FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.42 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61168-il-1000000-n5.txt Download as CSV file: xf-fx61168-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7599 0.08765 0.08539 -0.0560 1.0000 0.0032
-16.000 -0.7921 0.07724 0.07481 -0.0620 1.0000 0.0033
-15.750 -0.8105 0.07016 0.06760 -0.0660 1.0000 0.0034
-15.500 -0.8474 0.06092 0.05810 -0.0709 1.0000 0.0032
-15.250 -0.8572 0.05638 0.05344 -0.0728 1.0000 0.0033
-15.000 -0.8599 0.05307 0.05005 -0.0740 1.0000 0.0033
-14.750 -0.8723 0.04878 0.04561 -0.0751 1.0000 0.0033
-14.500 -0.8791 0.04552 0.04223 -0.0756 1.0000 0.0034
-14.250 -0.8843 0.04268 0.03927 -0.0756 1.0000 0.0034
-14.000 -0.8812 0.04018 0.03666 -0.0764 0.9997 0.0035
-13.750 -0.8694 0.03747 0.03381 -0.0791 0.9986 0.0035
-13.500 -0.8583 0.03489 0.03110 -0.0813 0.9969 0.0035
-13.250 -0.8496 0.03260 0.02867 -0.0824 0.9943 0.0036
-13.000 -0.8289 0.03149 0.02752 -0.0836 0.9916 0.0037
-12.750 -0.8185 0.02938 0.02527 -0.0845 0.9868 0.0038
-12.500 -0.8107 0.02814 0.02395 -0.0834 0.9757 0.0038
-12.250 -0.7950 0.02676 0.02248 -0.0839 0.9561 0.0039
-12.000 -0.7325 0.02458 0.02010 -0.0943 0.9341 0.0039
-11.750 -0.6400 0.02266 0.01774 -0.1108 0.8630 0.0042
-11.500 -0.6078 0.02159 0.01634 -0.1144 0.8082 0.0043
-11.250 -0.5865 0.02095 0.01552 -0.1150 0.7751 0.0045
-11.000 -0.5691 0.02019 0.01460 -0.1148 0.7494 0.0046
-10.750 -0.5512 0.01957 0.01385 -0.1144 0.7289 0.0047
-10.500 -0.5338 0.01897 0.01315 -0.1139 0.7114 0.0049
-10.250 -0.5176 0.01834 0.01242 -0.1131 0.6967 0.0049
-10.000 -0.5020 0.01773 0.01172 -0.1122 0.6851 0.0051
-9.500 -0.4729 0.01659 0.01044 -0.1096 0.6672 0.0054
-9.000 -0.4441 0.01553 0.00925 -0.1070 0.6530 0.0057
-8.750 -0.4252 0.01504 0.00866 -0.1064 0.6460 0.0059
-8.500 -0.4041 0.01464 0.00820 -0.1060 0.6404 0.0060
-8.250 -0.3842 0.01412 0.00762 -0.1054 0.6351 0.0062
-8.000 -0.3624 0.01372 0.00719 -0.1050 0.6303 0.0067
-7.750 -0.3391 0.01338 0.00681 -0.1047 0.6264 0.0070
-7.500 -0.3149 0.01307 0.00647 -0.1046 0.6225 0.0074
-7.250 -0.2905 0.01275 0.00611 -0.1044 0.6186 0.0079
-7.000 -0.2658 0.01244 0.00575 -0.1043 0.6149 0.0081
-6.750 -0.2402 0.01217 0.00543 -0.1043 0.6115 0.0084
-6.500 -0.2146 0.01181 0.00505 -0.1044 0.6082 0.0091
-6.250 -0.1881 0.01155 0.00476 -0.1045 0.6047 0.0099
-6.000 -0.1613 0.01133 0.00451 -0.1047 0.6016 0.0108
-5.750 -0.1342 0.01112 0.00426 -0.1049 0.5986 0.0116
-5.500 -0.1068 0.01087 0.00400 -0.1052 0.5962 0.0131
-5.250 -0.0787 0.01067 0.00378 -0.1055 0.5936 0.0146
-5.000 -0.0506 0.01046 0.00356 -0.1059 0.5906 0.0169
-4.750 -0.0224 0.01029 0.00337 -0.1062 0.5871 0.0197
-4.500 0.0059 0.01009 0.00319 -0.1066 0.5837 0.0268
-4.250 0.0346 0.00986 0.00300 -0.1072 0.5809 0.0435
-4.000 0.0639 0.00955 0.00280 -0.1079 0.5783 0.0720
-3.750 0.0940 0.00911 0.00257 -0.1090 0.5757 0.1326
-3.500 0.1278 0.00810 0.00214 -0.1117 0.5728 0.3029
-3.250 0.1617 0.00748 0.00187 -0.1139 0.5698 0.4147
-2.750 0.2262 0.00695 0.00172 -0.1166 0.5642 0.5473
-2.500 0.2567 0.00692 0.00173 -0.1172 0.5607 0.5720
-2.250 0.2864 0.00693 0.00172 -0.1177 0.5574 0.5822
-2.000 0.3158 0.00696 0.00171 -0.1181 0.5544 0.5874
-1.750 0.3451 0.00700 0.00170 -0.1184 0.5515 0.5922
-1.500 0.3749 0.00701 0.00171 -0.1189 0.5493 0.5966
-1.250 0.4045 0.00704 0.00172 -0.1193 0.5468 0.6012
-1.000 0.4340 0.00707 0.00172 -0.1198 0.5442 0.6056
-0.750 0.4634 0.00710 0.00174 -0.1201 0.5414 0.6096
-0.500 0.4924 0.00715 0.00177 -0.1205 0.5381 0.6134
-0.250 0.5217 0.00720 0.00179 -0.1208 0.5346 0.6174
0.000 0.5511 0.00723 0.00181 -0.1212 0.5310 0.6211
0.250 0.5802 0.00727 0.00185 -0.1216 0.5272 0.6241
0.500 0.6091 0.00733 0.00189 -0.1219 0.5234 0.6271
0.750 0.6380 0.00739 0.00194 -0.1222 0.5201 0.6303
1.000 0.6673 0.00743 0.00198 -0.1226 0.5169 0.6333
1.250 0.6963 0.00748 0.00202 -0.1229 0.5133 0.6356
1.500 0.7251 0.00754 0.00207 -0.1232 0.5096 0.6376
1.750 0.7536 0.00760 0.00213 -0.1235 0.5053 0.6397
2.000 0.7825 0.00765 0.00219 -0.1238 0.5000 0.6417
2.250 0.8107 0.00773 0.00226 -0.1240 0.4939 0.6436
2.500 0.8392 0.00780 0.00232 -0.1242 0.4889 0.6456
2.750 0.8675 0.00788 0.00239 -0.1245 0.4821 0.6477
3.000 0.8954 0.00799 0.00248 -0.1246 0.4747 0.6497
3.250 0.9234 0.00808 0.00255 -0.1248 0.4669 0.6513
3.500 0.9511 0.00818 0.00265 -0.1249 0.4604 0.6529
3.750 0.9787 0.00830 0.00276 -0.1250 0.4504 0.6545
4.000 1.0056 0.00844 0.00289 -0.1250 0.4384 0.6562
4.250 1.0323 0.00861 0.00302 -0.1250 0.4268 0.6581
4.500 1.0585 0.00881 0.00318 -0.1248 0.4139 0.6598
4.750 1.0843 0.00903 0.00335 -0.1246 0.3998 0.6614
5.000 1.1099 0.00925 0.00354 -0.1244 0.3859 0.6632
5.250 1.1361 0.00945 0.00371 -0.1243 0.3754 0.6649
5.500 1.1620 0.00965 0.00389 -0.1241 0.3649 0.6663
5.750 1.1867 0.00992 0.00412 -0.1238 0.3500 0.6678
6.000 1.2112 0.01019 0.00436 -0.1234 0.3358 0.6694
6.250 1.2346 0.01052 0.00463 -0.1228 0.3171 0.6710
6.500 1.2561 0.01095 0.00496 -0.1219 0.2934 0.6727
6.750 1.2757 0.01149 0.00536 -0.1207 0.2646 0.6744
7.000 1.2932 0.01212 0.00582 -0.1192 0.2321 0.6760
7.250 1.3089 0.01281 0.00634 -0.1173 0.1994 0.6776
7.500 1.3222 0.01359 0.00693 -0.1151 0.1676 0.6792
7.750 1.3334 0.01437 0.00754 -0.1124 0.1368 0.6807
8.000 1.3421 0.01508 0.00812 -0.1093 0.1135 0.6819
8.250 1.3524 0.01577 0.00872 -0.1065 0.0937 0.6835
8.500 1.3608 0.01654 0.00942 -0.1035 0.0755 0.6851
8.750 1.3684 0.01736 0.01016 -0.1005 0.0585 0.6866
9.000 1.3770 0.01815 0.01092 -0.0977 0.0462 0.6881
9.500 1.3897 0.02005 0.01275 -0.0920 0.0266 0.6910
9.750 1.3985 0.02094 0.01366 -0.0897 0.0214 0.6926
10.000 1.4059 0.02198 0.01470 -0.0875 0.0170 0.6942
10.250 1.4119 0.02316 0.01590 -0.0853 0.0129 0.6957
10.500 1.4164 0.02454 0.01729 -0.0831 0.0086 0.6969
10.750 1.4157 0.02640 0.01917 -0.0808 0.0030 0.6983
11.000 1.4224 0.02787 0.02070 -0.0794 0.0025 0.6997
11.250 1.4293 0.02942 0.02232 -0.0782 0.0022 0.7011
11.500 1.4358 0.03108 0.02406 -0.0771 0.0019 0.7025
11.750 1.4431 0.03274 0.02578 -0.0762 0.0018 0.7040
12.000 1.4502 0.03448 0.02759 -0.0754 0.0018 0.7057
12.250 1.4565 0.03635 0.02953 -0.0747 0.0017 0.7074
12.500 1.4625 0.03830 0.03156 -0.0740 0.0017 0.7089
12.750 1.4679 0.04036 0.03369 -0.0735 0.0016 0.7104
13.000 1.4727 0.04253 0.03593 -0.0730 0.0015 0.7116
13.250 1.4769 0.04481 0.03828 -0.0726 0.0015 0.7129
13.500 1.4807 0.04718 0.04074 -0.0723 0.0015 0.7143
13.750 1.4844 0.04963 0.04327 -0.0721 0.0014 0.7158
14.000 1.4873 0.05223 0.04595 -0.0719 0.0014 0.7173
14.250 1.4897 0.05495 0.04875 -0.0719 0.0013 0.7188
14.500 1.4916 0.05779 0.05168 -0.0719 0.0013 0.7203
14.750 1.4929 0.06080 0.05477 -0.0721 0.0013 0.7218
15.000 1.4938 0.06392 0.05800 -0.0724 0.0012 0.7234
15.250 1.4940 0.06722 0.06138 -0.0727 0.0012 0.7251
15.500 1.4935 0.07067 0.06492 -0.0732 0.0012 0.7266
16.000 1.4896 0.07830 0.07276 -0.0747 0.0011 0.7297
16.250 1.4873 0.08231 0.07687 -0.0757 0.0011 0.7313
16.500 1.4872 0.08605 0.08071 -0.0767 0.0011 0.7329
16.750 1.4863 0.08998 0.08474 -0.0778 0.0011 0.7346
17.000 1.4843 0.09415 0.08900 -0.0791 0.0011 0.7363
17.250 1.4832 0.09826 0.09320 -0.0805 0.0011 0.7381
17.500 1.4813 0.10252 0.09756 -0.0820 0.0010 0.7397
17.750 1.4781 0.10705 0.10219 -0.0836 0.0010 0.7413
18.250 1.4714 0.11635 0.11170 -0.0874 0.0010 0.7448
18.500 1.4665 0.12136 0.11683 -0.0897 0.0010 0.7467
18.750 1.4622 0.12628 0.12186 -0.0919 0.0010 0.7487
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