FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 100,000 Max Cl/Cd: 26.3 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66196v-il-100000-n5.txt Download as CSV file: xf-fx66196v-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 V1 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2910 0.09557 0.09066 -0.0909 0.8979 0.0282
-13.000 -0.3207 0.08329 0.07826 -0.0998 0.8865 0.0277
-12.750 -0.3491 0.07391 0.06864 -0.1073 0.8721 0.0273
-12.500 -0.3741 0.06683 0.06127 -0.1125 0.8571 0.0271
-12.250 -0.3941 0.06143 0.05559 -0.1158 0.8418 0.0270
-12.000 -0.4109 0.05701 0.05088 -0.1178 0.8276 0.0270
-11.750 -0.4255 0.05314 0.04670 -0.1190 0.8149 0.0271
-11.500 -0.4358 0.04996 0.04322 -0.1193 0.8026 0.0273
-11.250 -0.4435 0.04706 0.04003 -0.1191 0.7911 0.0275
-11.000 -0.4472 0.04455 0.03721 -0.1186 0.7809 0.0278
-10.750 -0.4485 0.04219 0.03452 -0.1176 0.7711 0.0282
-10.500 -0.4482 0.04021 0.03219 -0.1162 0.7616 0.0289
-10.250 -0.4392 0.03852 0.03034 -0.1153 0.7538 0.0298
-10.000 -0.4294 0.03727 0.02899 -0.1142 0.7448 0.0308
-9.750 -0.4181 0.03605 0.02759 -0.1131 0.7379 0.0320
-9.500 -0.4024 0.03468 0.02604 -0.1122 0.7298 0.0332
-9.250 -0.3829 0.03329 0.02440 -0.1115 0.7235 0.0345
-9.000 -0.3624 0.03208 0.02296 -0.1108 0.7166 0.0358
-8.750 -0.3443 0.03097 0.02186 -0.1100 0.7103 0.0377
-8.500 -0.3278 0.03011 0.02091 -0.1091 0.7047 0.0400
-8.250 -0.3102 0.02928 0.01998 -0.1081 0.6982 0.0425
-8.000 -0.2921 0.02845 0.01901 -0.1069 0.6930 0.0448
-7.750 -0.2786 0.02758 0.01815 -0.1055 0.6880 0.0475
-7.500 -0.2639 0.02690 0.01742 -0.1043 0.6825 0.0516
-7.250 -0.2493 0.02616 0.01659 -0.1030 0.6780 0.0560
-7.000 -0.2350 0.02541 0.01578 -0.1017 0.6742 0.0612
-6.750 -0.2206 0.02473 0.01509 -0.1005 0.6691 0.0689
-6.500 -0.2053 0.02402 0.01435 -0.0994 0.6647 0.0803
-6.250 -0.1901 0.02317 0.01355 -0.0985 0.6611 0.0993
-6.000 -0.1752 0.02223 0.01277 -0.0976 0.6573 0.1357
-5.500 -0.1508 0.01984 0.01168 -0.0957 0.6490 0.3629
-5.250 -0.1260 0.02018 0.01211 -0.0949 0.6458 0.4547
-5.000 -0.0998 0.02044 0.01210 -0.0948 0.6427 0.4906
-4.750 -0.0749 0.02098 0.01259 -0.0939 0.6389 0.5127
-4.500 -0.0495 0.02149 0.01301 -0.0931 0.6355 0.5320
-4.250 -0.0237 0.02199 0.01340 -0.0923 0.6326 0.5496
-4.000 0.0026 0.02244 0.01373 -0.0914 0.6301 0.5633
-3.750 0.0296 0.02263 0.01376 -0.0911 0.6280 0.5737
-3.500 0.0538 0.02280 0.01386 -0.0907 0.6247 0.5809
-3.250 0.0792 0.02276 0.01367 -0.0908 0.6217 0.5872
-3.000 0.1050 0.02282 0.01365 -0.0906 0.6191 0.5906
-2.750 0.1315 0.02282 0.01353 -0.0907 0.6167 0.5951
-2.500 0.1591 0.02272 0.01322 -0.0913 0.6147 0.6002
-2.250 0.1872 0.02264 0.01299 -0.0917 0.6130 0.6033
-2.000 0.2122 0.02272 0.01303 -0.0916 0.6104 0.6058
-1.750 0.2366 0.02280 0.01306 -0.0915 0.6075 0.6085
-1.500 0.2621 0.02284 0.01303 -0.0917 0.6049 0.6116
-1.250 0.2888 0.02286 0.01293 -0.0921 0.6026 0.6153
-1.000 0.3160 0.02288 0.01284 -0.0925 0.6007 0.6186
-0.750 0.3430 0.02294 0.01284 -0.0927 0.5991 0.6209
-0.500 0.3709 0.02299 0.01281 -0.0930 0.5977 0.6233
-0.250 0.3962 0.02315 0.01294 -0.0931 0.5959 0.6261
0.000 0.4185 0.02344 0.01325 -0.0929 0.5935 0.6294
0.250 0.4422 0.02370 0.01348 -0.0930 0.5913 0.6328
0.500 0.4661 0.02395 0.01373 -0.0929 0.5893 0.6351
0.750 0.4904 0.02419 0.01398 -0.0928 0.5875 0.6374
1.000 0.5157 0.02441 0.01419 -0.0928 0.5859 0.6401
1.250 0.5422 0.02459 0.01434 -0.0931 0.5845 0.6431
1.500 0.5700 0.02473 0.01443 -0.0936 0.5831 0.6466
1.750 0.5987 0.02487 0.01452 -0.0942 0.5818 0.6503
2.000 0.6139 0.02555 0.01533 -0.0929 0.5793 0.6533
2.250 0.6282 0.02631 0.01620 -0.0915 0.5767 0.6567
2.500 0.6447 0.02700 0.01696 -0.0906 0.5745 0.6604
2.750 0.6640 0.02757 0.01756 -0.0900 0.5724 0.6645
3.000 0.6859 0.02799 0.01802 -0.0896 0.5705 0.6680
3.250 0.7097 0.02832 0.01840 -0.0894 0.5690 0.6718
3.500 0.7346 0.02866 0.01877 -0.0895 0.5677 0.6762
3.750 0.7617 0.02896 0.01908 -0.0899 0.5666 0.6814
4.000 0.7228 0.03219 0.02257 -0.0823 0.5593 0.6849
4.250 0.7190 0.03383 0.02431 -0.0790 0.5557 0.6895
4.500 0.7363 0.03452 0.02503 -0.0782 0.5537 0.6955
4.750 0.7610 0.03487 0.02545 -0.0782 0.5524 0.7013
5.000 0.7890 0.03509 0.02572 -0.0786 0.5513 0.7079
5.250 0.8179 0.03535 0.02602 -0.0791 0.5504 0.7153
5.750 0.6781 0.04936 0.04030 -0.0658 0.5236 0.7261
6.000 0.7035 0.04965 0.04067 -0.0658 0.5221 0.7347
6.250 0.7321 0.04970 0.04079 -0.0659 0.5209 0.7448
6.500 0.7601 0.04977 0.04098 -0.0660 0.5201 0.7552
7.000 0.7484 0.05528 0.04671 -0.0631 0.5062 0.7789
7.250 0.7745 0.05548 0.04704 -0.0630 0.5052 0.7969
7.750 0.7703 0.06017 0.05209 -0.0604 0.4917 0.8505
8.250 0.7822 0.06361 0.05576 -0.0594 0.4791 1.0000
8.750 0.8384 0.06396 0.05620 -0.0601 0.4753 1.0000
9.250 0.8495 0.06808 0.06043 -0.0594 0.4620 1.0000
9.500 0.8780 0.06813 0.06055 -0.0596 0.4605 1.0000
10.000 0.8941 0.07159 0.06415 -0.0589 0.4468 1.0000
10.250 0.9241 0.07127 0.06392 -0.0590 0.4452 1.0000
10.750 0.9402 0.07468 0.06750 -0.0583 0.4311 1.0000
12.250 1.0115 0.08221 0.07568 -0.0568 0.3893 1.0000
12.750 1.0430 0.08357 0.07730 -0.0562 0.3750 1.0000
13.000 1.0469 0.08572 0.07956 -0.0560 0.3637 1.0000
13.250 1.0849 0.08300 0.07700 -0.0553 0.3589 1.0000
13.500 1.0965 0.08386 0.07796 -0.0550 0.3446 1.0000
13.750 1.1043 0.08539 0.07956 -0.0547 0.3263 1.0000
14.000 1.1242 0.08522 0.07941 -0.0543 0.3037 1.0000
14.250 1.1489 0.08432 0.07835 -0.0536 0.2704 1.0000
14.500 1.1629 0.08490 0.07863 -0.0529 0.2302 1.0000
14.750 1.1625 0.08762 0.08106 -0.0527 0.1929 1.0000
15.000 1.1564 0.09138 0.08458 -0.0527 0.1594 1.0000
15.250 1.1480 0.09559 0.08855 -0.0531 0.1290 1.0000
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