GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.43 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe367-il-1000000-n5.txt Download as CSV file: xf-goe367-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 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
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0955 0.03657 0.03305 -0.1137 1.0000 0.0254
-16.750 -1.0983 0.03368 0.03003 -0.1148 0.9950 0.0255
-16.500 -1.0912 0.03151 0.02773 -0.1160 0.9845 0.0257
-16.250 -1.0834 0.02977 0.02588 -0.1161 0.9735 0.0258
-16.000 -1.0763 0.02839 0.02437 -0.1152 0.9620 0.0260
-15.750 -1.0699 0.02720 0.02307 -0.1136 0.9509 0.0261
-15.500 -1.0627 0.02614 0.02189 -0.1118 0.9402 0.0262
-15.250 -1.0532 0.02519 0.02083 -0.1101 0.9309 0.0263
-14.750 -1.0329 0.02345 0.01886 -0.1062 0.9121 0.0265
-14.500 -1.0233 0.02262 0.01792 -0.1040 0.9028 0.0267
-14.250 -1.0080 0.02185 0.01707 -0.1026 0.8936 0.0269
-14.000 -0.9911 0.02119 0.01631 -0.1013 0.8849 0.0271
-13.750 -0.9722 0.02058 0.01562 -0.1003 0.8762 0.0273
-13.500 -0.9526 0.02003 0.01498 -0.0993 0.8683 0.0275
-13.250 -0.9317 0.01950 0.01438 -0.0986 0.8607 0.0277
-13.000 -0.9104 0.01901 0.01381 -0.0978 0.8529 0.0279
-12.750 -0.8880 0.01855 0.01329 -0.0971 0.8460 0.0282
-12.500 -0.8653 0.01813 0.01278 -0.0965 0.8383 0.0285
-12.250 -0.8424 0.01771 0.01228 -0.0959 0.8313 0.0287
-12.000 -0.8191 0.01728 0.01178 -0.0954 0.8240 0.0290
-11.750 -0.7956 0.01687 0.01128 -0.0948 0.8171 0.0292
-11.500 -0.7716 0.01646 0.01080 -0.0944 0.8114 0.0295
-11.250 -0.7472 0.01607 0.01034 -0.0939 0.8051 0.0297
-11.000 -0.7228 0.01572 0.00990 -0.0935 0.7988 0.0299
-10.750 -0.6977 0.01537 0.00949 -0.0931 0.7933 0.0301
-10.500 -0.6724 0.01504 0.00909 -0.0928 0.7874 0.0303
-10.250 -0.6482 0.01462 0.00861 -0.0923 0.7811 0.0306
-10.000 -0.6231 0.01426 0.00820 -0.0920 0.7743 0.0310
-9.750 -0.5976 0.01395 0.00784 -0.0917 0.7664 0.0313
-9.500 -0.5719 0.01368 0.00751 -0.0914 0.7596 0.0317
-9.250 -0.5455 0.01341 0.00720 -0.0912 0.7542 0.0321
-9.000 -0.5191 0.01316 0.00691 -0.0910 0.7490 0.0324
-8.750 -0.4926 0.01293 0.00662 -0.0908 0.7440 0.0329
-8.500 -0.4657 0.01270 0.00636 -0.0907 0.7399 0.0333
-8.250 -0.4387 0.01247 0.00609 -0.0906 0.7353 0.0338
-8.000 -0.4117 0.01226 0.00583 -0.0905 0.7306 0.0342
-7.750 -0.3848 0.01207 0.00559 -0.0903 0.7262 0.0345
-7.500 -0.3580 0.01180 0.00529 -0.0902 0.7223 0.0351
-7.250 -0.3308 0.01156 0.00505 -0.0901 0.7180 0.0356
-7.000 -0.3035 0.01137 0.00484 -0.0900 0.7137 0.0362
-6.750 -0.2762 0.01120 0.00464 -0.0900 0.7093 0.0369
-6.500 -0.2487 0.01104 0.00445 -0.0899 0.7051 0.0375
-6.250 -0.2209 0.01087 0.00426 -0.0899 0.7010 0.0382
-6.000 -0.1932 0.01072 0.00408 -0.0899 0.6965 0.0388
-5.750 -0.1656 0.01059 0.00391 -0.0898 0.6917 0.0393
-5.500 -0.1382 0.01041 0.00372 -0.0898 0.6873 0.0404
-5.250 -0.1103 0.01025 0.00357 -0.0898 0.6826 0.0414
-5.000 -0.0825 0.01013 0.00343 -0.0898 0.6772 0.0425
-4.500 -0.0272 0.00992 0.00316 -0.0897 0.6628 0.0443
-4.250 -0.0002 0.00983 0.00302 -0.0896 0.6528 0.0453
-4.000 0.0274 0.00971 0.00289 -0.0895 0.6436 0.0467
-3.750 0.0547 0.00963 0.00278 -0.0894 0.6358 0.0480
-3.500 0.0827 0.00954 0.00267 -0.0895 0.6286 0.0494
-3.250 0.1101 0.00950 0.00258 -0.0894 0.6193 0.0507
-3.000 0.1374 0.00940 0.00248 -0.0893 0.6094 0.0529
-2.750 0.1645 0.00935 0.00240 -0.0891 0.5987 0.0550
-2.500 0.1918 0.00932 0.00233 -0.0891 0.5879 0.0570
-2.250 0.2188 0.00927 0.00226 -0.0889 0.5779 0.0606
-1.750 0.2723 0.00917 0.00217 -0.0886 0.5565 0.0796
-1.500 0.2989 0.00916 0.00217 -0.0884 0.5460 0.0933
-1.250 0.3258 0.00917 0.00217 -0.0883 0.5351 0.1014
-1.000 0.3528 0.00918 0.00217 -0.0882 0.5263 0.1073
-0.750 0.3799 0.00920 0.00218 -0.0880 0.5176 0.1131
-0.500 0.4071 0.00924 0.00219 -0.0880 0.5104 0.1166
-0.250 0.4343 0.00924 0.00220 -0.0879 0.5029 0.1225
0.000 0.4611 0.00929 0.00222 -0.0877 0.4956 0.1280
0.250 0.4885 0.00931 0.00223 -0.0877 0.4886 0.1322
0.500 0.5147 0.00936 0.00227 -0.0875 0.4792 0.1383
0.750 0.5416 0.00940 0.00230 -0.0873 0.4698 0.1454
1.000 0.5673 0.00947 0.00235 -0.0870 0.4585 0.1549
1.500 0.6185 0.00959 0.00246 -0.0864 0.4335 0.1861
1.750 0.6423 0.00945 0.00254 -0.0858 0.4223 0.2843
2.000 0.6627 0.00888 0.00263 -0.0849 0.4121 0.5337
2.250 0.6761 0.00808 0.00283 -0.0820 0.4052 0.8666
2.500 0.7001 0.00820 0.00297 -0.0811 0.3968 0.8925
2.750 0.7249 0.00835 0.00309 -0.0805 0.3893 0.9054
3.000 0.7496 0.00849 0.00321 -0.0799 0.3814 0.9159
3.250 0.7736 0.00866 0.00334 -0.0792 0.3740 0.9239
3.500 0.7977 0.00880 0.00346 -0.0785 0.3673 0.9323
3.750 0.8216 0.00897 0.00360 -0.0778 0.3601 0.9386
4.000 0.8450 0.00911 0.00373 -0.0769 0.3544 0.9441
4.250 0.8688 0.00926 0.00386 -0.0762 0.3480 0.9493
4.750 0.9151 0.00960 0.00415 -0.0746 0.3353 0.9582
5.000 0.9363 0.00980 0.00431 -0.0734 0.3274 0.9634
5.250 0.9566 0.01000 0.00448 -0.0720 0.3204 0.9710
5.500 0.9798 0.01018 0.00466 -0.0712 0.3152 0.9796
5.750 1.0060 0.01042 0.00486 -0.0713 0.3093 0.9831
6.000 1.0328 0.01063 0.00506 -0.0715 0.3044 0.9856
6.250 1.0599 0.01083 0.00526 -0.0717 0.2996 0.9886
6.500 1.0853 0.01109 0.00549 -0.0717 0.2939 0.9924
6.750 1.1127 0.01135 0.00573 -0.0721 0.2887 0.9948
7.000 1.1398 0.01158 0.00596 -0.0725 0.2832 0.9979
7.250 1.1597 0.01187 0.00622 -0.0714 0.2766 1.0000
7.500 1.1783 0.01215 0.00648 -0.0701 0.2704 1.0000
7.750 1.1964 0.01252 0.00681 -0.0687 0.2605 1.0000
8.000 1.2138 0.01296 0.00719 -0.0674 0.2476 1.0000
8.250 1.2177 0.01408 0.00807 -0.0641 0.2037 1.0000
8.500 1.2193 0.01542 0.00918 -0.0607 0.1666 1.0000
8.750 1.2337 0.01614 0.00986 -0.0591 0.1556 1.0000
9.000 1.2483 0.01686 0.01054 -0.0577 0.1470 1.0000
9.250 1.2657 0.01746 0.01114 -0.0567 0.1403 1.0000
9.500 1.2798 0.01826 0.01189 -0.0553 0.1305 1.0000
10.000 1.2916 0.02094 0.01432 -0.0510 0.0850 1.0000
10.250 1.3055 0.02184 0.01522 -0.0498 0.0818 1.0000
10.500 1.3194 0.02275 0.01614 -0.0487 0.0786 1.0000
10.750 1.3343 0.02361 0.01703 -0.0478 0.0769 1.0000
11.000 1.3488 0.02452 0.01796 -0.0469 0.0755 1.0000
11.250 1.3618 0.02556 0.01903 -0.0459 0.0739 1.0000
11.500 1.3740 0.02665 0.02014 -0.0448 0.0723 1.0000
11.750 1.3855 0.02782 0.02134 -0.0438 0.0706 1.0000
12.000 1.3992 0.02885 0.02241 -0.0430 0.0696 1.0000
12.250 1.4129 0.02991 0.02351 -0.0423 0.0687 1.0000
12.500 1.4256 0.03107 0.02471 -0.0415 0.0675 1.0000
12.750 1.4371 0.03233 0.02601 -0.0407 0.0661 1.0000
13.000 1.4470 0.03374 0.02746 -0.0398 0.0647 1.0000
13.250 1.4562 0.03524 0.02899 -0.0390 0.0632 1.0000
13.500 1.4656 0.03678 0.03056 -0.0382 0.0618 1.0000
13.750 1.4770 0.03815 0.03198 -0.0376 0.0605 1.0000
14.000 1.4862 0.03973 0.03360 -0.0370 0.0586 1.0000
14.250 1.4937 0.04148 0.03538 -0.0363 0.0565 1.0000
14.500 1.5005 0.04333 0.03726 -0.0356 0.0544 1.0000
14.750 1.5073 0.04523 0.03919 -0.0350 0.0514 1.0000
15.000 1.5117 0.04739 0.04136 -0.0344 0.0478 1.0000
15.250 1.5140 0.04979 0.04377 -0.0337 0.0435 1.0000
15.500 1.5148 0.05239 0.04639 -0.0332 0.0401 1.0000
15.750 1.5144 0.05517 0.04921 -0.0327 0.0373 1.0000
16.000 1.5149 0.05792 0.05200 -0.0323 0.0351 1.0000
16.250 1.5132 0.06095 0.05507 -0.0319 0.0331 1.0000
16.500 1.5127 0.06388 0.05805 -0.0317 0.0316 1.0000
16.750 1.5108 0.06702 0.06126 -0.0315 0.0302 1.0000
17.000 1.5072 0.07040 0.06468 -0.0314 0.0289 1.0000
17.250 1.5061 0.07353 0.06787 -0.0314 0.0280 1.0000
17.500 1.5044 0.07673 0.07114 -0.0315 0.0270 1.0000
17.750 1.5009 0.08019 0.07466 -0.0316 0.0262 1.0000
18.000 1.4968 0.08375 0.07828 -0.0318 0.0254 1.0000
18.250 1.4939 0.08719 0.08178 -0.0321 0.0246 1.0000
18.500 1.4914 0.09062 0.08528 -0.0324 0.0241 1.0000
18.750 1.4887 0.09407 0.08880 -0.0328 0.0234 1.0000
19.000 1.4857 0.09756 0.09235 -0.0333 0.0227 1.0000
19.250 1.4811 0.10132 0.09618 -0.0339 0.0220 1.0000
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