FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 200,000 Max Cl/Cd: 57.69 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fauvel-il-200000.txt Download as CSV file: xf-fauvel-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4194 0.10202 0.09816 0.0102 0.6919 0.0773
-9.750 -0.4753 0.09063 0.08686 -0.0020 0.6961 0.0808
-9.500 -0.5238 0.08110 0.07726 -0.0100 0.6971 0.0810
-9.250 -0.4654 0.08195 0.07815 -0.0020 0.6840 0.0829
-9.000 -0.4538 0.07958 0.07574 -0.0010 0.6771 0.0843
-8.750 -0.4600 0.07476 0.07089 -0.0032 0.6731 0.0858
-8.500 -0.6096 0.06861 0.06435 -0.0088 0.6891 0.0833
-8.250 -0.5981 0.06666 0.06238 -0.0077 0.6815 0.0848
-8.000 -0.5983 0.06396 0.05956 -0.0064 0.6758 0.0868
-7.750 -0.6479 0.06299 0.05763 -0.0005 0.6742 0.0928
-7.500 -0.6257 0.05571 0.05070 -0.0022 0.6668 0.0946
-7.250 -0.6081 0.05350 0.04849 -0.0014 0.6597 0.0962
-7.000 -0.6459 0.03916 0.03222 0.0070 0.6605 0.0622
-6.750 -0.6283 0.03617 0.02904 0.0083 0.6543 0.0613
-6.500 -0.6102 0.03351 0.02613 0.0098 0.6469 0.0603
-6.250 -0.5913 0.03094 0.02318 0.0115 0.6405 0.0590
-6.000 -0.5700 0.02877 0.02066 0.0129 0.6335 0.0583
-5.750 -0.5465 0.02719 0.01881 0.0140 0.6262 0.0584
-5.500 -0.5220 0.02606 0.01744 0.0150 0.6196 0.0595
-5.250 -0.4963 0.02488 0.01608 0.0157 0.6112 0.0603
-5.000 -0.4700 0.02382 0.01477 0.0165 0.6047 0.0608
-4.750 -0.4426 0.02281 0.01365 0.0170 0.5960 0.0615
-4.500 -0.4155 0.02203 0.01268 0.0176 0.5893 0.0622
-4.250 -0.3876 0.02097 0.01166 0.0178 0.5812 0.0638
-4.000 -0.3609 0.02027 0.01097 0.0183 0.5740 0.0657
-3.750 -0.3341 0.01965 0.01034 0.0188 0.5663 0.0675
-3.500 -0.3077 0.01903 0.00968 0.0195 0.5587 0.0692
-3.250 -0.2817 0.01855 0.00911 0.0203 0.5523 0.0710
-3.000 -0.2575 0.01779 0.00847 0.0211 0.5443 0.0738
-2.750 -0.2330 0.01735 0.00800 0.0221 0.5387 0.0779
-2.500 -0.2089 0.01686 0.00756 0.0231 0.5304 0.0830
-2.250 -0.1851 0.01639 0.00708 0.0242 0.5240 0.0907
-2.000 -0.1629 0.01577 0.00656 0.0255 0.5176 0.1100
-1.750 -0.1494 0.01443 0.00614 0.0280 0.5111 0.2876
-1.500 -0.1370 0.01337 0.00570 0.0309 0.5062 0.4305
-1.250 -0.1276 0.01225 0.00595 0.0357 0.5007 0.7588
-1.000 -0.0959 0.01237 0.00619 0.0362 0.4931 0.8267
-0.750 -0.0622 0.01267 0.00638 0.0364 0.4874 0.8642
-0.500 -0.0272 0.01319 0.00689 0.0364 0.4796 0.8940
-0.250 0.0153 0.01377 0.00732 0.0350 0.4730 0.9130
0.000 0.0926 0.01474 0.00814 0.0271 0.4642 0.9261
0.250 0.1480 0.01514 0.00838 0.0227 0.4566 0.9346
0.500 0.1797 0.01534 0.00842 0.0222 0.4515 0.9435
0.750 0.2243 0.01547 0.00853 0.0191 0.4446 0.9474
1.000 0.2629 0.01556 0.00851 0.0172 0.4389 0.9529
1.250 0.2959 0.01570 0.00850 0.0162 0.4340 0.9591
1.500 0.3380 0.01576 0.00858 0.0135 0.4275 0.9637
1.750 0.3711 0.01587 0.00863 0.0124 0.4226 0.9707
2.000 0.4128 0.01589 0.00852 0.0097 0.4180 0.9745
2.250 0.4482 0.01599 0.00863 0.0080 0.4129 0.9796
2.500 0.4852 0.01599 0.00864 0.0061 0.4074 0.9843
2.750 0.5249 0.01597 0.00853 0.0036 0.4026 0.9892
3.000 0.5622 0.01612 0.00856 0.0016 0.3986 0.9940
3.250 0.6014 0.01607 0.00862 -0.0010 0.3937 0.9984
3.500 0.6301 0.01612 0.00869 -0.0015 0.3891 1.0000
3.750 0.6521 0.01621 0.00874 -0.0006 0.3853 1.0000
4.000 0.6743 0.01640 0.00884 0.0003 0.3821 1.0000
4.250 0.6961 0.01665 0.00916 0.0011 0.3785 1.0000
4.500 0.7178 0.01683 0.00943 0.0019 0.3743 1.0000
4.750 0.7398 0.01697 0.00959 0.0028 0.3703 1.0000
5.000 0.7621 0.01709 0.00965 0.0037 0.3667 1.0000
5.250 0.7844 0.01735 0.00984 0.0046 0.3628 1.0000
5.500 0.8053 0.01744 0.01009 0.0056 0.3571 1.0000
5.750 0.8271 0.01747 0.01010 0.0066 0.3518 1.0000
6.000 0.8495 0.01756 0.01011 0.0076 0.3478 1.0000
6.250 0.8706 0.01787 0.01047 0.0085 0.3438 1.0000
6.500 0.8912 0.01810 0.01083 0.0096 0.3391 1.0000
6.750 0.9127 0.01825 0.01100 0.0106 0.3347 1.0000
7.000 0.9348 0.01840 0.01109 0.0116 0.3311 1.0000
7.250 0.9558 0.01875 0.01146 0.0127 0.3272 1.0000
7.500 0.9753 0.01902 0.01188 0.0139 0.3222 1.0000
7.750 0.9964 0.01915 0.01204 0.0150 0.3175 1.0000
8.000 1.0186 0.01928 0.01209 0.0160 0.3136 1.0000
8.250 1.0378 0.01965 0.01257 0.0173 0.3088 1.0000
8.500 1.0571 0.01987 0.01291 0.0186 0.3034 1.0000
8.750 1.0786 0.01993 0.01293 0.0197 0.2986 1.0000
9.000 1.0985 0.02018 0.01320 0.0209 0.2934 1.0000
9.250 1.1166 0.02035 0.01350 0.0224 0.2866 1.0000
9.500 1.1381 0.02028 0.01334 0.0235 0.2805 1.0000
9.750 1.1545 0.02048 0.01370 0.0251 0.2723 1.0000
10.000 1.1742 0.02046 0.01361 0.0264 0.2649 1.0000
10.250 1.1901 0.02075 0.01406 0.0280 0.2564 1.0000
10.500 1.2081 0.02094 0.01419 0.0294 0.2491 1.0000
10.750 1.2227 0.02137 0.01478 0.0310 0.2402 1.0000
11.000 1.2378 0.02174 0.01510 0.0326 0.2320 1.0000
11.250 1.2500 0.02229 0.01576 0.0344 0.2221 1.0000
11.500 1.2604 0.02295 0.01646 0.0363 0.2126 1.0000
11.750 1.2677 0.02373 0.01718 0.0384 0.2039 1.0000
12.000 1.2717 0.02472 0.01827 0.0406 0.1945 1.0000
12.250 1.2672 0.02592 0.01944 0.0437 0.1877 1.0000
12.500 1.2595 0.02766 0.02125 0.0456 0.1807 1.0000
12.750 1.2534 0.02998 0.02354 0.0460 0.1745 1.0000
13.000 1.2493 0.03248 0.02611 0.0459 0.1675 1.0000
13.250 1.2439 0.03501 0.02856 0.0460 0.1616 1.0000
13.500 1.2388 0.03772 0.03138 0.0458 0.1553 1.0000
13.750 1.2329 0.04041 0.03400 0.0457 0.1498 1.0000
14.000 1.2271 0.04328 0.03694 0.0454 0.1443 1.0000
14.250 1.2205 0.04626 0.03993 0.0450 0.1390 1.0000
14.500 1.2158 0.04903 0.04266 0.0447 0.1338 1.0000
14.750 1.2077 0.05241 0.04613 0.0439 0.1287 1.0000
15.000 1.2054 0.05490 0.04849 0.0438 0.1233 1.0000
15.250 1.1968 0.05868 0.05241 0.0425 0.1185 1.0000
15.500 1.1918 0.06200 0.05573 0.0416 0.1136 1.0000
15.750 1.1896 0.06493 0.05863 0.0410 0.1086 1.0000
16.000 1.1832 0.06871 0.06250 0.0396 0.1041 1.0000
16.250 1.1859 0.07100 0.06468 0.0393 0.0998 1.0000
16.500 1.1818 0.07452 0.06830 0.0382 0.0962 1.0000
16.750 1.1780 0.07808 0.07193 0.0369 0.0927 1.0000
17.000 1.1815 0.08044 0.07425 0.0364 0.0898 1.0000
17.250 1.1854 0.08273 0.07653 0.0361 0.0870 1.0000
17.500 1.1804 0.08666 0.08060 0.0345 0.0848 1.0000
17.750 1.1794 0.08993 0.08394 0.0334 0.0826 1.0000
18.000 1.1832 0.09243 0.08644 0.0326 0.0807 1.0000
18.250 1.1992 0.09280 0.08671 0.0334 0.0786 1.0000
18.500 1.1908 0.09737 0.09144 0.0314 0.0773 1.0000
18.750 1.1811 0.10223 0.09647 0.0292 0.0761 1.0000
19.000 1.1729 0.10688 0.10127 0.0271 0.0750 1.0000
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