AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 50,000 Max Cl/Cd: 41.95 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100a-il-50000-n5.txt Download as CSV file: xf-ah79100a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 A 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3816 0.10441 0.09715 -0.0414 1.0000 0.0558
-9.250 -0.3786 0.10105 0.09384 -0.0415 1.0000 0.0552
-9.000 -0.3784 0.09773 0.09060 -0.0419 1.0000 0.0547
-8.750 -0.3818 0.09422 0.08716 -0.0426 1.0000 0.0547
-8.500 -0.3856 0.09095 0.08399 -0.0429 1.0000 0.0544
-8.250 -0.3931 0.08765 0.08081 -0.0431 1.0000 0.0545
-8.000 -0.4033 0.08457 0.07787 -0.0428 1.0000 0.0545
-7.750 -0.4137 0.08132 0.07477 -0.0428 1.0000 0.0544
-7.500 -0.4220 0.07762 0.07118 -0.0438 1.0000 0.0540
-7.250 -0.4311 0.07286 0.06650 -0.0464 1.0000 0.0540
-7.000 -0.4374 0.06761 0.06126 -0.0501 1.0000 0.0535
-6.750 -0.4419 0.06217 0.05574 -0.0540 1.0000 0.0533
-6.500 -0.4409 0.05637 0.04970 -0.0585 1.0000 0.0534
-6.250 -0.4320 0.05092 0.04388 -0.0625 1.0000 0.0535
-6.000 -0.4162 0.04562 0.03805 -0.0663 1.0000 0.0540
-5.750 -0.3948 0.04106 0.03278 -0.0693 1.0000 0.0553
-5.500 -0.3730 0.03789 0.02918 -0.0709 1.0000 0.0583
-5.250 -0.3516 0.03583 0.02692 -0.0714 1.0000 0.0617
-5.000 -0.3268 0.03335 0.02397 -0.0722 1.0000 0.0644
-4.750 -0.3010 0.03130 0.02137 -0.0726 1.0000 0.0684
-4.500 -0.2778 0.02981 0.01976 -0.0727 1.0000 0.0738
-4.250 -0.2535 0.02846 0.01816 -0.0725 1.0000 0.0790
-4.000 -0.2261 0.02722 0.01672 -0.0728 0.9985 0.0859
-3.750 -0.1899 0.02619 0.01551 -0.0748 0.9931 0.0984
-3.500 -0.1539 0.02519 0.01446 -0.0770 0.9876 0.1151
-3.250 -0.1167 0.02421 0.01353 -0.0796 0.9817 0.1457
-3.000 -0.0782 0.02312 0.01276 -0.0827 0.9761 0.2134
-2.750 -0.0412 0.02262 0.01282 -0.0851 0.9697 0.3430
-2.500 -0.0088 0.02275 0.01304 -0.0861 0.9618 0.4302
-2.250 0.0260 0.02300 0.01328 -0.0873 0.9547 0.4920
-2.000 0.0547 0.02317 0.01343 -0.0873 0.9459 0.5376
-1.750 0.0901 0.02329 0.01342 -0.0886 0.9390 0.5771
-1.500 0.1193 0.02331 0.01337 -0.0888 0.9299 0.6067
-1.250 0.1529 0.02330 0.01328 -0.0899 0.9222 0.6346
-1.000 0.1844 0.02325 0.01318 -0.0905 0.9135 0.6607
-0.750 0.2158 0.02320 0.01310 -0.0911 0.9047 0.6869
-0.500 0.2506 0.02310 0.01298 -0.0923 0.8969 0.7146
-0.250 0.2787 0.02303 0.01292 -0.0923 0.8871 0.7435
0.000 0.3152 0.02280 0.01276 -0.0936 0.8804 0.7794
0.250 0.3406 0.02262 0.01269 -0.0929 0.8695 0.8256
0.500 0.3767 0.02231 0.01248 -0.0944 0.8593 1.0000
0.750 0.4188 0.02240 0.01240 -0.0975 0.8514 1.0000
1.000 0.4505 0.02262 0.01248 -0.0986 0.8400 1.0000
1.250 0.4843 0.02279 0.01255 -0.0998 0.8297 1.0000
1.500 0.5220 0.02284 0.01252 -0.1015 0.8213 1.0000
1.750 0.5508 0.02307 0.01269 -0.1017 0.8091 1.0000
2.000 0.5809 0.02324 0.01284 -0.1021 0.7974 1.0000
2.250 0.6133 0.02333 0.01290 -0.1026 0.7866 1.0000
2.500 0.6473 0.02333 0.01290 -0.1033 0.7764 1.0000
2.750 0.6750 0.02352 0.01313 -0.1031 0.7634 1.0000
3.000 0.7031 0.02369 0.01333 -0.1029 0.7506 1.0000
3.250 0.7319 0.02382 0.01351 -0.1027 0.7378 1.0000
3.500 0.7611 0.02391 0.01365 -0.1025 0.7248 1.0000
3.750 0.7904 0.02398 0.01381 -0.1023 0.7114 1.0000
4.000 0.8194 0.02405 0.01395 -0.1019 0.6977 1.0000
4.250 0.8478 0.02414 0.01413 -0.1015 0.6833 1.0000
4.500 0.8753 0.02424 0.01436 -0.1008 0.6676 1.0000
4.750 0.9024 0.02435 0.01457 -0.1001 0.6509 1.0000
5.000 0.9297 0.02446 0.01478 -0.0994 0.6336 1.0000
5.250 0.9575 0.02451 0.01492 -0.0985 0.6152 1.0000
5.500 0.9831 0.02464 0.01517 -0.0975 0.5944 1.0000
5.750 1.0080 0.02480 0.01541 -0.0962 0.5713 1.0000
6.000 1.0315 0.02504 0.01572 -0.0948 0.5467 1.0000
6.250 1.0552 0.02529 0.01606 -0.0934 0.5212 1.0000
6.500 1.0768 0.02567 0.01651 -0.0919 0.4940 1.0000
6.750 1.0964 0.02615 0.01706 -0.0901 0.4644 1.0000
7.000 1.1143 0.02671 0.01765 -0.0881 0.4317 1.0000
7.250 1.1299 0.02739 0.01834 -0.0859 0.3954 1.0000
7.500 1.1436 0.02821 0.01912 -0.0836 0.3568 1.0000
7.750 1.1547 0.02924 0.02003 -0.0811 0.3160 1.0000
8.000 1.1636 0.03050 0.02117 -0.0785 0.2739 1.0000
8.250 1.1707 0.03200 0.02251 -0.0760 0.2343 1.0000
8.500 1.1747 0.03373 0.02402 -0.0732 0.1994 1.0000
8.750 1.1778 0.03561 0.02575 -0.0706 0.1682 1.0000
9.000 1.1795 0.03774 0.02770 -0.0681 0.1429 1.0000
9.250 1.1825 0.03992 0.02987 -0.0659 0.1200 1.0000
9.500 1.1843 0.04228 0.03214 -0.0639 0.1033 1.0000
9.750 1.1872 0.04468 0.03453 -0.0620 0.0898 1.0000
10.000 1.1915 0.04710 0.03701 -0.0603 0.0786 1.0000
10.250 1.1978 0.04956 0.03957 -0.0588 0.0704 1.0000
10.500 1.2019 0.05208 0.04208 -0.0574 0.0642 1.0000
10.750 1.2131 0.05449 0.04475 -0.0560 0.0582 1.0000
11.000 1.2223 0.05697 0.04733 -0.0548 0.0543 1.0000
11.250 1.2328 0.05965 0.05018 -0.0536 0.0508 1.0000
11.500 1.2399 0.06262 0.05350 -0.0526 0.0475 1.0000
11.750 1.2440 0.06568 0.05679 -0.0518 0.0451 1.0000
12.000 1.2482 0.06889 0.06016 -0.0510 0.0434 1.0000
12.250 1.2534 0.07234 0.06374 -0.0504 0.0421 1.0000
12.500 1.2513 0.07661 0.06828 -0.0500 0.0414 1.0000
12.750 1.2415 0.08149 0.07353 -0.0503 0.0410 1.0000
13.000 1.2279 0.08692 0.07929 -0.0513 0.0407 1.0000
13.250 1.2116 0.09292 0.08559 -0.0531 0.0405 1.0000
13.500 1.1933 0.09955 0.09250 -0.0559 0.0405 1.0000
13.750 1.1733 0.10691 0.10010 -0.0596 0.0406 1.0000
14.000 1.1525 0.11503 0.10842 -0.0642 0.0408 1.0000
14.250 1.1316 0.12394 0.11749 -0.0696 0.0411 1.0000
14.500 1.1114 0.13362 0.12729 -0.0758 0.0414 1.0000
14.750 1.0932 0.14379 0.13755 -0.0823 0.0417 1.0000
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