FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.01 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fauvel-il-1000000-n5.txt Download as CSV file: xf-fauvel-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.3326 0.05422 0.05078 -0.0309 1.0000 0.0144
-17.500 -1.3463 0.04928 0.04571 -0.0331 1.0000 0.0145
-17.000 -1.3618 0.04230 0.03850 -0.0343 1.0000 0.0146
-16.500 -1.3630 0.03773 0.03377 -0.0332 1.0000 0.0149
-16.000 -1.3357 0.03451 0.02991 -0.0348 0.7509 0.0151
-15.750 -1.3353 0.03317 0.02827 -0.0327 0.6690 0.0152
-15.500 -1.3306 0.03193 0.02689 -0.0308 0.6523 0.0153
-15.250 -1.3242 0.03082 0.02569 -0.0289 0.6432 0.0155
-15.000 -1.3171 0.02978 0.02454 -0.0268 0.6365 0.0156
-14.750 -1.3100 0.02876 0.02342 -0.0246 0.6316 0.0158
-14.500 -1.3002 0.02793 0.02251 -0.0225 0.6268 0.0160
-14.000 -1.2808 0.02627 0.02067 -0.0180 0.6189 0.0163
-13.750 -1.2685 0.02560 0.01991 -0.0158 0.6154 0.0165
-13.500 -1.2576 0.02484 0.01906 -0.0134 0.6123 0.0166
-13.250 -1.2449 0.02420 0.01832 -0.0111 0.6089 0.0167
-12.750 -1.2189 0.02297 0.01695 -0.0063 0.6013 0.0171
-12.500 -1.2047 0.02244 0.01638 -0.0040 0.5974 0.0173
-12.250 -1.1883 0.02195 0.01583 -0.0021 0.5939 0.0174
-12.000 -1.1693 0.02151 0.01535 -0.0005 0.5909 0.0176
-11.500 -1.1293 0.02066 0.01441 0.0023 0.5855 0.0180
-11.250 -1.1085 0.02025 0.01394 0.0036 0.5829 0.0182
-11.000 -1.0875 0.01981 0.01345 0.0048 0.5801 0.0184
-10.750 -1.0660 0.01939 0.01298 0.0060 0.5770 0.0186
-10.500 -1.0443 0.01897 0.01249 0.0072 0.5738 0.0189
-10.250 -1.0220 0.01857 0.01203 0.0083 0.5710 0.0191
-10.000 -0.9991 0.01819 0.01161 0.0094 0.5683 0.0194
-9.750 -0.9758 0.01783 0.01120 0.0104 0.5653 0.0197
-9.500 -0.9530 0.01740 0.01070 0.0114 0.5618 0.0198
-9.250 -0.9290 0.01709 0.01033 0.0123 0.5581 0.0200
-9.000 -0.9069 0.01656 0.00975 0.0135 0.5550 0.0203
-8.750 -0.8835 0.01614 0.00930 0.0144 0.5518 0.0206
-8.500 -0.8594 0.01577 0.00892 0.0153 0.5480 0.0208
-8.250 -0.8349 0.01545 0.00857 0.0161 0.5439 0.0210
-8.000 -0.8101 0.01516 0.00824 0.0169 0.5399 0.0213
-7.750 -0.7851 0.01487 0.00792 0.0177 0.5361 0.0216
-7.500 -0.7600 0.01458 0.00760 0.0184 0.5316 0.0219
-7.250 -0.7345 0.01432 0.00731 0.0191 0.5256 0.0223
-7.000 -0.7093 0.01404 0.00698 0.0198 0.5200 0.0226
-6.750 -0.6839 0.01375 0.00665 0.0205 0.5141 0.0229
-6.500 -0.6584 0.01347 0.00633 0.0212 0.5071 0.0232
-6.250 -0.6327 0.01322 0.00604 0.0219 0.5003 0.0234
-6.000 -0.6068 0.01299 0.00576 0.0225 0.4908 0.0236
-5.750 -0.5820 0.01265 0.00537 0.0233 0.4815 0.0239
-5.500 -0.5567 0.01237 0.00505 0.0241 0.4709 0.0244
-5.250 -0.5307 0.01216 0.00481 0.0247 0.4624 0.0248
-5.000 -0.5046 0.01196 0.00458 0.0253 0.4531 0.0252
-4.750 -0.4784 0.01177 0.00435 0.0258 0.4452 0.0255
-4.500 -0.4522 0.01159 0.00413 0.0264 0.4361 0.0259
-4.250 -0.4258 0.01142 0.00393 0.0270 0.4286 0.0263
-4.000 -0.3993 0.01127 0.00373 0.0275 0.4202 0.0267
-3.750 -0.3727 0.01112 0.00355 0.0280 0.4142 0.0271
-3.500 -0.3459 0.01097 0.00338 0.0285 0.4084 0.0274
-3.250 -0.3194 0.01082 0.00320 0.0290 0.4022 0.0279
-3.000 -0.2930 0.01065 0.00302 0.0296 0.3965 0.0287
-2.750 -0.2661 0.01051 0.00287 0.0301 0.3908 0.0293
-2.500 -0.2392 0.01040 0.00273 0.0305 0.3849 0.0299
-2.250 -0.2122 0.01030 0.00261 0.0309 0.3801 0.0306
-2.000 -0.1850 0.01019 0.00250 0.0313 0.3761 0.0313
-1.750 -0.1577 0.01010 0.00240 0.0317 0.3713 0.0319
-1.500 -0.1307 0.01001 0.00229 0.0321 0.3661 0.0332
-1.250 -0.1035 0.00993 0.00220 0.0325 0.3615 0.0348
-1.000 -0.0761 0.00984 0.00213 0.0329 0.3575 0.0368
-0.750 -0.0490 0.00975 0.00205 0.0333 0.3534 0.0422
-0.500 -0.0229 0.00958 0.00197 0.0338 0.3493 0.0686
-0.250 0.0036 0.00945 0.00192 0.0343 0.3453 0.0919
0.000 0.0296 0.00925 0.00184 0.0349 0.3420 0.1290
0.250 0.0536 0.00891 0.00180 0.0357 0.3381 0.2182
0.500 0.0804 0.00882 0.00178 0.0361 0.3342 0.2455
0.750 0.1072 0.00874 0.00177 0.0365 0.3305 0.2748
1.000 0.1330 0.00856 0.00175 0.0370 0.3277 0.3249
1.250 0.1573 0.00825 0.00170 0.0378 0.3250 0.4086
1.500 0.1709 0.00731 0.00158 0.0406 0.3221 0.6574
1.750 0.1925 0.00705 0.00160 0.0421 0.3185 0.7374
2.000 0.2174 0.00698 0.00164 0.0430 0.3151 0.7777
2.250 0.2424 0.00693 0.00171 0.0439 0.3118 0.8167
2.500 0.2689 0.00691 0.00177 0.0445 0.3098 0.8437
2.750 0.2966 0.00693 0.00183 0.0448 0.3072 0.8586
3.000 0.3243 0.00697 0.00190 0.0451 0.3040 0.8710
3.250 0.3523 0.00703 0.00196 0.0453 0.3005 0.8802
3.500 0.3804 0.00711 0.00204 0.0454 0.2970 0.8881
3.750 0.4084 0.00718 0.00211 0.0456 0.2944 0.8956
4.000 0.4372 0.00724 0.00218 0.0456 0.2912 0.9016
4.250 0.4656 0.00731 0.00226 0.0456 0.2874 0.9080
4.500 0.4936 0.00741 0.00234 0.0457 0.2832 0.9141
4.750 0.5224 0.00752 0.00245 0.0457 0.2787 0.9219
5.000 0.5503 0.00760 0.00254 0.0458 0.2755 0.9292
5.250 0.5803 0.00770 0.00264 0.0455 0.2709 0.9337
5.500 0.6092 0.00783 0.00276 0.0454 0.2657 0.9388
5.750 0.6372 0.00795 0.00287 0.0454 0.2621 0.9445
6.000 0.6693 0.00806 0.00300 0.0446 0.2582 0.9495
6.250 0.6985 0.00820 0.00314 0.0444 0.2534 0.9555
6.500 0.7285 0.00837 0.00328 0.0439 0.2488 0.9592
6.750 0.7607 0.00850 0.00343 0.0430 0.2453 0.9615
7.000 0.7917 0.00867 0.00358 0.0423 0.2384 0.9642
7.250 0.8206 0.00887 0.00375 0.0420 0.2318 0.9678
7.500 0.8495 0.00903 0.00392 0.0417 0.2257 0.9710
7.750 0.8816 0.00929 0.00413 0.0406 0.2167 0.9723
8.000 0.9134 0.00957 0.00437 0.0396 0.2057 0.9737
8.250 0.9447 0.00984 0.00461 0.0386 0.1956 0.9754
8.500 0.9740 0.01023 0.00492 0.0380 0.1808 0.9775
8.750 1.0002 0.01076 0.00534 0.0378 0.1616 0.9806
9.000 1.0275 0.01125 0.00576 0.0374 0.1455 0.9829
9.250 1.0575 0.01175 0.00619 0.0363 0.1326 0.9841
9.500 1.0871 0.01224 0.00664 0.0353 0.1226 0.9856
9.750 1.1164 0.01267 0.00704 0.0345 0.1152 0.9873
10.000 1.1449 0.01312 0.00747 0.0338 0.1089 0.9893
10.250 1.1726 0.01353 0.00788 0.0332 0.1040 0.9914
10.500 1.1993 0.01402 0.00835 0.0328 0.0988 0.9934
10.750 1.2292 0.01441 0.00876 0.0317 0.0947 0.9948
11.000 1.2576 0.01498 0.00930 0.0307 0.0889 0.9965
11.250 1.2861 0.01546 0.00979 0.0298 0.0843 0.9981
11.500 1.3132 0.01613 0.01043 0.0288 0.0781 0.9994
11.750 1.3338 0.01673 0.01104 0.0292 0.0726 1.0000
12.000 1.3445 0.01740 0.01170 0.0313 0.0679 1.0000
12.250 1.3536 0.01815 0.01244 0.0335 0.0631 1.0000
12.500 1.3604 0.01900 0.01331 0.0359 0.0588 1.0000
12.750 1.3621 0.02006 0.01439 0.0386 0.0553 1.0000
13.000 1.3519 0.02178 0.01618 0.0413 0.0534 1.0000
13.250 1.3490 0.02477 0.01924 0.0401 0.0508 1.0000
13.500 1.3456 0.02754 0.02206 0.0396 0.0487 1.0000
13.750 1.3411 0.03032 0.02489 0.0394 0.0467 1.0000
14.000 1.3369 0.03309 0.02771 0.0392 0.0453 1.0000
14.250 1.3302 0.03616 0.03083 0.0388 0.0436 1.0000
14.500 1.3236 0.03928 0.03401 0.0384 0.0426 1.0000
14.750 1.3169 0.04250 0.03730 0.0378 0.0415 1.0000
15.000 1.3112 0.04570 0.04056 0.0371 0.0407 1.0000
15.250 1.3051 0.04902 0.04395 0.0363 0.0399 1.0000
15.500 1.2999 0.05241 0.04740 0.0354 0.0393 1.0000
15.750 1.2934 0.05604 0.05109 0.0344 0.0384 1.0000
16.000 1.2869 0.05972 0.05485 0.0333 0.0379 1.0000
16.250 1.2799 0.06355 0.05874 0.0320 0.0372 1.0000
16.500 1.2740 0.06726 0.06250 0.0309 0.0367 1.0000
16.750 1.2677 0.07108 0.06639 0.0296 0.0361 1.0000
17.000 1.2627 0.07481 0.07018 0.0283 0.0359 1.0000
17.250 1.2601 0.07820 0.07364 0.0272 0.0355 1.0000
17.500 1.2548 0.08204 0.07755 0.0258 0.0352 1.0000
17.750 1.2521 0.08554 0.08110 0.0245 0.0348 1.0000
18.000 1.2465 0.08949 0.08512 0.0231 0.0345 1.0000
18.250 1.2439 0.09302 0.08871 0.0218 0.0342 1.0000
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