FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.27 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fauvel-il-1000000.txt Download as CSV file: xf-fauvel-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0214 0.06221 0.05975 -0.0221 1.0000 0.0183
-14.750 -1.0788 0.05088 0.04806 -0.0291 1.0000 0.0183
-14.500 -1.0868 0.04757 0.04465 -0.0297 1.0000 0.0185
-14.250 -1.0810 0.04441 0.04065 -0.0332 0.6985 0.0187
-14.000 -1.0972 0.04134 0.03733 -0.0316 0.6774 0.0188
-13.750 -1.1064 0.03903 0.03484 -0.0294 0.6659 0.0189
-13.500 -1.1139 0.03701 0.03262 -0.0268 0.6569 0.0191
-13.250 -1.1195 0.03517 0.03060 -0.0238 0.6504 0.0193
-13.000 -1.1199 0.03384 0.02911 -0.0207 0.6443 0.0195
-12.750 -1.1207 0.03248 0.02757 -0.0173 0.6394 0.0197
-12.500 -1.1170 0.03152 0.02648 -0.0140 0.6357 0.0198
-12.250 -1.1098 0.03108 0.02594 -0.0108 0.6320 0.0200
-12.000 -1.1133 0.02882 0.02344 -0.0069 0.6287 0.0203
-11.750 -1.1009 0.02782 0.02238 -0.0048 0.6250 0.0206
-11.500 -1.0850 0.02725 0.02175 -0.0030 0.6210 0.0208
-11.250 -1.0680 0.02668 0.02113 -0.0013 0.6183 0.0210
-11.000 -1.0504 0.02607 0.02047 0.0003 0.6152 0.0212
-10.750 -1.0320 0.02551 0.01985 0.0018 0.6118 0.0215
-10.500 -1.0131 0.02491 0.01917 0.0033 0.6085 0.0217
-10.250 -0.9939 0.02427 0.01843 0.0047 0.6049 0.0220
-10.000 -0.9742 0.02355 0.01762 0.0061 0.6022 0.0224
-9.750 -0.9538 0.02287 0.01684 0.0074 0.5993 0.0228
-9.500 -0.9330 0.02218 0.01602 0.0087 0.5959 0.0231
-9.250 -0.9113 0.02170 0.01543 0.0100 0.5926 0.0234
-9.000 -0.8890 0.02143 0.01504 0.0111 0.5892 0.0236
-8.750 -0.8685 0.01973 0.01326 0.0121 0.5861 0.0242
-8.500 -0.8451 0.01918 0.01270 0.0130 0.5829 0.0246
-8.250 -0.8213 0.01876 0.01226 0.0139 0.5795 0.0250
-8.000 -0.7972 0.01829 0.01174 0.0147 0.5761 0.0253
-7.750 -0.7730 0.01783 0.01122 0.0155 0.5723 0.0257
-7.500 -0.7483 0.01736 0.01070 0.0163 0.5689 0.0262
-7.250 -0.7234 0.01686 0.01015 0.0171 0.5649 0.0266
-7.000 -0.6982 0.01642 0.00965 0.0178 0.5608 0.0269
-6.750 -0.6729 0.01608 0.00924 0.0186 0.5566 0.0273
-6.500 -0.6470 0.01592 0.00902 0.0192 0.5526 0.0276
-6.250 -0.6237 0.01471 0.00781 0.0201 0.5482 0.0283
-6.000 -0.5987 0.01423 0.00733 0.0208 0.5429 0.0288
-5.750 -0.5735 0.01385 0.00692 0.0216 0.5375 0.0292
-5.500 -0.5477 0.01349 0.00655 0.0222 0.5320 0.0297
-5.250 -0.5221 0.01314 0.00617 0.0229 0.5257 0.0301
-5.000 -0.4964 0.01282 0.00582 0.0236 0.5195 0.0306
-4.750 -0.4704 0.01252 0.00549 0.0242 0.5119 0.0311
-4.500 -0.4441 0.01230 0.00522 0.0248 0.5035 0.0316
-4.250 -0.4177 0.01208 0.00497 0.0254 0.4943 0.0319
-4.000 -0.3938 0.01159 0.00442 0.0264 0.4849 0.0325
-3.750 -0.3687 0.01124 0.00405 0.0272 0.4753 0.0332
-3.500 -0.3428 0.01101 0.00379 0.0278 0.4662 0.0338
-3.250 -0.3166 0.01082 0.00357 0.0284 0.4567 0.0345
-3.000 -0.2902 0.01065 0.00336 0.0290 0.4479 0.0353
-2.750 -0.2636 0.01051 0.00318 0.0295 0.4392 0.0361
-2.500 -0.2367 0.01040 0.00303 0.0300 0.4316 0.0368
-2.250 -0.2106 0.01019 0.00279 0.0306 0.4247 0.0379
-2.000 -0.1842 0.01005 0.00263 0.0312 0.4174 0.0393
-1.750 -0.1572 0.00992 0.00250 0.0316 0.4120 0.0408
-1.500 -0.1301 0.00983 0.00238 0.0320 0.4057 0.0423
-1.250 -0.1036 0.00973 0.00226 0.0326 0.3988 0.0465
-1.000 -0.0775 0.00950 0.00216 0.0332 0.3946 0.0682
-0.750 -0.0536 0.00913 0.00202 0.0341 0.3898 0.1307
-0.500 -0.0308 0.00872 0.00195 0.0351 0.3847 0.2324
-0.250 -0.0046 0.00859 0.00191 0.0356 0.3798 0.2671
0.000 0.0208 0.00836 0.00186 0.0363 0.3757 0.3200
0.250 0.0388 0.00760 0.00169 0.0381 0.3715 0.4947
0.500 0.0522 0.00683 0.00162 0.0411 0.3674 0.7018
0.750 0.0748 0.00667 0.00165 0.0426 0.3629 0.7653
1.000 0.0994 0.00655 0.00170 0.0436 0.3600 0.8098
1.250 0.1261 0.00653 0.00174 0.0443 0.3563 0.8345
1.500 0.1534 0.00656 0.00178 0.0447 0.3521 0.8515
1.750 0.1800 0.00663 0.00186 0.0453 0.3471 0.8719
2.000 0.2078 0.00666 0.00193 0.0457 0.3442 0.8860
2.250 0.2355 0.00670 0.00200 0.0461 0.3413 0.9006
2.500 0.2624 0.00677 0.00207 0.0466 0.3379 0.9140
2.750 0.2915 0.00686 0.00215 0.0466 0.3342 0.9222
3.000 0.3183 0.00699 0.00224 0.0471 0.3297 0.9303
3.250 0.3487 0.00706 0.00233 0.0469 0.3270 0.9359
3.500 0.3763 0.00712 0.00240 0.0471 0.3243 0.9421
3.750 0.4066 0.00721 0.00248 0.0468 0.3210 0.9465
4.000 0.4372 0.00732 0.00257 0.0464 0.3169 0.9503
4.250 0.4653 0.00749 0.00269 0.0465 0.3120 0.9552
4.500 0.4956 0.00755 0.00277 0.0462 0.3095 0.9590
4.750 0.5299 0.00765 0.00288 0.0450 0.3058 0.9617
5.000 0.5632 0.00778 0.00299 0.0440 0.3018 0.9645
5.250 0.5934 0.00796 0.00312 0.0436 0.2968 0.9677
5.500 0.6229 0.00805 0.00323 0.0434 0.2936 0.9710
5.750 0.6595 0.00816 0.00334 0.0416 0.2902 0.9720
6.000 0.6972 0.00830 0.00347 0.0396 0.2861 0.9729
6.250 0.7331 0.00849 0.00363 0.0379 0.2814 0.9741
6.500 0.7673 0.00862 0.00377 0.0366 0.2780 0.9754
6.750 0.8009 0.00872 0.00388 0.0354 0.2743 0.9770
7.000 0.8327 0.00885 0.00400 0.0345 0.2689 0.9792
7.250 0.8604 0.00906 0.00418 0.0345 0.2636 0.9824
7.500 0.8956 0.00914 0.00428 0.0329 0.2595 0.9832
7.750 0.9300 0.00928 0.00441 0.0315 0.2533 0.9840
8.000 0.9640 0.00947 0.00458 0.0300 0.2471 0.9851
8.250 0.9975 0.00960 0.00472 0.0287 0.2406 0.9864
8.500 1.0299 0.00984 0.00492 0.0276 0.2324 0.9879
8.750 1.0620 0.01002 0.00510 0.0265 0.2243 0.9897
9.000 1.0924 0.01028 0.00534 0.0257 0.2161 0.9917
9.250 1.1225 0.01058 0.00560 0.0249 0.2054 0.9934
9.500 1.1554 0.01088 0.00586 0.0235 0.1934 0.9944
9.750 1.1869 0.01131 0.00622 0.0221 0.1781 0.9958
10.000 1.2175 0.01184 0.00666 0.0209 0.1616 0.9973
10.250 1.2477 0.01240 0.00715 0.0197 0.1461 0.9988
10.500 1.2773 0.01298 0.00766 0.0185 0.1339 1.0000
10.750 1.2938 0.01346 0.00813 0.0201 0.1263 1.0000
11.000 1.3102 0.01392 0.00858 0.0217 0.1202 1.0000
11.250 1.3259 0.01441 0.00906 0.0234 0.1148 1.0000
11.500 1.3408 0.01492 0.00957 0.0252 0.1097 1.0000
11.750 1.3564 0.01536 0.01004 0.0269 0.1056 1.0000
12.000 1.3692 0.01597 0.01063 0.0288 0.1008 1.0000
12.250 1.3833 0.01648 0.01117 0.0306 0.0969 1.0000
12.500 1.3955 0.01709 0.01179 0.0326 0.0922 1.0000
12.750 1.4050 0.01784 0.01254 0.0347 0.0873 1.0000
13.000 1.4136 0.01862 0.01332 0.0368 0.0824 1.0000
13.250 1.4135 0.01973 0.01444 0.0397 0.0772 1.0000
13.500 1.4044 0.02147 0.01624 0.0422 0.0737 1.0000
13.750 1.3970 0.02498 0.01980 0.0407 0.0689 1.0000
14.000 1.3916 0.02794 0.02281 0.0402 0.0647 1.0000
14.250 1.3809 0.03133 0.02622 0.0398 0.0610 1.0000
14.500 1.3730 0.03446 0.02940 0.0395 0.0581 1.0000
14.750 1.3604 0.03813 0.03311 0.0389 0.0556 1.0000
15.000 1.3495 0.04173 0.03678 0.0383 0.0534 1.0000
15.250 1.3402 0.04528 0.04039 0.0376 0.0517 1.0000
15.500 1.3294 0.04911 0.04428 0.0366 0.0503 1.0000
15.750 1.3156 0.05349 0.04871 0.0354 0.0486 1.0000
16.000 1.3055 0.05757 0.05286 0.0342 0.0475 1.0000
16.250 1.3004 0.06109 0.05644 0.0331 0.0467 1.0000
16.500 1.2935 0.06491 0.06034 0.0319 0.0460 1.0000
16.750 1.2850 0.06897 0.06447 0.0305 0.0452 1.0000
17.000 1.2781 0.07286 0.06842 0.0292 0.0445 1.0000
17.250 1.2688 0.07715 0.07276 0.0277 0.0438 1.0000
17.500 1.2596 0.08148 0.07714 0.0261 0.0431 1.0000
17.750 1.2513 0.08573 0.08144 0.0246 0.0423 1.0000
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Polar data table (+)
Polar graphs
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