FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 500,000 Max Cl/Cd: 89.76 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fauvel-il-500000.txt Download as CSV file: xf-fauvel-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4549 0.14343 0.14030 0.0328 0.6382 0.0305
-12.750 -0.5288 0.13697 0.13357 0.0234 0.6535 0.0303
-12.500 -0.5571 0.12455 0.12119 0.0152 0.6546 0.0322
-12.250 -0.5480 0.12206 0.11869 0.0148 0.6504 0.0324
-12.000 -0.5387 0.11974 0.11635 0.0143 0.6458 0.0327
-11.750 -0.5323 0.11674 0.11331 0.0133 0.6418 0.0330
-11.500 -0.5267 0.11364 0.11019 0.0121 0.6381 0.0335
-11.250 -0.6178 0.08401 0.08063 -0.0119 0.6457 0.0369
-11.000 -0.5899 0.08877 0.08540 -0.0047 0.6392 0.0372
-10.750 -0.5943 0.08379 0.08044 -0.0075 0.6365 0.0374
-10.500 -0.5828 0.08339 0.08004 -0.0065 0.6320 0.0377
-10.250 -0.6471 0.06785 0.06439 -0.0181 0.6334 0.0378
-10.000 -0.6810 0.06256 0.05897 -0.0180 0.6317 0.0379
-9.750 -0.8187 0.04594 0.04140 -0.0070 0.6355 0.0314
-9.500 -0.8199 0.04278 0.03807 -0.0043 0.6321 0.0308
-9.250 -0.8305 0.03821 0.03308 -0.0003 0.6292 0.0304
-9.000 -0.8311 0.03456 0.02899 0.0031 0.6259 0.0304
-8.750 -0.8239 0.03184 0.02587 0.0059 0.6223 0.0307
-8.500 -0.8114 0.02981 0.02349 0.0082 0.6186 0.0312
-8.250 -0.7960 0.02874 0.02206 0.0105 0.6145 0.0318
-8.000 -0.7797 0.02658 0.01960 0.0122 0.6104 0.0322
-7.750 -0.7581 0.02477 0.01765 0.0131 0.6061 0.0327
-7.500 -0.7346 0.02373 0.01656 0.0138 0.6016 0.0332
-7.250 -0.7104 0.02286 0.01565 0.0146 0.5969 0.0337
-7.000 -0.6862 0.02199 0.01467 0.0154 0.5925 0.0342
-6.750 -0.6618 0.02122 0.01377 0.0162 0.5880 0.0348
-6.500 -0.6368 0.02046 0.01292 0.0169 0.5830 0.0356
-6.250 -0.6115 0.01977 0.01210 0.0177 0.5776 0.0362
-6.000 -0.5859 0.01915 0.01135 0.0184 0.5728 0.0366
-5.750 -0.5600 0.01856 0.01066 0.0191 0.5678 0.0370
-5.500 -0.5333 0.01725 0.00936 0.0194 0.5621 0.0377
-5.250 -0.5076 0.01657 0.00867 0.0200 0.5567 0.0383
-5.000 -0.4818 0.01607 0.00817 0.0206 0.5506 0.0392
-4.750 -0.4559 0.01558 0.00767 0.0212 0.5438 0.0400
-4.500 -0.4304 0.01513 0.00715 0.0220 0.5379 0.0407
-4.250 -0.4045 0.01467 0.00669 0.0227 0.5306 0.0413
-4.000 -0.3789 0.01428 0.00624 0.0234 0.5235 0.0419
-3.750 -0.3536 0.01386 0.00579 0.0242 0.5158 0.0425
-3.500 -0.3297 0.01331 0.00523 0.0252 0.5076 0.0436
-3.250 -0.3045 0.01297 0.00489 0.0259 0.4993 0.0449
-3.000 -0.2789 0.01269 0.00458 0.0266 0.4907 0.0463
-2.750 -0.2531 0.01244 0.00429 0.0273 0.4827 0.0475
-2.500 -0.2274 0.01219 0.00400 0.0281 0.4742 0.0489
-2.250 -0.2020 0.01193 0.00373 0.0288 0.4663 0.0512
-2.000 -0.1758 0.01175 0.00352 0.0294 0.4580 0.0540
-1.750 -0.1501 0.01157 0.00332 0.0301 0.4506 0.0592
-1.500 -0.1248 0.01130 0.00316 0.0308 0.4436 0.0769
-1.250 -0.1049 0.01061 0.00293 0.0323 0.4375 0.1917
-1.000 -0.0812 0.01030 0.00286 0.0332 0.4315 0.2663
-0.750 -0.0569 0.01001 0.00276 0.0341 0.4253 0.3202
-0.500 -0.0400 0.00925 0.00253 0.0361 0.4197 0.4669
-0.250 -0.0324 0.00828 0.00249 0.0404 0.4152 0.7211
0.000 -0.0097 0.00810 0.00258 0.0421 0.4102 0.7934
0.250 0.0161 0.00811 0.00267 0.0430 0.4051 0.8341
0.500 0.0423 0.00822 0.00276 0.0439 0.3999 0.8603
0.750 0.0698 0.00829 0.00285 0.0444 0.3954 0.8785
1.000 0.0983 0.00837 0.00295 0.0448 0.3904 0.8932
1.250 0.1272 0.00853 0.00309 0.0451 0.3857 0.9090
1.500 0.1576 0.00879 0.00328 0.0451 0.3809 0.9209
1.750 0.1878 0.00894 0.00345 0.0452 0.3773 0.9319
2.000 0.2226 0.00912 0.00361 0.0442 0.3729 0.9379
2.250 0.2507 0.00926 0.00369 0.0445 0.3686 0.9448
2.500 0.2884 0.00952 0.00386 0.0427 0.3637 0.9472
2.750 0.3252 0.00964 0.00399 0.0411 0.3603 0.9496
3.000 0.3606 0.00977 0.00410 0.0397 0.3564 0.9525
3.250 0.3883 0.00988 0.00419 0.0399 0.3528 0.9581
3.500 0.4273 0.01006 0.00431 0.0377 0.3487 0.9591
3.750 0.4664 0.01027 0.00448 0.0355 0.3445 0.9605
4.000 0.5047 0.01038 0.00461 0.0335 0.3410 0.9624
4.250 0.5400 0.01050 0.00472 0.0321 0.3373 0.9650
4.500 0.5679 0.01062 0.00481 0.0321 0.3333 0.9699
4.750 0.6053 0.01085 0.00496 0.0302 0.3284 0.9717
5.000 0.6452 0.01091 0.00508 0.0278 0.3244 0.9736
5.250 0.6813 0.01099 0.00516 0.0261 0.3201 0.9759
5.500 0.7142 0.01110 0.00524 0.0250 0.3153 0.9786
5.750 0.7431 0.01129 0.00541 0.0247 0.3110 0.9824
6.000 0.7798 0.01133 0.00549 0.0229 0.3073 0.9837
6.250 0.8156 0.01139 0.00558 0.0212 0.3032 0.9854
6.500 0.8502 0.01151 0.00567 0.0197 0.2990 0.9875
6.750 0.8832 0.01169 0.00584 0.0185 0.2947 0.9900
7.000 0.9158 0.01177 0.00599 0.0174 0.2910 0.9926
7.250 0.9508 0.01182 0.00607 0.0158 0.2861 0.9944
7.500 0.9852 0.01195 0.00616 0.0142 0.2808 0.9964
7.750 1.0198 0.01202 0.00629 0.0127 0.2755 0.9985
8.000 1.0527 0.01209 0.00639 0.0114 0.2693 1.0000
8.250 1.0738 0.01229 0.00655 0.0124 0.2638 1.0000
8.500 1.0964 0.01236 0.00670 0.0133 0.2578 1.0000
8.750 1.1175 0.01253 0.00686 0.0143 0.2508 1.0000
9.000 1.1388 0.01271 0.00708 0.0154 0.2444 1.0000
9.250 1.1597 0.01292 0.00730 0.0164 0.2373 1.0000
9.500 1.1799 0.01318 0.00757 0.0176 0.2306 1.0000
9.750 1.2000 0.01345 0.00785 0.0187 0.2224 1.0000
10.000 1.2193 0.01377 0.00818 0.0199 0.2139 1.0000
10.250 1.2371 0.01420 0.00857 0.0213 0.2035 1.0000
10.500 1.2548 0.01462 0.00899 0.0227 0.1921 1.0000
10.750 1.2708 0.01515 0.00950 0.0243 0.1796 1.0000
11.000 1.2849 0.01579 0.01010 0.0260 0.1669 1.0000
11.250 1.2977 0.01650 0.01077 0.0279 0.1557 1.0000
11.500 1.3089 0.01728 0.01152 0.0299 0.1462 1.0000
11.750 1.3189 0.01810 0.01232 0.0320 0.1381 1.0000
12.000 1.3283 0.01891 0.01316 0.0340 0.1317 1.0000
12.250 1.3341 0.01990 0.01415 0.0363 0.1259 1.0000
12.500 1.3368 0.02103 0.01531 0.0387 0.1212 1.0000
12.750 1.3310 0.02239 0.01674 0.0417 0.1178 1.0000
13.000 1.3230 0.02535 0.01977 0.0412 0.1143 1.0000
13.250 1.3135 0.02854 0.02300 0.0409 0.1106 1.0000
13.500 1.3142 0.03073 0.02526 0.0409 0.1072 1.0000
13.750 1.3086 0.03352 0.02810 0.0408 0.1035 1.0000
14.000 1.2973 0.03693 0.03153 0.0405 0.1002 1.0000
14.250 1.2927 0.03979 0.03446 0.0402 0.0968 1.0000
14.500 1.2865 0.04288 0.03761 0.0397 0.0929 1.0000
14.750 1.2743 0.04668 0.04143 0.0390 0.0894 1.0000
15.000 1.2665 0.05013 0.04494 0.0382 0.0854 1.0000
15.250 1.2575 0.05394 0.04878 0.0371 0.0814 1.0000
15.500 1.2449 0.05828 0.05315 0.0358 0.0778 1.0000
15.750 1.2376 0.06208 0.05700 0.0347 0.0737 1.0000
16.000 1.2253 0.06655 0.06149 0.0332 0.0707 1.0000
16.250 1.2173 0.07055 0.06553 0.0319 0.0678 1.0000
16.500 1.2115 0.07433 0.06935 0.0306 0.0653 1.0000
16.750 1.2007 0.07881 0.07384 0.0290 0.0628 1.0000
17.000 1.1931 0.08289 0.07795 0.0276 0.0611 1.0000
17.250 1.1914 0.08624 0.08136 0.0265 0.0594 1.0000
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