FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 50,000 Max Cl/Cd: 9.94 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fauvel-il-50000.txt Download as CSV file: xf-fauvel-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FAUVEL 14% 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4551 0.11979 0.11388 0.0257 1.0000 0.2889
-9.500 -0.4345 0.11489 0.10906 0.0254 1.0000 0.2976
-9.250 -0.4678 0.11466 0.10901 0.0229 1.0000 0.3099
-9.000 -0.4174 0.10796 0.10231 0.0235 1.0000 0.3206
-8.750 -0.4181 0.10473 0.09920 0.0222 1.0000 0.3329
-8.500 -0.4358 0.10316 0.09779 0.0207 1.0000 0.3484
-8.250 -0.3997 0.09824 0.09291 0.0203 1.0000 0.3639
-8.000 -0.3819 0.09444 0.08922 0.0194 1.0000 0.3808
-7.750 -0.3922 0.09250 0.08742 0.0187 1.0000 0.4042
-7.500 -0.3746 0.08874 0.08379 0.0177 1.0000 0.4243
-7.250 -0.3469 0.08478 0.07991 0.0163 1.0000 0.4442
-7.000 -0.3213 0.08125 0.07647 0.0145 1.0000 0.4647
-6.750 -0.4971 0.06086 0.05531 -0.0182 0.9461 0.1944
-6.500 -0.4993 0.05346 0.04683 -0.0214 0.9243 0.1678
-6.250 -0.4710 0.04958 0.04265 -0.0231 0.9025 0.1636
-6.000 -0.4526 0.04623 0.03890 -0.0230 0.8831 0.1590
-5.750 -0.4399 0.04313 0.03511 -0.0214 0.8663 0.1539
-5.500 -0.4247 0.04101 0.03225 -0.0194 0.8506 0.1515
-5.250 -0.4033 0.03916 0.03024 -0.0183 0.8352 0.1534
-5.000 -0.3817 0.03777 0.02867 -0.0170 0.8202 0.1564
-4.750 -0.3589 0.03637 0.02700 -0.0161 0.8055 0.1586
-4.500 -0.3337 0.03505 0.02538 -0.0153 0.7920 0.1610
-4.250 -0.3071 0.03395 0.02393 -0.0145 0.7793 0.1648
-4.000 -0.2789 0.03299 0.02293 -0.0140 0.7667 0.1723
-3.750 -0.2467 0.03225 0.02203 -0.0145 0.7537 0.1825
-3.500 -0.2091 0.03144 0.02132 -0.0156 0.7415 0.1970
-3.250 -0.1742 0.03075 0.02078 -0.0158 0.7303 0.2242
-3.000 0.1188 0.02992 0.02219 -0.0438 0.6994 1.0000
-2.750 0.1375 0.03020 0.02221 -0.0431 0.6905 1.0000
-2.500 0.1596 0.03054 0.02237 -0.0437 0.6803 1.0000
-2.250 0.1785 0.03097 0.02259 -0.0429 0.6723 1.0000
-2.000 0.2010 0.03145 0.02294 -0.0435 0.6626 1.0000
-1.750 0.2192 0.03197 0.02327 -0.0424 0.6552 1.0000
-1.500 0.2430 0.03265 0.02388 -0.0436 0.6462 1.0000
-1.250 0.2612 0.03323 0.02431 -0.0425 0.6395 1.0000
-1.000 0.2843 0.03413 0.02516 -0.0438 0.6311 1.0000
-0.750 0.3031 0.03482 0.02574 -0.0431 0.6240 1.0000
-0.500 0.3236 0.03584 0.02670 -0.0436 0.6174 1.0000
-0.250 0.3438 0.03691 0.02774 -0.0443 0.6105 1.0000
0.000 0.3606 0.03769 0.02839 -0.0428 0.6050 1.0000
0.250 0.3795 0.03925 0.02999 -0.0446 0.5979 1.0000
0.500 0.3961 0.04051 0.03121 -0.0446 0.5923 1.0000
0.750 0.4120 0.04145 0.03205 -0.0430 0.5879 1.0000
1.000 0.4236 0.04364 0.03431 -0.0449 0.5825 1.0000
1.250 0.4336 0.04540 0.03606 -0.0449 0.5775 1.0000
1.500 0.4450 0.04687 0.03749 -0.0439 0.5736 1.0000
1.750 0.4561 0.04844 0.03900 -0.0426 0.5706 1.0000
2.000 0.4512 0.05118 0.04178 -0.0428 0.5687 1.0000
2.250 0.4435 0.05371 0.04430 -0.0417 0.5680 1.0000
2.500 0.4375 0.05608 0.04665 -0.0402 0.5691 1.0000
3.250 0.2145 0.06552 0.05604 -0.0262 0.7474 1.0000
3.500 0.2297 0.06713 0.05757 -0.0250 0.7295 1.0000
3.750 0.2329 0.06792 0.05827 -0.0223 0.7129 1.0000
4.000 0.2369 0.06901 0.05927 -0.0200 0.6973 1.0000
4.250 0.2447 0.07052 0.06071 -0.0183 0.6835 1.0000
4.500 0.2788 0.07398 0.06412 -0.0199 0.6736 1.0000
4.750 0.2762 0.07445 0.06452 -0.0170 0.6593 1.0000
5.000 0.2778 0.07580 0.06580 -0.0150 0.6480 1.0000
5.250 0.3149 0.07963 0.06962 -0.0167 0.6387 1.0000
5.500 0.3043 0.07970 0.06962 -0.0134 0.6254 1.0000
5.750 0.3113 0.08166 0.07153 -0.0123 0.6168 1.0000
6.000 0.3338 0.08433 0.07418 -0.0125 0.6059 1.0000
6.250 0.3291 0.08527 0.07508 -0.0104 0.5944 1.0000
6.500 0.3555 0.08888 0.07867 -0.0111 0.5867 1.0000
6.750 0.3554 0.08981 0.07958 -0.0094 0.5741 1.0000
7.000 0.3568 0.09152 0.08126 -0.0082 0.5644 1.0000
7.250 0.3914 0.09578 0.08554 -0.0093 0.5548 1.0000
7.500 0.3792 0.09597 0.08569 -0.0071 0.5425 1.0000
7.750 0.3878 0.09848 0.08820 -0.0067 0.5339 1.0000
8.000 0.4107 0.10165 0.09138 -0.0069 0.5223 1.0000
8.250 0.4025 0.10267 0.09238 -0.0056 0.5115 1.0000
8.500 0.4287 0.10684 0.09657 -0.0062 0.5032 1.0000
8.750 0.4264 0.10782 0.09755 -0.0051 0.4906 1.0000
9.000 0.4307 0.11039 0.10012 -0.0049 0.4828 1.0000
9.250 0.4505 0.11347 0.10323 -0.0049 0.4715 1.0000
9.500 0.4440 0.11499 0.10474 -0.0043 0.4618 1.0000
9.750 0.4740 0.11947 0.10926 -0.0048 0.4530 1.0000
10.000 0.4593 0.12020 0.10997 -0.0043 0.4442 1.0000
10.250 0.4895 0.12477 0.11460 -0.0047 0.4354 1.0000
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Polar data table (+)
Polar graphs
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