5.000 1.1760 0.01822 0.00869 -0.1364 0.4219 1.0000
5.250 1.2002 0.01875 0.00924 -0.1357 0.4068 1.0000
5.500 1.2243 0.01929 0.00980 -0.1351 0.3935 1.0000
5.750 1.2486 0.01983 0.01040 -0.1344 0.3817 1.0000
6.000 1.2729 0.02037 0.01103 -0.1338 0.3701 1.0000
6.250 1.2966 0.02093 0.01171 -0.1331 0.3578 1.0000
6.500 1.3196 0.02150 0.01236 -0.1323 0.3445 1.0000
6.750 1.3423 0.02208 0.01304 -0.1314 0.3315 1.0000
7.000 1.3631 0.02262 0.01368 -0.1302 0.3127 1.0000
7.250 1.3808 0.02318 0.01425 -0.1286 0.2835 1.0000
7.500 1.3970 0.02387 0.01491 -0.1268 0.2476 1.0000
7.750 1.4137 0.02469 0.01567 -0.1251 0.2053 1.0000
8.000 1.4232 0.02634 0.01679 -0.1227 0.1209 1.0000
8.250 1.4263 0.02901 0.01889 -0.1195 0.0548 1.0000
8.500 1.4334 0.03109 0.02089 -0.1165 0.0353 1.0000
8.750 1.4419 0.03281 0.02272 -0.1137 0.0285 1.0000
9.250 1.4494 0.03634 0.02659 -0.1068 0.0238 1.0000
9.500 1.4504 0.03813 0.02861 -0.1031 0.0225 1.0000
9.750 1.4504 0.04008 0.03078 -0.0997 0.0212 1.0000
10.000 1.4497 0.04220 0.03315 -0.0965 0.0198 1.0000
10.250 1.4476 0.04454 0.03566 -0.0936 0.0187 1.0000
10.500 1.4436 0.04719 0.03848 -0.0909 0.0178 1.0000
10.750 1.4384 0.05013 0.04158 -0.0884 0.0173 1.0000
11.000 1.4334 0.05329 0.04488 -0.0861 0.0168 1.0000
11.250 1.4294 0.05660 0.04834 -0.0839 0.0164 1.0000
11.500 1.4291 0.05984 0.05169 -0.0819 0.0160 1.0000
11.750 1.4313 0.06280 0.05487 -0.0803 0.0158 1.0000
12.000 1.4322 0.06594 0.05824 -0.0790 0.0154 1.0000
12.250 1.4314 0.06931 0.06187 -0.0779 0.0150 1.0000
12.500 1.4286 0.07298 0.06579 -0.0771 0.0146 1.0000
12.750 1.4235 0.07697 0.07004 -0.0767 0.0141 1.0000
13.000 1.4169 0.08131 0.07463 -0.0767 0.0138 1.0000
13.250 1.4085 0.08601 0.07958 -0.0771 0.0135 1.0000
13.500 1.3985 0.09110 0.08492 -0.0780 0.0133 1.0000
13.750 1.3871 0.09663 0.09070 -0.0795 0.0132 1.0000
14.000 1.3747 0.10265 0.09696 -0.0816 0.0132 1.0000
14.250 1.3612 0.10915 0.10371 -0.0844 0.0132 1.0000
14.500 1.3469 0.11618 0.11097 -0.0880 0.0132 1.0000
14.750 1.3322 0.12374 0.11876 -0.0923 0.0132 1.0000
15.000 1.3171 0.13185 0.12708 -0.0973 0.0133 1.0000
15.250 1.3015 0.14061 0.13604 -0.1030 0.0134 1.0000
15.500 1.2855 0.15005 0.14566 -0.1093 0.0136 1.0000
15.750 1.2692 0.16025 0.15601 -0.1163 0.0138 1.0000
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Polar data table (+)
Polar graphs
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