FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 50,000 Max Cl/Cd: 9.51 at α=16° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s196-il-50000-n5.txt Download as CSV file: xf-fx66s196-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2476 0.10745 0.10101 -0.0914 0.9160 0.0559
-12.500 -0.2564 0.09839 0.09192 -0.0979 0.9073 0.0551
-12.000 -0.3601 0.07368 0.06665 -0.1166 0.8889 0.0511
-11.750 -0.3765 0.06877 0.06146 -0.1197 0.8776 0.0511
-11.500 -0.3913 0.06484 0.05726 -0.1213 0.8656 0.0511
-11.250 -0.4024 0.06142 0.05361 -0.1219 0.8549 0.0513
-11.000 -0.4069 0.05839 0.05032 -0.1220 0.8457 0.0517
-10.750 -0.4105 0.05594 0.04767 -0.1214 0.8356 0.0522
-10.500 -0.4099 0.05363 0.04514 -0.1206 0.8275 0.0530
-10.250 -0.4081 0.05162 0.04293 -0.1194 0.8194 0.0538
-10.000 -0.4040 0.04992 0.04102 -0.1181 0.8125 0.0554
-9.750 -0.3978 0.04829 0.03916 -0.1168 0.8050 0.0574
-9.500 -0.3863 0.04646 0.03693 -0.1158 0.7996 0.0599
-9.250 -0.3734 0.04489 0.03498 -0.1146 0.7924 0.0623
-9.000 -0.3390 0.04316 0.03324 -0.1150 0.7877 0.0659
-8.750 -0.3095 0.04195 0.03183 -0.1150 0.7832 0.0715
-8.500 -0.2778 0.04102 0.03081 -0.1147 0.7779 0.0779
-8.250 -0.2552 0.04024 0.02989 -0.1137 0.7734 0.0861
-8.000 -0.2350 0.03940 0.02905 -0.1125 0.7697 0.0944
-7.750 -0.2248 0.03886 0.02849 -0.1106 0.7640 0.1040
-7.500 -0.2166 0.03816 0.02780 -0.1087 0.7590 0.1156
-7.250 -0.2114 0.03726 0.02698 -0.1065 0.7550 0.1287
-7.000 -0.2137 0.03659 0.02646 -0.1038 0.7496 0.1433
-6.750 -0.2165 0.03584 0.02587 -0.1009 0.7443 0.1638
-6.500 -0.2200 0.03474 0.02502 -0.0981 0.7403 0.1961
-6.250 -0.2270 0.03378 0.02446 -0.0948 0.7361 0.2447
-6.000 -0.2348 0.03353 0.02502 -0.0903 0.7309 0.3326
-5.750 -0.1985 0.03693 0.02895 -0.0854 0.7278 0.4651
-5.500 -0.2047 0.03590 0.02756 -0.0838 0.7241 0.5130
-5.250 -0.1951 0.03712 0.02860 -0.0805 0.7196 0.5413
-5.000 -0.1843 0.03856 0.02991 -0.0768 0.7148 0.5649
-4.750 -0.1694 0.03956 0.03070 -0.0739 0.7114 0.5899
-4.500 -0.1457 0.04062 0.03158 -0.0713 0.7090 0.6096
-4.250 -0.1239 0.04143 0.03220 -0.0690 0.7066 0.6264
-4.000 -0.1361 0.04223 0.03296 -0.0643 0.7001 0.6394
-3.750 -0.1182 0.04295 0.03355 -0.0616 0.6967 0.6504
-3.500 -0.0991 0.04318 0.03360 -0.0600 0.6942 0.6616
-3.250 -0.0799 0.04312 0.03332 -0.0590 0.6922 0.6732
-3.000 -0.0944 0.04420 0.03443 -0.0538 0.6862 0.6799
-2.750 -0.0911 0.04442 0.03452 -0.0516 0.6820 0.6890
-2.500 -0.0729 0.04458 0.03452 -0.0503 0.6792 0.6948
-2.250 -0.0518 0.04440 0.03413 -0.0504 0.6771 0.7023
-2.000 -0.0645 0.04538 0.03511 -0.0461 0.6723 0.7074
-1.750 -0.0689 0.04612 0.03581 -0.0430 0.6680 0.7132
-1.500 -0.0532 0.04628 0.03579 -0.0429 0.6650 0.7196
-1.250 -0.0314 0.04642 0.03580 -0.0425 0.6628 0.7232
-1.000 -0.0046 0.04645 0.03566 -0.0430 0.6611 0.7269
-0.750 -0.0161 0.04771 0.03690 -0.0401 0.6558 0.7313
-0.500 -0.0045 0.04838 0.03745 -0.0399 0.6529 0.7356
-0.250 0.0122 0.04889 0.03787 -0.0394 0.6503 0.7385
0.000 0.0347 0.04922 0.03808 -0.0396 0.6480 0.7415
0.250 0.0611 0.04948 0.03820 -0.0404 0.6461 0.7449
0.500 0.0691 0.05045 0.03910 -0.0398 0.6424 0.7486
0.750 0.0771 0.05148 0.04007 -0.0392 0.6389 0.7519
1.000 0.0924 0.05218 0.04072 -0.0387 0.6358 0.7551
1.250 0.1139 0.05273 0.04119 -0.0389 0.6332 0.7591
1.500 0.1398 0.05322 0.04158 -0.0396 0.6310 0.7635
1.750 0.1697 0.05367 0.04193 -0.0410 0.6294 0.7671
2.000 0.1632 0.05524 0.04352 -0.0390 0.6240 0.7698
2.250 0.1788 0.05611 0.04435 -0.0389 0.6205 0.7725
2.500 0.1999 0.05688 0.04507 -0.0393 0.6179 0.7757
2.750 0.2249 0.05760 0.04574 -0.0402 0.6158 0.7789
3.000 0.2549 0.05821 0.04628 -0.0416 0.6139 0.7819
3.250 0.2521 0.05980 0.04790 -0.0402 0.6083 0.7846
3.500 0.2676 0.06084 0.04895 -0.0401 0.6049 0.7876
3.750 0.2889 0.06176 0.04986 -0.0407 0.6022 0.7909
4.000 0.3162 0.06251 0.05058 -0.0417 0.5998 0.7945
4.250 0.3295 0.06378 0.05186 -0.0418 0.5958 0.7985
4.500 0.3377 0.06510 0.05322 -0.0412 0.5909 0.8021
4.750 0.3582 0.06604 0.05419 -0.0415 0.5873 0.8065
5.000 0.3860 0.06677 0.05494 -0.0424 0.5845 0.8119
5.250 0.3949 0.06812 0.05634 -0.0419 0.5793 0.8171
5.500 0.4065 0.06935 0.05764 -0.0416 0.5741 0.8231
6.000 0.4564 0.07106 0.05949 -0.0428 0.5681 0.8371
6.250 0.4571 0.07285 0.06136 -0.0420 0.5614 0.8450
6.500 0.4738 0.07396 0.06258 -0.0420 0.5568 0.8540
6.750 0.4990 0.07484 0.06359 -0.0427 0.5536 0.8658
7.000 0.5135 0.07622 0.06509 -0.0429 0.5490 0.8809
7.250 0.5235 0.07776 0.06678 -0.0431 0.5424 0.9021
7.500 0.5521 0.07832 0.06750 -0.0447 0.5382 0.9912
7.750 0.5610 0.08010 0.06931 -0.0449 0.5313 1.0000
8.000 0.5822 0.08143 0.07068 -0.0461 0.5253 1.0000
8.250 0.6147 0.08233 0.07161 -0.0476 0.5219 1.0000
8.500 0.6147 0.08460 0.07394 -0.0476 0.5129 1.0000
8.750 0.6405 0.08573 0.07512 -0.0486 0.5084 1.0000
9.000 0.6524 0.08751 0.07696 -0.0490 0.5017 1.0000
9.250 0.6669 0.08916 0.07867 -0.0494 0.4951 1.0000
9.500 0.6958 0.09005 0.07965 -0.0503 0.4915 1.0000
9.750 0.6961 0.09231 0.08199 -0.0501 0.4816 1.0000
10.000 0.7249 0.09296 0.08272 -0.0507 0.4770 1.0000
10.250 0.7278 0.09507 0.08491 -0.0506 0.4671 1.0000
10.500 0.7558 0.09568 0.08565 -0.0511 0.4624 1.0000
10.750 0.7569 0.09806 0.08813 -0.0510 0.4526 1.0000
11.000 0.7839 0.09869 0.08887 -0.0514 0.4479 1.0000
11.250 0.7847 0.10114 0.09143 -0.0513 0.4376 1.0000
11.500 0.8138 0.10134 0.09179 -0.0515 0.4326 1.0000
11.750 0.8151 0.10368 0.09423 -0.0514 0.4213 1.0000
12.000 0.8420 0.10383 0.09453 -0.0514 0.4157 1.0000
12.250 0.8472 0.10587 0.09671 -0.0514 0.4049 1.0000
12.500 0.8533 0.10799 0.09895 -0.0515 0.3948 1.0000
12.750 0.8795 0.10800 0.09916 -0.0514 0.3889 1.0000
13.000 0.8829 0.11031 0.10160 -0.0515 0.3770 1.0000
13.250 0.8948 0.11165 0.10310 -0.0515 0.3670 1.0000
13.500 0.9203 0.11119 0.10283 -0.0510 0.3591 1.0000
13.750 0.9254 0.11331 0.10510 -0.0511 0.3466 1.0000
14.250 0.9718 0.11214 0.10437 -0.0499 0.3280 1.0000
14.750 0.9944 0.11374 0.10633 -0.0492 0.2998 1.0000
15.750 1.0630 0.11239 0.10554 -0.0465 0.2197 1.0000
16.000 1.0753 0.11303 0.10601 -0.0461 0.1864 1.0000
16.250 1.0796 0.11516 0.10786 -0.0461 0.1554 1.0000
16.500 1.0779 0.11851 0.11094 -0.0466 0.1301 1.0000
16.750 1.0744 0.12228 0.11443 -0.0475 0.1111 1.0000
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