FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 100,000 Max Cl/Cd: 39.46 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fauvel-il-100000-n5.txt Download as CSV file: xf-fauvel-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5762 0.09500 0.08998 0.0014 0.7824 0.0424
-10.250 -0.6179 0.07683 0.07156 -0.0116 0.7533 0.0420
-10.000 -0.6451 0.07047 0.06500 -0.0144 0.7421 0.0418
-9.750 -0.6738 0.06532 0.05960 -0.0144 0.7321 0.0418
-9.500 -0.6985 0.06123 0.05524 -0.0120 0.7233 0.0418
-9.250 -0.7186 0.05706 0.05071 -0.0093 0.7154 0.0419
-9.000 -0.7322 0.05291 0.04610 -0.0065 0.7084 0.0421
-8.750 -0.7373 0.04918 0.04189 -0.0038 0.7009 0.0422
-8.500 -0.7357 0.04594 0.03818 -0.0014 0.6940 0.0424
-8.250 -0.7231 0.04371 0.03575 0.0001 0.6859 0.0428
-8.000 -0.7082 0.04179 0.03362 0.0014 0.6781 0.0432
-7.750 -0.6913 0.04025 0.03190 0.0026 0.6709 0.0440
-7.500 -0.6745 0.03860 0.03001 0.0040 0.6633 0.0451
-7.250 -0.6578 0.03673 0.02778 0.0055 0.6567 0.0461
-7.000 -0.6394 0.03479 0.02546 0.0069 0.6495 0.0470
-6.750 -0.6193 0.03301 0.02329 0.0083 0.6425 0.0476
-6.500 -0.5973 0.03144 0.02134 0.0094 0.6359 0.0482
-6.250 -0.5732 0.03014 0.01994 0.0101 0.6281 0.0490
-6.000 -0.5493 0.02923 0.01894 0.0108 0.6217 0.0502
-5.750 -0.5242 0.02830 0.01792 0.0114 0.6138 0.0517
-5.500 -0.4989 0.02734 0.01677 0.0121 0.6069 0.0532
-5.250 -0.4722 0.02635 0.01562 0.0126 0.5996 0.0543
-5.000 -0.4456 0.02543 0.01461 0.0131 0.5921 0.0554
-4.750 -0.4200 0.02464 0.01382 0.0136 0.5855 0.0566
-4.500 -0.3944 0.02396 0.01316 0.0142 0.5774 0.0584
-4.250 -0.3695 0.02338 0.01247 0.0150 0.5713 0.0609
-4.000 -0.3443 0.02275 0.01183 0.0157 0.5630 0.0633
-3.750 -0.3203 0.02217 0.01126 0.0166 0.5564 0.0656
-3.500 -0.2959 0.02164 0.01072 0.0174 0.5487 0.0684
-3.250 -0.2716 0.02114 0.01016 0.0184 0.5416 0.0719
-3.000 -0.2475 0.02067 0.00969 0.0193 0.5352 0.0774
-2.750 -0.2231 0.02020 0.00927 0.0201 0.5274 0.0858
-2.500 -0.1993 0.01967 0.00875 0.0212 0.5216 0.1001
-2.250 -0.1761 0.01905 0.00838 0.0221 0.5136 0.1330
-2.000 -0.1549 0.01835 0.00814 0.0234 0.5073 0.2336
-1.750 -0.1328 0.01784 0.00788 0.0245 0.5012 0.3059
-1.500 -0.1138 0.01703 0.00757 0.0261 0.4944 0.4121
-1.250 -0.0751 0.01636 0.00843 0.0268 0.4881 0.8045
-1.000 -0.0366 0.01699 0.00904 0.0267 0.4801 0.8610
-0.750 0.0095 0.01753 0.00940 0.0248 0.4729 0.8855
-0.500 0.0483 0.01783 0.00952 0.0235 0.4667 0.8998
-0.250 0.0845 0.01802 0.00959 0.0223 0.4596 0.9089
0.000 0.1185 0.01810 0.00949 0.0215 0.4540 0.9163
0.250 0.1545 0.01823 0.00951 0.0202 0.4476 0.9229
0.500 0.1861 0.01835 0.00953 0.0197 0.4414 0.9310
0.750 0.2245 0.01845 0.00947 0.0179 0.4363 0.9374
1.000 0.2550 0.01858 0.00952 0.0174 0.4310 0.9451
1.250 0.2933 0.01869 0.00957 0.0154 0.4246 0.9504
1.500 0.3245 0.01879 0.00956 0.0148 0.4197 0.9581
1.750 0.3637 0.01887 0.00953 0.0126 0.4150 0.9633
2.000 0.3955 0.01905 0.00972 0.0117 0.4096 0.9699
2.250 0.4301 0.01911 0.00973 0.0102 0.4045 0.9737
2.500 0.4620 0.01916 0.00967 0.0093 0.4003 0.9778
2.750 0.4917 0.01933 0.00983 0.0087 0.3957 0.9823
3.000 0.5254 0.01947 0.01000 0.0072 0.3906 0.9856
3.250 0.5576 0.01958 0.01009 0.0061 0.3862 0.9895
3.500 0.5887 0.01969 0.01010 0.0053 0.3825 0.9933
3.750 0.6216 0.01986 0.01032 0.0039 0.3780 0.9970
4.000 0.6525 0.02010 0.01062 0.0029 0.3731 1.0000
4.250 0.6740 0.02032 0.01085 0.0038 0.3694 1.0000
4.500 0.6955 0.02051 0.01101 0.0048 0.3661 1.0000
4.750 0.7170 0.02072 0.01114 0.0058 0.3631 1.0000
5.000 0.7374 0.02114 0.01173 0.0067 0.3584 1.0000
5.250 0.7579 0.02150 0.01216 0.0077 0.3543 1.0000
5.500 0.7788 0.02178 0.01245 0.0087 0.3507 1.0000
5.750 0.8001 0.02200 0.01262 0.0098 0.3476 1.0000
6.000 0.8202 0.02240 0.01309 0.0109 0.3438 1.0000
6.250 0.8391 0.02291 0.01375 0.0119 0.3389 1.0000
6.500 0.8593 0.02315 0.01400 0.0131 0.3339 1.0000
6.750 0.8810 0.02316 0.01391 0.0144 0.3295 1.0000
7.000 0.8983 0.02368 0.01462 0.0156 0.3230 1.0000
7.250 0.9174 0.02398 0.01497 0.0168 0.3176 1.0000
7.500 0.9382 0.02414 0.01508 0.0181 0.3137 1.0000
7.750 0.9560 0.02464 0.01569 0.0193 0.3089 1.0000
8.000 0.9728 0.02520 0.01641 0.0206 0.3035 1.0000
8.250 0.9921 0.02548 0.01670 0.0219 0.2990 1.0000
8.500 1.0126 0.02566 0.01684 0.0232 0.2951 1.0000
8.750 1.0255 0.02651 0.01793 0.0247 0.2889 1.0000
9.000 1.0428 0.02690 0.01838 0.0260 0.2837 1.0000
9.250 1.0636 0.02699 0.01841 0.0273 0.2795 1.0000
9.500 1.0730 0.02800 0.01967 0.0290 0.2727 1.0000
9.750 1.0887 0.02842 0.02014 0.0304 0.2671 1.0000
10.000 1.1038 0.02888 0.02063 0.0319 0.2617 1.0000
10.250 1.1110 0.02988 0.02181 0.0337 0.2548 1.0000
10.500 1.1262 0.03017 0.02208 0.0352 0.2491 1.0000
10.750 1.1265 0.03154 0.02362 0.0373 0.2421 1.0000
11.000 1.1314 0.03242 0.02454 0.0392 0.2356 1.0000
11.250 1.1233 0.03397 0.02615 0.0417 0.2294 1.0000
11.500 1.1053 0.03681 0.02908 0.0426 0.2230 1.0000
11.750 1.1008 0.03903 0.03129 0.0428 0.2163 1.0000
12.000 1.0789 0.04334 0.03571 0.0420 0.2089 1.0000
12.250 1.0758 0.04573 0.03806 0.0419 0.2018 1.0000
12.500 1.0521 0.05071 0.04313 0.0405 0.1943 1.0000
12.750 1.0495 0.05331 0.04569 0.0402 0.1873 1.0000
13.000 1.0301 0.05820 0.05065 0.0387 0.1799 1.0000
13.250 1.0290 0.06078 0.05319 0.0383 0.1732 1.0000
13.500 1.0138 0.06542 0.05789 0.0368 0.1664 1.0000
13.750 1.0175 0.06747 0.05989 0.0365 0.1603 1.0000
14.000 1.0034 0.07237 0.06487 0.0347 0.1540 1.0000
14.250 1.0163 0.07319 0.06558 0.0350 0.1488 1.0000
14.500 0.9985 0.07892 0.07144 0.0328 0.1431 1.0000
14.750 1.0010 0.08149 0.07399 0.0321 0.1380 1.0000
15.000 1.0011 0.08450 0.07700 0.0312 0.1332 1.0000
15.250 0.9916 0.08917 0.08176 0.0294 0.1282 1.0000
15.500 1.0022 0.09049 0.08301 0.0293 0.1239 1.0000
15.750 0.9913 0.09554 0.08816 0.0273 0.1193 1.0000
16.000 0.9853 0.09984 0.09253 0.0256 0.1148 1.0000
16.250 0.9999 0.10049 0.09309 0.0258 0.1110 1.0000
16.500 0.9809 0.10725 0.10001 0.0228 0.1068 1.0000
16.750 0.9746 0.11181 0.10463 0.0208 0.1025 1.0000
17.000 0.9919 0.11197 0.10470 0.0211 0.0993 1.0000
17.250 0.9603 0.12146 0.11440 0.0166 0.0950 1.0000
17.500 0.9506 0.12694 0.11996 0.0141 0.0913 1.0000
17.750 0.9691 0.12685 0.11981 0.0144 0.0889 1.0000
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