AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 50,000 Max Cl/Cd: 31.52 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100c-il-50000-n5.txt Download as CSV file: xf-ah79100c-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2639 0.11570 0.10941 -0.0454 0.9656 0.0951
-6.750 -0.2667 0.11404 0.10780 -0.0464 0.9585 0.0979
-6.500 -0.2710 0.11299 0.10680 -0.0501 0.9509 0.0998
-6.250 -0.2672 0.11081 0.10466 -0.0564 0.9429 0.1005
-6.000 -0.2577 0.10667 0.10055 -0.0565 0.9383 0.1014
-5.750 -0.2470 0.10289 0.09677 -0.0536 0.9342 0.1037
-5.500 -0.2330 0.09973 0.09360 -0.0550 0.9298 0.1086
-5.250 -0.2249 0.09740 0.09127 -0.0652 0.9203 0.1154
-5.000 -0.2122 0.09331 0.08720 -0.0641 0.9168 0.1178
-4.750 -0.2017 0.09036 0.08425 -0.0638 0.9117 0.1211
-4.500 -0.1684 0.08145 0.07508 -0.0784 0.9052 0.0704
-4.250 -0.1436 0.07710 0.07065 -0.0826 0.9017 0.0672
-4.000 -0.1219 0.07290 0.06635 -0.0880 0.8956 0.0674
-3.750 -0.0854 0.06769 0.06094 -0.0966 0.8914 0.0675
-3.500 -0.0367 0.06155 0.05449 -0.1074 0.8887 0.0659
-3.250 0.0241 0.05519 0.04756 -0.1203 0.8870 0.0689
-3.000 0.0723 0.05032 0.04206 -0.1287 0.8835 0.0693
-2.750 0.1263 0.04601 0.03677 -0.1369 0.8807 0.0720
-2.500 0.1595 0.04442 0.03505 -0.1394 0.8770 0.0759
-2.250 0.2034 0.04228 0.03235 -0.1436 0.8745 0.0786
-2.000 0.2476 0.04057 0.02998 -0.1473 0.8723 0.0839
-1.750 0.2695 0.03990 0.02908 -0.1471 0.8659 0.0887
-1.500 0.3025 0.03910 0.02803 -0.1485 0.8618 0.0949
-1.250 0.3393 0.03839 0.02708 -0.1503 0.8587 0.1055
-1.000 0.3635 0.03816 0.02662 -0.1501 0.8528 0.1166
-0.750 0.3929 0.03789 0.02626 -0.1507 0.8477 0.1327
-0.500 0.4291 0.03752 0.02582 -0.1524 0.8442 0.1603
-0.250 0.4546 0.03743 0.02578 -0.1525 0.8383 0.1957
0.000 0.4846 0.03720 0.02583 -0.1535 0.8329 0.2691
0.250 0.5211 0.03668 0.02587 -0.1555 0.8295 0.4234
0.500 0.5331 0.03602 0.02626 -0.1523 0.8229 0.7190
0.750 0.5537 0.03593 0.02603 -0.1508 0.8160 1.0000
1.000 0.5857 0.03630 0.02605 -0.1517 0.8111 1.0000
1.250 0.6061 0.03695 0.02648 -0.1510 0.8029 1.0000
1.500 0.6415 0.03717 0.02646 -0.1524 0.7987 1.0000
1.750 0.6587 0.03794 0.02708 -0.1512 0.7897 1.0000
2.000 0.6918 0.03818 0.02715 -0.1522 0.7846 1.0000
2.250 0.7117 0.03887 0.02774 -0.1514 0.7761 1.0000
2.500 0.7423 0.03915 0.02790 -0.1519 0.7702 1.0000
2.750 0.7643 0.03977 0.02845 -0.1514 0.7620 1.0000
3.000 0.7928 0.04010 0.02871 -0.1516 0.7554 1.0000
3.250 0.8156 0.04067 0.02926 -0.1511 0.7473 1.0000
3.500 0.8432 0.04100 0.02955 -0.1512 0.7402 1.0000
3.750 0.8647 0.04160 0.03014 -0.1505 0.7314 1.0000
4.000 0.8946 0.04174 0.03028 -0.1507 0.7244 1.0000
4.250 0.9132 0.04245 0.03103 -0.1496 0.7143 1.0000
4.500 0.9462 0.04236 0.03096 -0.1500 0.7084 1.0000
4.750 0.9622 0.04321 0.03185 -0.1487 0.6972 1.0000
5.000 0.9981 0.04284 0.03154 -0.1493 0.6922 1.0000
5.250 1.0124 0.04376 0.03255 -0.1477 0.6800 1.0000
5.500 1.0509 0.04304 0.03191 -0.1483 0.6754 1.0000
5.750 1.0654 0.04387 0.03283 -0.1466 0.6627 1.0000
6.000 1.0813 0.04461 0.03368 -0.1451 0.6504 1.0000
6.250 1.1204 0.04364 0.03286 -0.1456 0.6456 1.0000
6.500 1.1342 0.04449 0.03383 -0.1438 0.6324 1.0000
6.750 1.1508 0.04512 0.03459 -0.1422 0.6197 1.0000
7.250 1.2080 0.04437 0.03418 -0.1409 0.6008 1.0000
7.500 1.2243 0.04494 0.03490 -0.1392 0.5872 1.0000
7.750 1.2426 0.04534 0.03549 -0.1376 0.5738 1.0000
8.250 1.2865 0.04541 0.03592 -0.1350 0.5474 1.0000
8.500 1.3116 0.04518 0.03587 -0.1338 0.5341 1.0000
8.750 1.3364 0.04499 0.03589 -0.1326 0.5200 1.0000
9.000 1.3593 0.04500 0.03608 -0.1313 0.5048 1.0000
9.250 1.3791 0.04524 0.03650 -0.1297 0.4879 1.0000
9.500 1.3988 0.04548 0.03690 -0.1281 0.4696 1.0000
9.750 1.4203 0.04557 0.03715 -0.1265 0.4505 1.0000
10.000 1.4416 0.04574 0.03742 -0.1250 0.4309 1.0000
10.250 1.4501 0.04703 0.03887 -0.1227 0.4102 1.0000
10.500 1.4622 0.04800 0.03993 -0.1206 0.3890 1.0000
10.750 1.4702 0.04931 0.04134 -0.1182 0.3671 1.0000
11.000 1.4708 0.05116 0.04323 -0.1155 0.3426 1.0000
11.250 1.4662 0.05348 0.04555 -0.1127 0.3160 1.0000
11.500 1.4587 0.05619 0.04820 -0.1100 0.2875 1.0000
11.750 1.4490 0.05934 0.05125 -0.1077 0.2579 1.0000
12.000 1.4392 0.06283 0.05466 -0.1058 0.2281 1.0000
12.250 1.4299 0.06656 0.05830 -0.1044 0.1989 1.0000
12.500 1.4206 0.07057 0.06225 -0.1033 0.1699 1.0000
12.750 1.4101 0.07498 0.06655 -0.1025 0.1411 1.0000
13.000 1.3987 0.07978 0.07122 -0.1021 0.1145 1.0000
13.250 1.3863 0.08493 0.07622 -0.1020 0.0946 1.0000
13.500 1.3758 0.09004 0.08128 -0.1021 0.0793 1.0000
13.750 1.3656 0.09522 0.08644 -0.1026 0.0696 1.0000
14.000 1.3582 0.10011 0.09138 -0.1031 0.0621 1.0000
14.250 1.3527 0.10477 0.09610 -0.1036 0.0568 1.0000
14.500 1.3493 0.10910 0.10055 -0.1042 0.0527 1.0000
14.750 1.3456 0.11343 0.10490 -0.1050 0.0500 1.0000
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Polar data table (+)
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