GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.49 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe526-il-1000000.txt Download as CSV file: xf-goe526-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9593 0.03603 0.03318 -0.1015 1.0000 0.0263
-14.250 -0.9804 0.03375 0.03078 -0.0983 1.0000 0.0264
-14.000 -1.0061 0.03255 0.02950 -0.0916 1.0000 0.0265
-13.750 -1.0197 0.03119 0.02804 -0.0866 0.9997 0.0266
-13.500 -0.9972 0.02935 0.02604 -0.0883 0.9975 0.0269
-13.250 -0.9734 0.02776 0.02430 -0.0898 0.9950 0.0272
-13.000 -0.9485 0.02637 0.02277 -0.0911 0.9926 0.0275
-12.750 -0.9241 0.02529 0.02156 -0.0917 0.9893 0.0278
-12.500 -0.8956 0.02447 0.02062 -0.0928 0.9866 0.0281
-12.250 -0.8733 0.02243 0.01837 -0.0939 0.9839 0.0285
-12.000 -0.8461 0.02102 0.01686 -0.0951 0.9822 0.0290
-11.750 -0.8216 0.02023 0.01602 -0.0951 0.9778 0.0293
-11.500 -0.7924 0.01953 0.01526 -0.0959 0.9746 0.0297
-11.250 -0.7602 0.01894 0.01463 -0.0973 0.9723 0.0301
-11.000 -0.7272 0.01829 0.01391 -0.0988 0.9700 0.0306
-10.750 -0.6989 0.01763 0.01316 -0.0993 0.9651 0.0310
-10.500 -0.6709 0.01698 0.01242 -0.0996 0.9591 0.0314
-10.250 -0.6389 0.01634 0.01168 -0.1008 0.9544 0.0318
-10.000 -0.6146 0.01588 0.01113 -0.1002 0.9447 0.0321
-9.750 -0.5864 0.01543 0.01058 -0.1003 0.9368 0.0323
-9.500 -0.5669 0.01440 0.00943 -0.0991 0.9250 0.0330
-9.250 -0.5435 0.01390 0.00887 -0.0983 0.9139 0.0335
-9.000 -0.5186 0.01356 0.00847 -0.0976 0.9027 0.0341
-8.750 -0.4947 0.01322 0.00806 -0.0968 0.8902 0.0345
-8.500 -0.4705 0.01290 0.00767 -0.0960 0.8783 0.0351
-8.250 -0.4462 0.01258 0.00725 -0.0952 0.8674 0.0356
-8.000 -0.4217 0.01230 0.00688 -0.0944 0.8565 0.0361
-7.750 -0.3969 0.01204 0.00654 -0.0937 0.8466 0.0366
-7.500 -0.3719 0.01182 0.00623 -0.0929 0.8370 0.0369
-7.250 -0.3490 0.01129 0.00563 -0.0919 0.8284 0.0377
-7.000 -0.3244 0.01099 0.00528 -0.0912 0.8204 0.0385
-6.750 -0.2988 0.01078 0.00504 -0.0906 0.8130 0.0394
-6.500 -0.2732 0.01060 0.00480 -0.0900 0.8049 0.0403
-6.250 -0.2476 0.01040 0.00455 -0.0894 0.7969 0.0411
-6.000 -0.2216 0.01024 0.00432 -0.0888 0.7890 0.0418
-5.750 -0.1966 0.00997 0.00399 -0.0881 0.7820 0.0428
-5.500 -0.1709 0.00970 0.00372 -0.0875 0.7754 0.0443
-5.250 -0.1448 0.00955 0.00353 -0.0869 0.7684 0.0455
-5.000 -0.1184 0.00942 0.00336 -0.0865 0.7622 0.0470
-4.750 -0.0919 0.00926 0.00317 -0.0860 0.7555 0.0484
-4.500 -0.0663 0.00906 0.00295 -0.0854 0.7490 0.0508
-4.250 -0.0395 0.00893 0.00281 -0.0850 0.7433 0.0529
-4.000 -0.0128 0.00880 0.00266 -0.0845 0.7377 0.0550
-3.750 0.0133 0.00863 0.00249 -0.0840 0.7323 0.0584
-3.500 0.0403 0.00854 0.00238 -0.0836 0.7273 0.0612
-3.250 0.0669 0.00837 0.00223 -0.0832 0.7221 0.0656
-3.000 0.0937 0.00829 0.00214 -0.0828 0.7170 0.0696
-2.750 0.1200 0.00817 0.00203 -0.0823 0.7117 0.0756
-2.500 0.1471 0.00805 0.00194 -0.0820 0.7066 0.0817
-2.250 0.1738 0.00796 0.00187 -0.0816 0.7009 0.0892
-2.000 0.2002 0.00788 0.00180 -0.0811 0.6955 0.0990
-1.750 0.2273 0.00779 0.00176 -0.0808 0.6905 0.1093
-1.500 0.2543 0.00772 0.00172 -0.0804 0.6848 0.1191
-1.250 0.2808 0.00770 0.00169 -0.0800 0.6785 0.1280
-1.000 0.3078 0.00762 0.00166 -0.0796 0.6719 0.1373
-0.750 0.3344 0.00761 0.00163 -0.0792 0.6635 0.1444
-0.500 0.3609 0.00756 0.00160 -0.0787 0.6562 0.1538
-0.250 0.3876 0.00754 0.00158 -0.0783 0.6480 0.1610
0.000 0.4137 0.00750 0.00155 -0.0778 0.6393 0.1713
0.250 0.4399 0.00749 0.00153 -0.0773 0.6289 0.1807
0.500 0.4658 0.00745 0.00152 -0.0767 0.6180 0.1953
0.750 0.4908 0.00742 0.00152 -0.0760 0.6047 0.2180
1.000 0.5148 0.00734 0.00154 -0.0751 0.5899 0.2672
1.250 0.5359 0.00707 0.00157 -0.0738 0.5744 0.3919
1.500 0.5513 0.00656 0.00163 -0.0713 0.5576 0.6163
1.750 0.5685 0.00592 0.00184 -0.0686 0.5385 0.9325
2.000 0.6137 0.00620 0.00202 -0.0722 0.5103 0.9599
2.250 0.6515 0.00650 0.00218 -0.0743 0.4827 0.9712
2.500 0.6898 0.00683 0.00237 -0.0765 0.4593 0.9793
2.750 0.7310 0.00711 0.00254 -0.0794 0.4410 0.9840
3.000 0.7738 0.00734 0.00268 -0.0826 0.4262 0.9878
3.250 0.8105 0.00753 0.00281 -0.0845 0.4140 0.9914
3.500 0.8500 0.00773 0.00294 -0.0870 0.4037 0.9944
3.750 0.8973 0.00790 0.00304 -0.0913 0.3921 0.9977
4.000 0.9387 0.00803 0.00312 -0.0943 0.3808 1.0000
4.250 0.9586 0.00820 0.00323 -0.0927 0.3712 1.0000
4.500 0.9800 0.00830 0.00332 -0.0913 0.3630 1.0000
4.750 0.9996 0.00847 0.00344 -0.0897 0.3539 1.0000
5.000 1.0206 0.00857 0.00354 -0.0883 0.3469 1.0000
5.500 1.0599 0.00887 0.00378 -0.0849 0.3294 1.0000
5.750 1.0783 0.00906 0.00392 -0.0830 0.3195 1.0000
6.000 1.0969 0.00923 0.00406 -0.0811 0.3084 1.0000
6.250 1.1153 0.00941 0.00422 -0.0792 0.2982 1.0000
6.500 1.1320 0.00965 0.00439 -0.0770 0.2840 1.0000
6.750 1.1476 0.00993 0.00459 -0.0746 0.2663 1.0000
7.000 1.1599 0.01033 0.00486 -0.0716 0.2408 1.0000
7.250 1.1695 0.01084 0.00520 -0.0682 0.2091 1.0000
7.500 1.1796 0.01134 0.00556 -0.0648 0.1864 1.0000
7.750 1.1920 0.01171 0.00587 -0.0619 0.1749 1.0000
8.000 1.2022 0.01206 0.00617 -0.0585 0.1661 1.0000
8.250 1.2166 0.01231 0.00642 -0.0559 0.1614 1.0000
8.500 1.2298 0.01264 0.00673 -0.0532 0.1554 1.0000
8.750 1.2451 0.01295 0.00704 -0.0510 0.1501 1.0000
9.000 1.2620 0.01323 0.00733 -0.0490 0.1458 1.0000
9.250 1.2770 0.01360 0.00769 -0.0469 0.1401 1.0000
9.500 1.2936 0.01394 0.00803 -0.0451 0.1349 1.0000
9.750 1.3096 0.01433 0.00840 -0.0432 0.1276 1.0000
10.000 1.3251 0.01475 0.00881 -0.0413 0.1198 1.0000
10.250 1.3386 0.01530 0.00929 -0.0392 0.1084 1.0000
10.500 1.3509 0.01593 0.00986 -0.0371 0.0969 1.0000
10.750 1.3622 0.01664 0.01050 -0.0348 0.0875 1.0000
11.000 1.3749 0.01730 0.01116 -0.0329 0.0819 1.0000
11.250 1.3869 0.01803 0.01188 -0.0310 0.0768 1.0000
11.500 1.4003 0.01872 0.01257 -0.0293 0.0730 1.0000
11.750 1.4111 0.01958 0.01342 -0.0274 0.0689 1.0000
12.000 1.4251 0.02027 0.01415 -0.0260 0.0665 1.0000
12.250 1.4376 0.02109 0.01499 -0.0245 0.0635 1.0000
12.500 1.4473 0.02211 0.01601 -0.0228 0.0602 1.0000
12.750 1.4606 0.02293 0.01687 -0.0215 0.0585 1.0000
13.000 1.4726 0.02386 0.01783 -0.0202 0.0561 1.0000
13.250 1.4825 0.02497 0.01895 -0.0189 0.0539 1.0000
13.500 1.4919 0.02614 0.02016 -0.0175 0.0517 1.0000
13.750 1.5035 0.02718 0.02125 -0.0164 0.0502 1.0000
14.000 1.5127 0.02843 0.02252 -0.0153 0.0483 1.0000
14.250 1.5197 0.02988 0.02399 -0.0140 0.0463 1.0000
14.500 1.5279 0.03126 0.02542 -0.0130 0.0450 1.0000
14.750 1.5371 0.03261 0.02682 -0.0121 0.0438 1.0000
15.000 1.5446 0.03413 0.02838 -0.0112 0.0422 1.0000
15.250 1.5492 0.03592 0.03021 -0.0102 0.0408 1.0000
15.500 1.5530 0.03785 0.03218 -0.0093 0.0393 1.0000
15.750 1.5600 0.03954 0.03394 -0.0087 0.0386 1.0000
16.000 1.5658 0.04138 0.03584 -0.0081 0.0373 1.0000
16.250 1.5690 0.04350 0.03800 -0.0075 0.0363 1.0000
16.500 1.5702 0.04588 0.04044 -0.0070 0.0353 1.0000
16.750 1.5688 0.04863 0.04324 -0.0066 0.0342 1.0000
17.000 1.5734 0.05079 0.04548 -0.0064 0.0335 1.0000
17.250 1.5752 0.05329 0.04806 -0.0062 0.0327 1.0000
17.500 1.5754 0.05602 0.05085 -0.0062 0.0318 1.0000
17.750 1.5728 0.05916 0.05404 -0.0063 0.0308 1.0000
18.000 1.5671 0.06275 0.05770 -0.0066 0.0301 1.0000
18.250 1.5632 0.06618 0.06122 -0.0069 0.0294 1.0000
18.500 1.5634 0.06914 0.06426 -0.0073 0.0287 1.0000
18.750 1.5596 0.07269 0.06789 -0.0079 0.0280 1.0000
19.000 1.5543 0.07648 0.07176 -0.0086 0.0274 1.0000
19.250 1.5466 0.08061 0.07597 -0.0095 0.0268 1.0000
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Polar data table (+)
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