FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 500,000 Max Cl/Cd: 103.5 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s196-il-500000-n5.txt Download as CSV file: xf-fx66s196-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.4931 0.11074 0.10758 -0.0840 0.8555 0.0093
-17.500 -0.5641 0.09260 0.08914 -0.0936 0.8622 0.0090
-17.250 -0.5718 0.08691 0.08324 -0.0972 0.8361 0.0092
-17.000 -0.5901 0.07993 0.07601 -0.1012 0.8189 0.0093
-16.750 -0.6090 0.07332 0.06916 -0.1049 0.8054 0.0093
-16.500 -0.6259 0.06745 0.06308 -0.1078 0.7929 0.0092
-16.250 -0.6306 0.06354 0.05899 -0.1098 0.7790 0.0094
-16.000 -0.6360 0.05978 0.05505 -0.1116 0.7668 0.0095
-15.750 -0.6430 0.05600 0.05109 -0.1130 0.7567 0.0096
-15.500 -0.6445 0.05303 0.04796 -0.1142 0.7474 0.0097
-15.000 -0.6476 0.04750 0.04212 -0.1156 0.7308 0.0100
-14.500 -0.6432 0.04316 0.03748 -0.1163 0.7158 0.0102
-14.250 -0.6399 0.04124 0.03540 -0.1163 0.7091 0.0104
-14.000 -0.6358 0.03945 0.03350 -0.1162 0.7034 0.0104
-13.750 -0.6323 0.03766 0.03158 -0.1160 0.6976 0.0106
-13.500 -0.6291 0.03591 0.02973 -0.1156 0.6924 0.0107
-13.250 -0.6241 0.03432 0.02808 -0.1152 0.6874 0.0110
-13.000 -0.6173 0.03291 0.02658 -0.1148 0.6820 0.0111
-12.750 -0.6097 0.03161 0.02520 -0.1143 0.6770 0.0113
-12.500 -0.6011 0.03036 0.02389 -0.1137 0.6725 0.0115
-12.250 -0.5904 0.02932 0.02277 -0.1133 0.6674 0.0118
-12.000 -0.5811 0.02819 0.02155 -0.1125 0.6627 0.0120
-11.750 -0.5699 0.02720 0.02049 -0.1119 0.6586 0.0124
-11.500 -0.5589 0.02622 0.01944 -0.1112 0.6544 0.0126
-11.250 -0.5487 0.02520 0.01833 -0.1103 0.6501 0.0129
-11.000 -0.5376 0.02427 0.01731 -0.1094 0.6463 0.0132
-10.750 -0.5269 0.02333 0.01630 -0.1084 0.6426 0.0133
-10.500 -0.5148 0.02248 0.01538 -0.1075 0.6388 0.0136
-10.250 -0.5066 0.02145 0.01428 -0.1062 0.6349 0.0139
-10.000 -0.4971 0.02055 0.01332 -0.1049 0.6314 0.0143
-9.750 -0.4869 0.01974 0.01247 -0.1036 0.6283 0.0147
-9.500 -0.4767 0.01903 0.01172 -0.1021 0.6252 0.0151
-9.250 -0.4684 0.01847 0.01111 -0.1000 0.6220 0.0155
-9.000 -0.4547 0.01796 0.01054 -0.0986 0.6189 0.0161
-8.750 -0.4382 0.01749 0.00999 -0.0975 0.6160 0.0166
-8.500 -0.4206 0.01703 0.00945 -0.0965 0.6134 0.0170
-8.250 -0.4023 0.01651 0.00890 -0.0957 0.6108 0.0177
-8.000 -0.3822 0.01607 0.00844 -0.0950 0.6081 0.0186
-7.750 -0.3609 0.01568 0.00802 -0.0945 0.6053 0.0196
-7.500 -0.3387 0.01534 0.00761 -0.0940 0.6027 0.0210
-7.250 -0.3165 0.01496 0.00718 -0.0936 0.6003 0.0226
-7.000 -0.2935 0.01463 0.00681 -0.0932 0.5981 0.0249
-6.750 -0.2693 0.01433 0.00648 -0.0931 0.5960 0.0277
-6.500 -0.2454 0.01398 0.00613 -0.0929 0.5936 0.0315
-6.250 -0.2208 0.01368 0.00582 -0.0927 0.5911 0.0362
-6.000 -0.1960 0.01339 0.00553 -0.0926 0.5887 0.0427
-5.750 -0.1707 0.01314 0.00525 -0.0926 0.5864 0.0510
-5.500 -0.1456 0.01286 0.00498 -0.0925 0.5843 0.0616
-5.250 -0.1206 0.01255 0.00472 -0.0925 0.5823 0.0797
-4.750 -0.0705 0.01176 0.00418 -0.0926 0.5782 0.1432
-4.500 -0.0461 0.01127 0.00388 -0.0927 0.5761 0.1985
-4.250 -0.0224 0.01067 0.00354 -0.0927 0.5742 0.2749
-4.000 0.0000 0.00991 0.00316 -0.0925 0.5724 0.3795
-3.750 0.0244 0.00960 0.00320 -0.0923 0.5707 0.4809
-3.500 0.0532 0.00967 0.00316 -0.0926 0.5692 0.5014
-3.250 0.0818 0.00972 0.00313 -0.0929 0.5676 0.5096
-3.000 0.1104 0.00975 0.00315 -0.0932 0.5663 0.5201
-2.750 0.1392 0.00980 0.00315 -0.0935 0.5649 0.5291
-2.500 0.1677 0.00984 0.00319 -0.0938 0.5634 0.5355
-2.250 0.1965 0.00989 0.00319 -0.0941 0.5619 0.5413
-2.000 0.2250 0.00995 0.00325 -0.0944 0.5605 0.5484
-1.750 0.2536 0.01004 0.00331 -0.0947 0.5590 0.5552
-1.500 0.2823 0.01010 0.00330 -0.0950 0.5576 0.5588
-1.250 0.3108 0.01013 0.00329 -0.0953 0.5562 0.5605
-1.000 0.3393 0.01015 0.00328 -0.0957 0.5549 0.5619
-0.750 0.3678 0.01019 0.00329 -0.0960 0.5537 0.5635
-0.500 0.3963 0.01025 0.00332 -0.0963 0.5524 0.5652
-0.250 0.4249 0.01030 0.00334 -0.0967 0.5512 0.5666
0.000 0.4534 0.01031 0.00336 -0.0970 0.5499 0.5675
0.250 0.4818 0.01034 0.00338 -0.0974 0.5485 0.5684
0.500 0.5103 0.01037 0.00340 -0.0977 0.5471 0.5692
0.750 0.5387 0.01040 0.00343 -0.0980 0.5458 0.5698
1.000 0.5670 0.01044 0.00347 -0.0984 0.5446 0.5705
1.250 0.5953 0.01048 0.00351 -0.0987 0.5433 0.5711
1.500 0.6235 0.01053 0.00355 -0.0990 0.5421 0.5719
1.750 0.6517 0.01059 0.00360 -0.0993 0.5409 0.5728
2.000 0.6798 0.01065 0.00366 -0.0997 0.5398 0.5737
2.250 0.7080 0.01072 0.00372 -0.1000 0.5386 0.5745
2.500 0.7361 0.01080 0.00379 -0.1003 0.5375 0.5751
2.750 0.7643 0.01088 0.00387 -0.1006 0.5364 0.5758
3.000 0.7920 0.01094 0.00397 -0.1009 0.5354 0.5765
3.250 0.8196 0.01100 0.00409 -0.1011 0.5343 0.5774
3.500 0.8471 0.01107 0.00420 -0.1014 0.5331 0.5785
3.750 0.8745 0.01114 0.00432 -0.1016 0.5318 0.5795
4.000 0.9017 0.01121 0.00444 -0.1017 0.5303 0.5808
4.250 0.9289 0.01128 0.00455 -0.1019 0.5286 0.5820
4.500 0.9559 0.01135 0.00467 -0.1020 0.5271 0.5832
4.750 0.9830 0.01143 0.00479 -0.1022 0.5256 0.5843
5.000 1.0102 0.01153 0.00490 -0.1024 0.5242 0.5856
5.250 1.0374 0.01163 0.00503 -0.1026 0.5228 0.5868
5.500 1.0648 0.01176 0.00518 -0.1028 0.5212 0.5882
5.750 1.0906 0.01185 0.00536 -0.1027 0.5196 0.5894
6.000 1.1162 0.01195 0.00553 -0.1026 0.5175 0.5908
6.250 1.1415 0.01203 0.00570 -0.1025 0.5152 0.5922
6.500 1.1665 0.01211 0.00585 -0.1023 0.5127 0.5937
6.750 1.1915 0.01219 0.00599 -0.1020 0.5101 0.5954
7.000 1.2166 0.01229 0.00609 -0.1018 0.5066 0.5974
7.250 1.2384 0.01236 0.00629 -0.1010 0.5022 0.5994
7.500 1.2600 0.01243 0.00645 -0.1001 0.4970 0.6017
7.750 1.2806 0.01252 0.00653 -0.0990 0.4907 0.6040
8.000 1.2997 0.01261 0.00674 -0.0977 0.4829 0.6064
8.250 1.3155 0.01271 0.00689 -0.0958 0.4735 0.6089
8.500 1.3275 0.01284 0.00708 -0.0931 0.4627 0.6116
8.750 1.3329 0.01319 0.00740 -0.0893 0.4465 0.6146
9.000 1.3387 0.01368 0.00788 -0.0859 0.4293 0.6179
9.250 1.3250 0.01489 0.00892 -0.0798 0.3904 0.6212
9.500 1.3130 0.01642 0.01034 -0.0748 0.3633 0.6246
9.750 1.2990 0.01841 0.01225 -0.0703 0.3349 0.6282
10.000 1.2764 0.02131 0.01502 -0.0657 0.3040 0.6321
10.250 1.2638 0.02396 0.01761 -0.0627 0.2786 0.6363
10.750 1.2280 0.03063 0.02410 -0.0570 0.2243 0.6445
11.000 1.2128 0.03401 0.02737 -0.0548 0.1991 0.6498
11.250 1.1990 0.03743 0.03069 -0.0530 0.1715 0.6547
11.500 1.1887 0.04071 0.03388 -0.0515 0.1479 0.6603
11.750 1.1876 0.04331 0.03644 -0.0507 0.1294 0.6672
12.000 1.1813 0.04639 0.03943 -0.0497 0.1072 0.6737
12.250 1.1832 0.04888 0.04191 -0.0493 0.0923 0.6825
12.500 1.1844 0.05155 0.04454 -0.0490 0.0760 0.6920
12.750 1.1842 0.05437 0.04731 -0.0487 0.0598 0.7033
13.000 1.1891 0.05684 0.04979 -0.0487 0.0477 0.7170
13.250 1.1951 0.05936 0.05235 -0.0491 0.0399 0.7318
13.500 1.2062 0.06163 0.05472 -0.0500 0.0335 0.7535
13.750 1.2149 0.06434 0.05750 -0.0511 0.0257 0.7831
14.000 1.2392 0.06767 0.06107 -0.0560 0.0198 0.8593
14.250 1.2743 0.07153 0.06511 -0.0632 0.0159 0.9997
14.500 1.2808 0.07377 0.06739 -0.0631 0.0145 1.0000
14.750 1.2859 0.07616 0.06982 -0.0629 0.0129 1.0000
15.000 1.2923 0.07842 0.07213 -0.0629 0.0119 1.0000
15.250 1.2975 0.08087 0.07463 -0.0628 0.0110 1.0000
15.500 1.3029 0.08331 0.07711 -0.0628 0.0102 1.0000
15.750 1.3074 0.08583 0.07967 -0.0628 0.0093 1.0000
16.000 1.3121 0.08839 0.08229 -0.0628 0.0092 1.0000
16.250 1.3169 0.09091 0.08487 -0.0629 0.0085 1.0000
16.500 1.3210 0.09351 0.08750 -0.0630 0.0079 1.0000
16.750 1.3243 0.09629 0.09035 -0.0632 0.0077 1.0000
17.000 1.3266 0.09916 0.09329 -0.0634 0.0074 1.0000
17.250 1.3291 0.10207 0.09626 -0.0637 0.0071 1.0000
17.500 1.3326 0.10486 0.09912 -0.0640 0.0070 1.0000
17.750 1.3356 0.10768 0.10202 -0.0643 0.0067 1.0000
18.000 1.3368 0.11080 0.10522 -0.0648 0.0065 1.0000
18.250 1.3390 0.11380 0.10829 -0.0653 0.0064 1.0000
18.500 1.3407 0.11689 0.11144 -0.0659 0.0061 1.0000
18.750 1.3422 0.12004 0.11467 -0.0666 0.0060 1.0000
19.000 1.3428 0.12332 0.11802 -0.0673 0.0058 1.0000
19.250 1.3426 0.12675 0.12153 -0.0682 0.0056 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 66-S-196 AIRFOIL (fx66s196-il)