GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.58 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe526-il-1000000-n5.txt Download as CSV file: xf-goe526-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 526 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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1203 0.03353 0.03033 -0.1057 1.0000 0.0224
-15.750 -1.1362 0.03126 0.02793 -0.1029 1.0000 0.0224
-15.500 -1.1521 0.02987 0.02645 -0.0979 1.0000 0.0225
-15.250 -1.1471 0.02866 0.02516 -0.0957 0.9992 0.0228
-15.000 -1.1264 0.02723 0.02362 -0.0966 0.9966 0.0230
-14.750 -1.1071 0.02597 0.02224 -0.0968 0.9926 0.0232
-14.500 -1.0866 0.02492 0.02109 -0.0968 0.9889 0.0235
-14.250 -1.0627 0.02400 0.02008 -0.0973 0.9856 0.0238
-14.000 -1.0374 0.02306 0.01902 -0.0979 0.9831 0.0240
-13.750 -1.0144 0.02223 0.01809 -0.0979 0.9790 0.0242
-13.500 -0.9906 0.02129 0.01705 -0.0981 0.9750 0.0243
-13.250 -0.9640 0.02024 0.01593 -0.0990 0.9721 0.0248
-13.000 -0.9339 0.01946 0.01509 -0.1003 0.9696 0.0251
-12.750 -0.9076 0.01879 0.01435 -0.1006 0.9638 0.0253
-12.500 -0.8775 0.01815 0.01365 -0.1016 0.9590 0.0256
-12.250 -0.8478 0.01757 0.01300 -0.1024 0.9539 0.0260
-12.000 -0.8212 0.01701 0.01236 -0.1026 0.9461 0.0262
-11.750 -0.7938 0.01648 0.01174 -0.1028 0.9384 0.0265
-11.500 -0.7689 0.01601 0.01119 -0.1025 0.9277 0.0268
-11.250 -0.7441 0.01561 0.01070 -0.1020 0.9166 0.0271
-11.000 -0.7202 0.01520 0.01019 -0.1013 0.9045 0.0274
-10.750 -0.6969 0.01482 0.00971 -0.1005 0.8916 0.0276
-10.500 -0.6739 0.01445 0.00923 -0.0996 0.8783 0.0278
-10.250 -0.6504 0.01414 0.00882 -0.0987 0.8654 0.0280
-10.000 -0.6284 0.01372 0.00829 -0.0976 0.8528 0.0283
-9.750 -0.6057 0.01334 0.00783 -0.0966 0.8411 0.0287
-9.500 -0.5820 0.01301 0.00743 -0.0958 0.8315 0.0290
-9.000 -0.5335 0.01245 0.00674 -0.0943 0.8135 0.0297
-8.750 -0.5089 0.01221 0.00643 -0.0935 0.8048 0.0302
-8.500 -0.4837 0.01197 0.00614 -0.0929 0.7977 0.0306
-8.250 -0.4586 0.01173 0.00584 -0.0923 0.7907 0.0310
-8.000 -0.4334 0.01150 0.00554 -0.0916 0.7844 0.0314
-7.750 -0.4076 0.01128 0.00527 -0.0911 0.7781 0.0318
-7.500 -0.3819 0.01108 0.00501 -0.0905 0.7716 0.0321
-7.250 -0.3565 0.01083 0.00471 -0.0899 0.7661 0.0326
-7.000 -0.3305 0.01059 0.00445 -0.0894 0.7610 0.0332
-6.750 -0.3046 0.01039 0.00422 -0.0889 0.7550 0.0339
-6.500 -0.2788 0.01022 0.00401 -0.0883 0.7483 0.0345
-6.250 -0.2525 0.01005 0.00380 -0.0879 0.7408 0.0352
-6.000 -0.2264 0.00991 0.00361 -0.0873 0.7336 0.0359
-5.750 -0.1998 0.00977 0.00343 -0.0869 0.7278 0.0367
-5.500 -0.1735 0.00959 0.00324 -0.0864 0.7214 0.0378
-5.000 -0.1207 0.00931 0.00291 -0.0855 0.7086 0.0401
-4.750 -0.0941 0.00920 0.00277 -0.0851 0.7016 0.0414
-4.500 -0.0677 0.00909 0.00262 -0.0846 0.6948 0.0427
-4.250 -0.0410 0.00895 0.00249 -0.0842 0.6881 0.0446
-4.000 -0.0142 0.00885 0.00237 -0.0838 0.6825 0.0464
-3.750 0.0126 0.00877 0.00226 -0.0834 0.6775 0.0482
-3.500 0.0395 0.00864 0.00215 -0.0830 0.6720 0.0510
-3.250 0.0663 0.00856 0.00205 -0.0826 0.6658 0.0536
-3.000 0.0930 0.00847 0.00196 -0.0822 0.6605 0.0565
-2.750 0.1201 0.00837 0.00187 -0.0819 0.6551 0.0599
-2.500 0.1468 0.00830 0.00179 -0.0815 0.6483 0.0633
-2.250 0.1734 0.00823 0.00172 -0.0810 0.6416 0.0678
-2.000 0.2002 0.00816 0.00166 -0.0806 0.6341 0.0728
-1.750 0.2265 0.00811 0.00161 -0.0801 0.6268 0.0793
-1.500 0.2533 0.00803 0.00156 -0.0798 0.6193 0.0874
-1.250 0.2792 0.00801 0.00153 -0.0792 0.6086 0.0955
-1.000 0.3053 0.00799 0.00150 -0.0787 0.5953 0.1042
-0.750 0.3304 0.00801 0.00149 -0.0780 0.5769 0.1144
-0.500 0.3553 0.00805 0.00149 -0.0772 0.5565 0.1232
-0.250 0.3802 0.00812 0.00150 -0.0765 0.5346 0.1299
0.000 0.4047 0.00821 0.00152 -0.0757 0.5124 0.1373
0.250 0.4291 0.00832 0.00156 -0.0749 0.4905 0.1439
0.500 0.4536 0.00842 0.00160 -0.0741 0.4698 0.1504
0.750 0.4778 0.00854 0.00165 -0.0733 0.4495 0.1577
1.250 0.5269 0.00873 0.00177 -0.0718 0.4188 0.1765
1.500 0.5518 0.00876 0.00183 -0.0711 0.4091 0.1938
1.750 0.5770 0.00878 0.00189 -0.0704 0.4014 0.2168
2.000 0.6013 0.00877 0.00195 -0.0697 0.3926 0.2560
2.250 0.6249 0.00870 0.00203 -0.0688 0.3849 0.3225
2.750 0.6595 0.00791 0.00221 -0.0646 0.3715 0.6912
3.000 0.6835 0.00747 0.00243 -0.0635 0.3655 0.9375
3.250 0.7349 0.00769 0.00262 -0.0686 0.3561 0.9622
3.500 0.7727 0.00785 0.00275 -0.0707 0.3497 0.9709
3.750 0.8090 0.00802 0.00288 -0.0725 0.3420 0.9769
4.000 0.8427 0.00822 0.00303 -0.0738 0.3328 0.9836
4.250 0.8810 0.00847 0.00320 -0.0762 0.3189 0.9883
4.500 0.9130 0.00866 0.00335 -0.0771 0.3082 0.9916
4.750 0.9443 0.00889 0.00350 -0.0780 0.2945 0.9941
5.000 0.9796 0.00912 0.00367 -0.0798 0.2811 0.9967
5.250 1.0123 0.00941 0.00385 -0.0810 0.2619 0.9987
5.500 1.0411 0.00980 0.00410 -0.0815 0.2361 1.0000
5.750 1.0512 0.01030 0.00440 -0.0782 0.2001 1.0000
6.000 1.0629 0.01073 0.00470 -0.0750 0.1779 1.0000
6.250 1.0778 0.01102 0.00494 -0.0725 0.1678 1.0000
6.500 1.0941 0.01127 0.00516 -0.0703 0.1607 1.0000
6.750 1.1104 0.01152 0.00538 -0.0680 0.1553 1.0000
7.000 1.1267 0.01176 0.00561 -0.0657 0.1503 1.0000
7.250 1.1442 0.01196 0.00581 -0.0637 0.1470 1.0000
7.500 1.1587 0.01217 0.00602 -0.0611 0.1431 1.0000
7.750 1.1721 0.01242 0.00625 -0.0583 0.1385 1.0000
8.000 1.1871 0.01267 0.00649 -0.0559 0.1347 1.0000
8.250 1.2034 0.01291 0.00674 -0.0537 0.1296 1.0000
8.500 1.2187 0.01322 0.00703 -0.0515 0.1239 1.0000
8.750 1.2351 0.01353 0.00732 -0.0495 0.1185 1.0000
9.000 1.2497 0.01393 0.00768 -0.0473 0.1096 1.0000
9.250 1.2628 0.01443 0.00811 -0.0450 0.0973 1.0000
9.500 1.2768 0.01493 0.00856 -0.0429 0.0889 1.0000
9.750 1.2911 0.01543 0.00903 -0.0408 0.0825 1.0000
10.000 1.3048 0.01598 0.00956 -0.0388 0.0773 1.0000
10.250 1.3205 0.01645 0.01005 -0.0372 0.0740 1.0000
10.500 1.3355 0.01698 0.01058 -0.0355 0.0709 1.0000
10.750 1.3494 0.01759 0.01119 -0.0337 0.0676 1.0000
11.000 1.3648 0.01813 0.01175 -0.0322 0.0653 1.0000
11.250 1.3797 0.01873 0.01237 -0.0307 0.0629 1.0000
11.500 1.3928 0.01945 0.01310 -0.0291 0.0600 1.0000
11.750 1.4065 0.02016 0.01382 -0.0276 0.0578 1.0000
12.000 1.4209 0.02085 0.01454 -0.0262 0.0559 1.0000
12.250 1.4333 0.02169 0.01540 -0.0248 0.0533 1.0000
12.500 1.4449 0.02261 0.01633 -0.0233 0.0509 1.0000
12.750 1.4582 0.02345 0.01719 -0.0221 0.0491 1.0000
13.000 1.4699 0.02441 0.01818 -0.0209 0.0471 1.0000
13.250 1.4801 0.02551 0.01930 -0.0195 0.0451 1.0000
13.500 1.4914 0.02656 0.02038 -0.0184 0.0437 1.0000
13.750 1.5026 0.02764 0.02150 -0.0173 0.0423 1.0000
14.000 1.5125 0.02885 0.02274 -0.0162 0.0410 1.0000
14.250 1.5204 0.03023 0.02415 -0.0151 0.0393 1.0000
14.500 1.5294 0.03155 0.02551 -0.0141 0.0382 1.0000
14.750 1.5383 0.03292 0.02694 -0.0132 0.0373 1.0000
15.000 1.5460 0.03444 0.02849 -0.0123 0.0358 1.0000
15.250 1.5520 0.03611 0.03020 -0.0114 0.0346 1.0000
15.500 1.5586 0.03778 0.03192 -0.0106 0.0340 1.0000
15.750 1.5640 0.03961 0.03381 -0.0099 0.0329 1.0000
16.000 1.5699 0.04144 0.03570 -0.0093 0.0321 1.0000
16.250 1.5744 0.04342 0.03773 -0.0087 0.0312 1.0000
16.500 1.5779 0.04557 0.03993 -0.0082 0.0303 1.0000
16.750 1.5799 0.04793 0.04234 -0.0078 0.0295 1.0000
17.000 1.5814 0.05040 0.04488 -0.0076 0.0287 1.0000
17.250 1.5838 0.05282 0.04737 -0.0074 0.0281 1.0000
17.500 1.5847 0.05545 0.05006 -0.0073 0.0270 1.0000
17.750 1.5844 0.05827 0.05295 -0.0073 0.0263 1.0000
18.000 1.5831 0.06129 0.05604 -0.0075 0.0257 1.0000
18.250 1.5791 0.06468 0.05949 -0.0078 0.0249 1.0000
18.500 1.5775 0.06783 0.06273 -0.0081 0.0243 1.0000
18.750 1.5745 0.07122 0.06620 -0.0086 0.0238 1.0000
19.000 1.5697 0.07487 0.06993 -0.0093 0.0228 1.0000
19.250 1.5636 0.07877 0.07389 -0.0101 0.0221 1.0000
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