FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 200,000 Max Cl/Cd: 60.48 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fauvel-il-200000-n5.txt Download as CSV file: xf-fauvel-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6965 0.07505 0.07055 -0.0120 0.6864 0.0276
-11.500 -0.7341 0.06569 0.06099 -0.0188 0.6833 0.0274
-11.250 -0.7725 0.05907 0.05410 -0.0209 0.6793 0.0274
-10.750 -0.8394 0.05004 0.04439 -0.0156 0.6705 0.0275
-10.500 -0.8591 0.04709 0.04113 -0.0112 0.6654 0.0276
-10.250 -0.8585 0.04504 0.03889 -0.0086 0.6596 0.0278
-10.000 -0.8542 0.04316 0.03683 -0.0063 0.6544 0.0281
-9.750 -0.8459 0.04149 0.03500 -0.0044 0.6490 0.0283
-9.500 -0.8363 0.03980 0.03313 -0.0024 0.6437 0.0287
-9.250 -0.8262 0.03803 0.03109 -0.0004 0.6390 0.0290
-9.000 -0.8141 0.03629 0.02912 0.0014 0.6342 0.0295
-8.750 -0.8009 0.03460 0.02716 0.0033 0.6290 0.0302
-8.500 -0.7873 0.03281 0.02499 0.0052 0.6243 0.0309
-8.250 -0.7720 0.03110 0.02286 0.0071 0.6198 0.0316
-8.000 -0.7537 0.02957 0.02100 0.0087 0.6147 0.0321
-7.750 -0.7318 0.02834 0.01968 0.0095 0.6094 0.0325
-7.500 -0.7096 0.02735 0.01857 0.0104 0.6047 0.0330
-7.250 -0.6864 0.02637 0.01749 0.0112 0.5992 0.0335
-7.000 -0.6629 0.02550 0.01650 0.0121 0.5936 0.0342
-6.750 -0.6391 0.02470 0.01555 0.0129 0.5887 0.0350
-6.500 -0.6146 0.02385 0.01456 0.0136 0.5832 0.0359
-6.250 -0.5895 0.02304 0.01358 0.0144 0.5772 0.0366
-6.000 -0.5643 0.02222 0.01265 0.0150 0.5721 0.0371
-5.750 -0.5389 0.02141 0.01186 0.0156 0.5660 0.0377
-5.500 -0.5137 0.02073 0.01118 0.0162 0.5600 0.0384
-5.250 -0.4888 0.02014 0.01053 0.0169 0.5548 0.0391
-5.000 -0.4634 0.01959 0.00997 0.0176 0.5477 0.0403
-4.750 -0.4383 0.01907 0.00938 0.0183 0.5411 0.0414
-4.500 -0.4131 0.01858 0.00882 0.0191 0.5349 0.0423
-4.250 -0.3888 0.01800 0.00827 0.0199 0.5277 0.0431
-4.000 -0.3645 0.01753 0.00778 0.0208 0.5217 0.0442
-3.750 -0.3397 0.01711 0.00737 0.0215 0.5138 0.0453
-3.500 -0.3150 0.01673 0.00693 0.0224 0.5064 0.0466
-3.000 -0.2651 0.01604 0.00620 0.0239 0.4912 0.0509
-2.750 -0.2398 0.01576 0.00587 0.0247 0.4846 0.0537
-2.500 -0.2145 0.01546 0.00558 0.0254 0.4768 0.0572
-2.250 -0.1893 0.01520 0.00527 0.0262 0.4700 0.0631
-2.000 -0.1642 0.01490 0.00504 0.0269 0.4623 0.0755
-1.750 -0.1399 0.01456 0.00477 0.0277 0.4553 0.1024
-1.500 -0.1182 0.01401 0.00455 0.0289 0.4494 0.1715
-1.250 -0.0951 0.01366 0.00444 0.0298 0.4430 0.2454
-1.000 -0.0714 0.01341 0.00428 0.0308 0.4371 0.2878
-0.750 -0.0509 0.01294 0.00410 0.0322 0.4316 0.3659
-0.500 -0.0469 0.01151 0.00407 0.0372 0.4266 0.6965
-0.250 -0.0185 0.01144 0.00428 0.0380 0.4206 0.7891
0.000 0.0129 0.01161 0.00447 0.0382 0.4157 0.8384
0.250 0.0470 0.01182 0.00471 0.0378 0.4099 0.8664
0.500 0.0804 0.01206 0.00489 0.0373 0.4043 0.8853
0.750 0.1091 0.01223 0.00494 0.0376 0.3995 0.8975
1.000 0.1443 0.01240 0.00506 0.0365 0.3942 0.9038
1.250 0.1702 0.01251 0.00512 0.0372 0.3896 0.9131
1.500 0.2070 0.01269 0.00522 0.0357 0.3849 0.9171
1.750 0.2403 0.01288 0.00529 0.0349 0.3808 0.9225
2.000 0.2680 0.01299 0.00540 0.0351 0.3762 0.9298
2.250 0.3060 0.01315 0.00553 0.0333 0.3712 0.9330
2.500 0.3409 0.01331 0.00562 0.0320 0.3671 0.9368
2.750 0.3684 0.01347 0.00569 0.0322 0.3638 0.9428
3.000 0.4046 0.01363 0.00585 0.0306 0.3595 0.9462
3.250 0.4415 0.01378 0.00600 0.0289 0.3549 0.9496
3.500 0.4737 0.01393 0.00612 0.0281 0.3509 0.9547
3.750 0.5048 0.01410 0.00623 0.0275 0.3475 0.9591
4.000 0.5393 0.01426 0.00637 0.0261 0.3442 0.9615
4.250 0.5718 0.01440 0.00655 0.0252 0.3403 0.9647
4.500 0.6009 0.01454 0.00670 0.0249 0.3362 0.9690
4.750 0.6328 0.01469 0.00683 0.0240 0.3326 0.9719
5.000 0.6661 0.01486 0.00695 0.0228 0.3295 0.9745
5.250 0.6982 0.01504 0.00717 0.0218 0.3259 0.9777
5.500 0.7278 0.01520 0.00740 0.0213 0.3214 0.9816
5.750 0.7610 0.01531 0.00751 0.0201 0.3163 0.9841
6.000 0.7938 0.01546 0.00760 0.0189 0.3113 0.9868
6.250 0.8259 0.01559 0.00784 0.0178 0.3052 0.9899
6.500 0.8569 0.01574 0.00802 0.0169 0.3001 0.9930
6.750 0.8897 0.01591 0.00814 0.0157 0.2959 0.9955
7.000 0.9223 0.01609 0.00844 0.0144 0.2911 0.9982
7.250 0.9518 0.01629 0.00870 0.0138 0.2865 1.0000
7.500 0.9726 0.01649 0.00891 0.0149 0.2824 1.0000
7.750 0.9931 0.01673 0.00916 0.0160 0.2783 1.0000
8.000 1.0138 0.01697 0.00952 0.0171 0.2734 1.0000
8.250 1.0340 0.01722 0.00981 0.0182 0.2686 1.0000
8.500 1.0538 0.01748 0.01007 0.0195 0.2642 1.0000
8.750 1.0736 0.01778 0.01047 0.0206 0.2587 1.0000
9.000 1.0929 0.01807 0.01081 0.0219 0.2525 1.0000
9.250 1.1115 0.01839 0.01115 0.0232 0.2462 1.0000
9.500 1.1298 0.01873 0.01156 0.0245 0.2377 1.0000
9.750 1.1469 0.01913 0.01198 0.0258 0.2282 1.0000
10.000 1.1625 0.01961 0.01244 0.0273 0.2177 1.0000
10.250 1.1777 0.02015 0.01301 0.0288 0.2063 1.0000
10.500 1.1917 0.02076 0.01365 0.0304 0.1962 1.0000
10.750 1.2034 0.02148 0.01437 0.0322 0.1868 1.0000
11.000 1.2128 0.02232 0.01521 0.0341 0.1769 1.0000
11.250 1.2200 0.02327 0.01618 0.0360 0.1676 1.0000
11.500 1.2219 0.02447 0.01739 0.0383 0.1595 1.0000
11.750 1.2161 0.02589 0.01883 0.0411 0.1530 1.0000
12.000 1.2043 0.02842 0.02140 0.0420 0.1479 1.0000
12.250 1.1995 0.03093 0.02395 0.0421 0.1422 1.0000
12.500 1.1913 0.03379 0.02683 0.0422 0.1371 1.0000
12.750 1.1856 0.03651 0.02959 0.0422 0.1328 1.0000
13.000 1.1794 0.03934 0.03246 0.0420 0.1284 1.0000
13.250 1.1704 0.04254 0.03569 0.0417 0.1245 1.0000
13.500 1.1638 0.04559 0.03879 0.0413 0.1209 1.0000
13.750 1.1582 0.04866 0.04192 0.0408 0.1170 1.0000
14.000 1.1507 0.05199 0.04529 0.0401 0.1136 1.0000
14.250 1.1419 0.05554 0.04884 0.0393 0.1104 1.0000
14.500 1.1396 0.05859 0.05199 0.0385 0.1069 1.0000
14.750 1.1349 0.06202 0.05546 0.0375 0.1033 1.0000
15.000 1.1284 0.06570 0.05916 0.0363 0.0999 1.0000
15.250 1.1251 0.06909 0.06262 0.0353 0.0965 1.0000
15.500 1.1215 0.07258 0.06619 0.0341 0.0929 1.0000
15.750 1.1153 0.07644 0.07007 0.0328 0.0894 1.0000
16.000 1.1117 0.08003 0.07371 0.0315 0.0862 1.0000
16.250 1.1078 0.08374 0.07748 0.0302 0.0827 1.0000
16.500 1.1026 0.08763 0.08139 0.0287 0.0797 1.0000
16.750 1.0987 0.09141 0.08522 0.0273 0.0767 1.0000
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