FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 500,000 Max Cl/Cd: 99.21 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61147-il-500000.txt Download as CSV file: xf-fx61147-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4052 0.08401 0.08198 -0.0480 1.0000 0.0179
-9.500 -0.4417 0.07219 0.07016 -0.0551 1.0000 0.0176
-9.250 -0.4540 0.06393 0.06177 -0.0646 0.9970 0.0177
-9.000 -0.4596 0.05766 0.05534 -0.0726 0.9911 0.0177
-8.750 -0.4563 0.05285 0.05038 -0.0795 0.9838 0.0180
-8.250 -0.4611 0.03106 0.02702 -0.0899 0.9649 0.0130
-8.000 -0.4278 0.02972 0.02566 -0.0930 0.9629 0.0136
-7.750 -0.4012 0.03088 0.02687 -0.0939 0.9553 0.0179
-7.500 -0.3799 0.02163 0.01647 -0.0945 0.9516 0.0128
-7.250 -0.3453 0.02017 0.01495 -0.0968 0.9495 0.0137
-7.000 -0.3199 0.01929 0.01400 -0.0968 0.9416 0.0145
-6.750 -0.2862 0.01775 0.01229 -0.0982 0.9380 0.0151
-6.500 -0.2501 0.01631 0.01071 -0.1000 0.9347 0.0158
-6.250 -0.2197 0.01542 0.00970 -0.1006 0.9260 0.0166
-6.000 -0.1799 0.01376 0.00798 -0.1037 0.9215 0.0181
-5.750 -0.1427 0.01308 0.00727 -0.1061 0.9120 0.0200
-5.500 -0.0955 0.01240 0.00651 -0.1106 0.9048 0.0229
-5.250 -0.0530 0.01157 0.00563 -0.1143 0.8928 0.0264
-5.000 -0.0143 0.01121 0.00517 -0.1168 0.8775 0.0295
-4.750 0.0199 0.01057 0.00445 -0.1187 0.8593 0.0357
-4.500 0.0519 0.01015 0.00395 -0.1198 0.8387 0.0456
-4.250 0.0827 0.00952 0.00343 -0.1211 0.8174 0.0981
-4.000 0.1148 0.00790 0.00275 -0.1242 0.7953 0.3725
-3.750 0.1460 0.00735 0.00258 -0.1256 0.7741 0.5200
-3.500 0.1738 0.00735 0.00259 -0.1255 0.7538 0.5680
-3.250 0.2009 0.00746 0.00261 -0.1253 0.7338 0.5962
-3.000 0.2273 0.00766 0.00273 -0.1247 0.7150 0.6187
-2.750 0.2538 0.00791 0.00287 -0.1242 0.6978 0.6369
-2.500 0.2798 0.00820 0.00306 -0.1236 0.6821 0.6504
-2.250 0.3058 0.00846 0.00323 -0.1229 0.6673 0.6603
-2.000 0.3325 0.00867 0.00332 -0.1226 0.6533 0.6675
-1.750 0.3597 0.00879 0.00334 -0.1224 0.6402 0.6723
-1.500 0.3861 0.00892 0.00342 -0.1220 0.6280 0.6760
-1.250 0.4133 0.00905 0.00346 -0.1218 0.6167 0.6802
-1.000 0.4417 0.00918 0.00346 -0.1220 0.6059 0.6852
-0.750 0.4681 0.00928 0.00351 -0.1217 0.5957 0.6880
-0.500 0.4951 0.00938 0.00358 -0.1215 0.5863 0.6910
-0.250 0.5223 0.00952 0.00363 -0.1213 0.5777 0.6946
0.000 0.5507 0.00961 0.00366 -0.1215 0.5687 0.6988
0.250 0.5781 0.00970 0.00370 -0.1215 0.5607 0.7020
0.500 0.6050 0.00980 0.00378 -0.1213 0.5528 0.7044
0.750 0.6321 0.00991 0.00386 -0.1212 0.5456 0.7071
1.000 0.6597 0.01001 0.00392 -0.1212 0.5379 0.7104
1.250 0.6880 0.01013 0.00397 -0.1214 0.5310 0.7140
1.500 0.7156 0.01020 0.00403 -0.1215 0.5238 0.7166
1.750 0.7422 0.01032 0.00412 -0.1212 0.5171 0.7189
2.000 0.7692 0.01040 0.00422 -0.1211 0.5099 0.7214
2.250 0.7962 0.01056 0.00432 -0.1210 0.5035 0.7243
2.500 0.8242 0.01062 0.00441 -0.1212 0.4968 0.7274
2.750 0.8521 0.01076 0.00449 -0.1214 0.4905 0.7304
3.000 0.8789 0.01084 0.00460 -0.1212 0.4846 0.7324
3.250 0.9056 0.01094 0.00472 -0.1211 0.4784 0.7346
3.500 0.9322 0.01110 0.00486 -0.1210 0.4726 0.7370
3.750 0.9594 0.01118 0.00498 -0.1210 0.4663 0.7398
4.000 0.9867 0.01133 0.00511 -0.1210 0.4606 0.7425
4.250 1.0144 0.01146 0.00525 -0.1212 0.4549 0.7451
4.500 1.0406 0.01155 0.00539 -0.1210 0.4488 0.7471
4.750 1.0665 0.01172 0.00556 -0.1207 0.4430 0.7492
5.000 1.0931 0.01181 0.00573 -0.1206 0.4368 0.7514
5.250 1.1192 0.01198 0.00590 -0.1204 0.4311 0.7539
5.500 1.1458 0.01212 0.00608 -0.1204 0.4247 0.7566
5.750 1.1719 0.01229 0.00625 -0.1202 0.4170 0.7591
6.000 1.1972 0.01239 0.00641 -0.1199 0.4087 0.7610
6.250 1.2211 0.01258 0.00660 -0.1193 0.4000 0.7631
6.500 1.2461 0.01269 0.00678 -0.1189 0.3905 0.7654
6.750 1.2705 0.01288 0.00701 -0.1184 0.3821 0.7678
7.000 1.2940 0.01309 0.00721 -0.1178 0.3705 0.7703
7.250 1.3178 0.01330 0.00743 -0.1173 0.3569 0.7729
7.500 1.3413 0.01352 0.00767 -0.1167 0.3443 0.7751
7.750 1.3629 0.01378 0.00795 -0.1157 0.3290 0.7771
8.000 1.3834 0.01412 0.00827 -0.1146 0.3122 0.7793
8.250 1.4037 0.01449 0.00862 -0.1135 0.2935 0.7818
8.500 1.4213 0.01501 0.00905 -0.1119 0.2699 0.7845
8.750 1.4363 0.01561 0.00954 -0.1100 0.2429 0.7869
9.000 1.4482 0.01634 0.01015 -0.1075 0.2140 0.7892
9.250 1.4571 0.01722 0.01089 -0.1046 0.1815 0.7915
9.500 1.4615 0.01836 0.01183 -0.1011 0.1455 0.7941
9.750 1.4640 0.01962 0.01292 -0.0975 0.1153 0.7968
10.000 1.4659 0.02092 0.01408 -0.0939 0.0889 0.7995
10.250 1.4688 0.02221 0.01527 -0.0907 0.0685 0.8021
10.500 1.4717 0.02352 0.01653 -0.0877 0.0546 0.8045
10.750 1.4744 0.02486 0.01786 -0.0849 0.0432 0.8072
11.000 1.4777 0.02626 0.01928 -0.0823 0.0349 0.8101
11.250 1.4811 0.02775 0.02080 -0.0800 0.0287 0.8131
11.500 1.4830 0.02948 0.02257 -0.0779 0.0230 0.8160
11.750 1.4816 0.03156 0.02469 -0.0758 0.0171 0.8187
12.000 1.4774 0.03400 0.02719 -0.0738 0.0122 0.8215
12.250 1.4732 0.03667 0.02993 -0.0722 0.0095 0.8246
12.500 1.4731 0.03916 0.03252 -0.0712 0.0082 0.8281
12.750 1.4708 0.04205 0.03550 -0.0705 0.0074 0.8315
13.000 1.4685 0.04506 0.03864 -0.0699 0.0068 0.8347
13.250 1.4676 0.04805 0.04176 -0.0697 0.0065 0.8381
13.500 1.4661 0.05128 0.04512 -0.0697 0.0061 0.8417
13.750 1.4636 0.05478 0.04875 -0.0700 0.0059 0.8454
14.000 1.4600 0.05851 0.05260 -0.0704 0.0057 0.8491
14.250 1.4553 0.06249 0.05672 -0.0710 0.0055 0.8532
14.500 1.4495 0.06679 0.06116 -0.0718 0.0054 0.8579
14.750 1.4423 0.07142 0.06592 -0.0729 0.0052 0.8628
15.000 1.4340 0.07634 0.07101 -0.0742 0.0051 0.8685
15.250 1.4244 0.08161 0.07642 -0.0757 0.0050 0.8749
15.500 1.4143 0.08698 0.08196 -0.0773 0.0049 0.8836
15.750 1.4046 0.09175 0.08690 -0.0782 0.0049 0.9034
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