GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe374-il-1000000-n5.txt Download as CSV file: xf-goe374-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3216 0.09572 0.09417 -0.0180 1.0000 0.0042
-8.000 -0.3181 0.09299 0.09147 -0.0186 1.0000 0.0042
-7.750 -0.3166 0.09027 0.08877 -0.0189 1.0000 0.0042
-7.500 -0.3112 0.08738 0.08590 -0.0202 0.9935 0.0042
-7.250 -0.2957 0.08338 0.08190 -0.0250 0.9807 0.0042
-7.000 -0.2700 0.07877 0.07729 -0.0323 0.9695 0.0040
-6.750 -0.2343 0.07322 0.07169 -0.0429 0.9567 0.0039
-6.250 -0.1740 0.06385 0.06211 -0.0589 0.9022 0.0039
-6.000 -0.1581 0.06136 0.05950 -0.0613 0.8745 0.0051
-5.000 -0.0826 0.04679 0.04443 -0.0718 0.8011 0.0041
-4.750 -0.0602 0.04320 0.04069 -0.0738 0.7838 0.0040
-4.500 -0.0368 0.03991 0.03723 -0.0754 0.7617 0.0039
-4.250 -0.0125 0.03639 0.03349 -0.0766 0.7348 0.0039
-4.000 0.0124 0.03239 0.02919 -0.0774 0.7012 0.0041
-3.750 0.0378 0.02802 0.02447 -0.0777 0.6721 0.0044
-3.500 0.0623 0.02629 0.02251 -0.0776 0.6477 0.0047
-3.250 0.0878 0.02367 0.01962 -0.0773 0.6311 0.0049
-3.000 0.1135 0.02131 0.01698 -0.0768 0.6171 0.0056
-2.500 0.1639 0.01362 0.00827 -0.0741 0.5957 0.0075
-2.250 0.1900 0.01258 0.00702 -0.0735 0.5831 0.0086
-2.000 0.2159 0.01128 0.00547 -0.0729 0.5702 0.0102
-1.750 0.2425 0.01118 0.00527 -0.0726 0.5535 0.0114
-1.500 0.2676 0.00975 0.00353 -0.0718 0.5352 0.0147
-1.250 0.2944 0.01007 0.00377 -0.0716 0.5080 0.0153
-1.000 0.3206 0.01027 0.00385 -0.0713 0.4794 0.0163
-0.750 0.3468 0.01020 0.00363 -0.0709 0.4571 0.0177
-0.500 0.3732 0.01009 0.00340 -0.0705 0.4409 0.0196
-0.250 0.3994 0.00995 0.00313 -0.0701 0.4237 0.0208
0.250 0.4519 0.00960 0.00261 -0.0695 0.4006 0.0230
0.500 0.4780 0.00940 0.00239 -0.0691 0.3920 0.0241
0.750 0.5044 0.00927 0.00224 -0.0688 0.3827 0.0251
1.000 0.5307 0.00919 0.00211 -0.0685 0.3727 0.0259
1.250 0.5571 0.00910 0.00198 -0.0682 0.3640 0.0263
1.500 0.5835 0.00904 0.00188 -0.0679 0.3560 0.0266
1.750 0.6098 0.00902 0.00182 -0.0676 0.3461 0.0273
2.000 0.6363 0.00897 0.00174 -0.0673 0.3383 0.0272
2.250 0.6627 0.00896 0.00169 -0.0670 0.3293 0.0268
2.500 0.6890 0.00897 0.00166 -0.0668 0.3187 0.0265
2.750 0.7153 0.00900 0.00165 -0.0665 0.3075 0.0263
3.000 0.7416 0.00905 0.00166 -0.0662 0.2964 0.0261
3.250 0.7678 0.00913 0.00170 -0.0659 0.2855 0.0260
3.500 0.7940 0.00921 0.00175 -0.0656 0.2750 0.0259
3.750 0.8201 0.00931 0.00181 -0.0653 0.2647 0.0261
4.000 0.8462 0.00942 0.00190 -0.0651 0.2545 0.0265
4.250 0.8721 0.00957 0.00200 -0.0648 0.2436 0.0276
4.500 0.8980 0.00971 0.00212 -0.0645 0.2323 0.0298
4.750 0.9237 0.00989 0.00227 -0.0641 0.2195 0.0339
5.000 0.9640 0.00873 0.00278 -0.0680 0.1885 1.0000
5.250 0.9878 0.00908 0.00302 -0.0674 0.1646 1.0000
5.500 1.0101 0.00960 0.00334 -0.0665 0.1318 1.0000
5.750 1.0338 0.00997 0.00362 -0.0659 0.1156 1.0000
6.000 1.0576 0.01031 0.00391 -0.0653 0.1032 1.0000
6.250 1.0810 0.01069 0.00421 -0.0647 0.0860 1.0000
6.500 1.0964 0.01202 0.00513 -0.0629 0.0156 1.0000
6.750 1.1203 0.01235 0.00549 -0.0622 0.0098 1.0000
7.000 1.1438 0.01271 0.00590 -0.0616 0.0079 1.0000
7.250 1.1670 0.01310 0.00633 -0.0609 0.0062 1.0000
7.500 1.1902 0.01347 0.00673 -0.0602 0.0052 1.0000
7.750 1.2122 0.01396 0.00726 -0.0594 0.0043 1.0000
8.000 1.2348 0.01437 0.00773 -0.0586 0.0038 1.0000
8.250 1.2567 0.01485 0.00828 -0.0578 0.0035 1.0000
8.500 1.2783 0.01535 0.00883 -0.0569 0.0032 1.0000
8.750 1.2989 0.01592 0.00946 -0.0559 0.0029 1.0000
9.000 1.3181 0.01663 0.01026 -0.0546 0.0025 1.0000
9.250 1.3385 0.01717 0.01086 -0.0536 0.0023 1.0000
9.500 1.3571 0.01786 0.01164 -0.0524 0.0022 1.0000
9.750 1.3752 0.01855 0.01241 -0.0510 0.0020 1.0000
10.000 1.3915 0.01936 0.01334 -0.0495 0.0019 1.0000
10.250 1.4074 0.02014 0.01420 -0.0479 0.0018 1.0000
10.500 1.4225 0.02093 0.01506 -0.0463 0.0017 1.0000
10.750 1.4343 0.02190 0.01612 -0.0442 0.0016 1.0000
11.000 1.4411 0.02299 0.01733 -0.0412 0.0015 1.0000
11.250 1.4424 0.02421 0.01867 -0.0375 0.0014 1.0000
11.500 1.4423 0.02559 0.02018 -0.0340 0.0014 1.0000
11.750 1.4423 0.02709 0.02180 -0.0310 0.0014 1.0000
12.000 1.4448 0.02854 0.02337 -0.0287 0.0013 1.0000
12.250 1.4439 0.03040 0.02535 -0.0265 0.0013 1.0000
12.500 1.4388 0.03282 0.02791 -0.0246 0.0013 1.0000
12.750 1.4345 0.03546 0.03069 -0.0234 0.0012 1.0000
13.000 1.4260 0.03883 0.03422 -0.0227 0.0012 1.0000
13.250 1.4227 0.04198 0.03750 -0.0227 0.0011 1.0000
13.500 1.4123 0.04632 0.04201 -0.0234 0.0011 1.0000
13.750 1.4036 0.05071 0.04655 -0.0244 0.0011 1.0000
14.000 1.3952 0.05521 0.05118 -0.0257 0.0011 1.0000
14.250 1.3890 0.05958 0.05567 -0.0272 0.0011 1.0000
14.500 1.3724 0.06553 0.06177 -0.0292 0.0011 1.0000
14.750 1.3589 0.07124 0.06761 -0.0312 0.0011 1.0000
15.000 1.3480 0.07677 0.07328 -0.0334 0.0010 1.0000
15.250 1.3389 0.08210 0.07872 -0.0357 0.0010 1.0000
15.500 1.3240 0.08851 0.08526 -0.0383 0.0010 1.0000
15.750 1.3098 0.09497 0.09184 -0.0410 0.0010 1.0000
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Polar data table (+)
Polar graphs
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