SA7026 (sa7026-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 100,000 Max Cl/Cd: 61.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7026-il-100000.txt Download as CSV file: xf-sa7026-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SA7026
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3617 0.10601 0.10151 -0.0378 1.0000 0.0748
-8.250 -0.3813 0.10553 0.10116 -0.0362 1.0000 0.0750
-8.000 -0.4014 0.10499 0.10073 -0.0340 1.0000 0.0751
-7.750 -0.3661 0.09710 0.09274 -0.0310 1.0000 0.0783
-7.500 -0.3717 0.09529 0.09099 -0.0284 1.0000 0.0800
-7.250 -0.3829 0.09386 0.08965 -0.0258 1.0000 0.0814
-7.000 -0.3975 0.09264 0.08851 -0.0231 1.0000 0.0825
-6.750 -0.4106 0.09104 0.08699 -0.0216 1.0000 0.0843
-6.500 -0.4215 0.08908 0.08510 -0.0221 1.0000 0.0862
-6.000 -0.4347 0.08254 0.07858 -0.0326 1.0000 0.0895
-5.750 -0.4328 0.07993 0.07606 -0.0258 1.0000 0.0914
-5.500 -0.4301 0.07754 0.07369 -0.0239 1.0000 0.0944
-5.250 -0.4158 0.07310 0.06890 -0.0387 1.0000 0.1029
-5.000 -0.4143 0.06944 0.06545 -0.0334 1.0000 0.1044
-4.750 -0.4090 0.06712 0.06318 -0.0305 1.0000 0.1076
-4.500 -0.3893 0.06254 0.05836 -0.0377 1.0000 0.1181
-4.250 -0.3815 0.06020 0.05611 -0.0351 1.0000 0.1215
-4.000 -0.3464 0.05614 0.05190 -0.0410 0.9952 0.1363
-3.750 -0.3090 0.05225 0.04778 -0.0476 0.9895 0.1612
-3.500 -0.2712 0.04917 0.04449 -0.0527 0.9842 0.1886
-3.250 -0.2435 0.04629 0.04162 -0.0540 0.9784 0.2060
-3.000 -0.1572 0.03299 0.02603 -0.0657 0.9778 0.0699
-2.750 -0.1129 0.02987 0.02198 -0.0679 0.9735 0.0599
-2.500 -0.0731 0.02774 0.01940 -0.0700 0.9689 0.0576
-2.250 -0.0380 0.02620 0.01751 -0.0711 0.9627 0.0574
-2.000 0.0041 0.02503 0.01607 -0.0733 0.9580 0.0598
-1.750 0.0348 0.02409 0.01512 -0.0740 0.9508 0.0671
-1.500 0.0746 0.02325 0.01431 -0.0762 0.9451 0.0826
-1.250 0.1071 0.02062 0.01374 -0.0773 0.9404 0.5282
-1.000 0.1459 0.01965 0.01362 -0.0783 0.9336 1.0000
-0.750 0.1827 0.02001 0.01358 -0.0803 0.9258 1.0000
-0.500 0.2209 0.02033 0.01360 -0.0826 0.9179 1.0000
-0.250 0.2521 0.02063 0.01367 -0.0835 0.9084 1.0000
0.000 0.2967 0.02091 0.01370 -0.0868 0.9023 1.0000
0.250 0.3238 0.02117 0.01382 -0.0869 0.8917 1.0000
0.500 0.3576 0.02142 0.01393 -0.0882 0.8829 1.0000
0.750 0.3984 0.02155 0.01392 -0.0905 0.8756 1.0000
1.000 0.4270 0.02176 0.01405 -0.0908 0.8650 1.0000
1.250 0.4657 0.02182 0.01403 -0.0927 0.8571 1.0000
1.500 0.5046 0.02177 0.01394 -0.0944 0.8485 1.0000
1.750 0.5354 0.02185 0.01397 -0.0949 0.8379 1.0000
2.000 0.5852 0.02144 0.01356 -0.0981 0.8330 1.0000
2.250 0.6128 0.02146 0.01357 -0.0978 0.8214 1.0000
2.500 0.6431 0.02140 0.01353 -0.0978 0.8108 1.0000
2.750 0.6879 0.02078 0.01295 -0.0998 0.8054 1.0000
3.000 0.7161 0.02064 0.01284 -0.0993 0.7935 1.0000
3.250 0.7461 0.02040 0.01268 -0.0990 0.7821 1.0000
3.500 0.7789 0.01999 0.01232 -0.0989 0.7713 1.0000
3.750 0.8194 0.01920 0.01158 -0.0997 0.7635 1.0000
4.000 0.8491 0.01885 0.01130 -0.0991 0.7503 1.0000
4.250 0.8793 0.01847 0.01103 -0.0986 0.7366 1.0000
4.500 0.9098 0.01810 0.01072 -0.0981 0.7222 1.0000
4.750 0.9358 0.01795 0.01065 -0.0970 0.7045 1.0000
5.000 0.9633 0.01773 0.01050 -0.0960 0.6858 1.0000
5.250 0.9933 0.01743 0.01026 -0.0954 0.6669 1.0000
5.500 1.0176 0.01740 0.01029 -0.0940 0.6432 1.0000
5.750 1.0429 0.01739 0.01031 -0.0928 0.6186 1.0000
6.000 1.0674 0.01749 0.01042 -0.0915 0.5922 1.0000
6.250 1.0903 0.01769 0.01067 -0.0901 0.5636 1.0000
6.500 1.1117 0.01798 0.01094 -0.0885 0.5325 1.0000
6.750 1.1322 0.01835 0.01125 -0.0867 0.4997 1.0000
7.000 1.1500 0.01884 0.01172 -0.0846 0.4643 1.0000
7.250 1.1672 0.01942 0.01222 -0.0825 0.4292 1.0000
7.500 1.1822 0.02009 0.01291 -0.0802 0.3921 1.0000
7.750 1.1956 0.02085 0.01360 -0.0778 0.3544 1.0000
8.000 1.2059 0.02171 0.01435 -0.0749 0.3137 1.0000
8.250 1.2120 0.02268 0.01518 -0.0716 0.2668 1.0000
8.500 1.2150 0.02387 0.01612 -0.0681 0.2150 1.0000
8.750 1.2149 0.02539 0.01729 -0.0645 0.1585 1.0000
9.000 1.2079 0.02773 0.01911 -0.0600 0.1018 1.0000
9.250 1.1981 0.03065 0.02163 -0.0554 0.0651 1.0000
9.500 1.1944 0.03318 0.02408 -0.0517 0.0525 1.0000
9.750 1.1984 0.03549 0.02648 -0.0487 0.0459 1.0000
10.000 1.2063 0.03792 0.02885 -0.0466 0.0414 1.0000
10.250 1.2313 0.04081 0.03191 -0.0457 0.0383 1.0000
10.500 1.2555 0.04341 0.03476 -0.0449 0.0358 1.0000
10.750 1.2711 0.04590 0.03746 -0.0437 0.0334 1.0000
11.000 1.2870 0.04900 0.04066 -0.0429 0.0312 1.0000
11.250 1.3044 0.05342 0.04539 -0.0423 0.0306 1.0000
11.500 1.3085 0.05714 0.04947 -0.0403 0.0305 1.0000
11.750 1.3053 0.06049 0.05317 -0.0378 0.0306 1.0000
12.000 1.2973 0.06390 0.05692 -0.0353 0.0308 1.0000
12.250 1.2852 0.06736 0.06073 -0.0330 0.0311 1.0000
12.500 1.2695 0.07123 0.06496 -0.0312 0.0315 1.0000
12.750 1.2504 0.07571 0.06977 -0.0302 0.0319 1.0000
13.000 1.2256 0.08094 0.07535 -0.0302 0.0324 1.0000
13.250 1.1976 0.08703 0.08176 -0.0316 0.0330 1.0000
13.500 1.1710 0.09376 0.08876 -0.0342 0.0333 1.0000
13.750 1.1432 0.10148 0.09671 -0.0382 0.0338 1.0000
14.000 1.1146 0.11036 0.10579 -0.0438 0.0344 1.0000
14.250 1.0846 0.12103 0.11662 -0.0511 0.0351 1.0000
14.500 1.0546 0.13372 0.12940 -0.0600 0.0361 1.0000
14.750 1.0333 0.14578 0.14146 -0.0674 0.0378 1.0000
15.000 1.0235 0.15484 0.15049 -0.0722 0.0390 1.0000
15.250 1.0204 0.16163 0.15726 -0.0752 0.0398 1.0000
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Polar data table (+)
Polar graphs
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