GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.43 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe741-il-1000000.txt Download as CSV file: xf-goe741-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7891 0.06500 0.06195 -0.0330 0.6745 0.0264
-13.250 -0.7377 0.07048 0.06749 -0.0280 0.6612 0.0266
-13.000 -0.9049 0.04136 0.03765 -0.0496 0.6680 0.0261
-12.750 -0.9325 0.03815 0.03423 -0.0456 0.6620 0.0261
-12.500 -0.9548 0.03552 0.03138 -0.0405 0.6549 0.0262
-12.250 -0.9688 0.03240 0.02798 -0.0366 0.6480 0.0264
-12.000 -0.9654 0.03043 0.02582 -0.0341 0.6401 0.0265
-11.750 -0.9557 0.02891 0.02414 -0.0320 0.6309 0.0266
-11.500 -0.9417 0.02771 0.02284 -0.0303 0.6224 0.0268
-11.250 -0.9248 0.02680 0.02182 -0.0288 0.6132 0.0270
-11.000 -0.9064 0.02599 0.02092 -0.0275 0.6051 0.0272
-10.750 -0.8878 0.02513 0.01995 -0.0261 0.5968 0.0273
-10.500 -0.8679 0.02439 0.01909 -0.0249 0.5892 0.0275
-10.250 -0.8482 0.02351 0.01810 -0.0237 0.5823 0.0277
-10.000 -0.8277 0.02271 0.01716 -0.0225 0.5752 0.0279
-9.750 -0.8066 0.02190 0.01624 -0.0214 0.5691 0.0281
-9.500 -0.7849 0.02112 0.01534 -0.0203 0.5637 0.0283
-9.250 -0.7626 0.02038 0.01449 -0.0193 0.5584 0.0284
-9.000 -0.7398 0.01970 0.01368 -0.0183 0.5527 0.0287
-8.750 -0.7164 0.01902 0.01291 -0.0174 0.5493 0.0288
-8.500 -0.6924 0.01841 0.01221 -0.0166 0.5452 0.0291
-8.250 -0.6679 0.01786 0.01156 -0.0158 0.5409 0.0293
-8.000 -0.6431 0.01737 0.01096 -0.0151 0.5362 0.0295
-7.750 -0.6178 0.01692 0.01043 -0.0144 0.5324 0.0297
-7.500 -0.5919 0.01652 0.00996 -0.0138 0.5297 0.0298
-7.250 -0.5672 0.01581 0.00918 -0.0130 0.5267 0.0301
-7.000 -0.5433 0.01500 0.00831 -0.0122 0.5235 0.0305
-6.750 -0.5176 0.01454 0.00780 -0.0116 0.5200 0.0308
-6.500 -0.4915 0.01420 0.00741 -0.0111 0.5159 0.0312
-6.250 -0.4648 0.01387 0.00706 -0.0106 0.5132 0.0315
-6.000 -0.4378 0.01357 0.00674 -0.0101 0.5110 0.0320
-5.750 -0.4107 0.01329 0.00644 -0.0097 0.5085 0.0325
-5.500 -0.3835 0.01301 0.00612 -0.0093 0.5059 0.0329
-5.250 -0.3564 0.01274 0.00580 -0.0089 0.5031 0.0333
-5.000 -0.3291 0.01250 0.00551 -0.0085 0.5000 0.0336
-4.500 -0.2752 0.01191 0.00485 -0.0076 0.4944 0.0345
-4.250 -0.2481 0.01159 0.00453 -0.0072 0.4924 0.0352
-4.000 -0.2204 0.01136 0.00431 -0.0068 0.4902 0.0359
-3.750 -0.1926 0.01117 0.00410 -0.0065 0.4879 0.0367
-3.500 -0.1647 0.01100 0.00391 -0.0063 0.4854 0.0375
-3.250 -0.1368 0.01086 0.00374 -0.0060 0.4826 0.0383
-3.000 -0.1094 0.01067 0.00351 -0.0056 0.4793 0.0395
-2.750 -0.0817 0.01052 0.00337 -0.0053 0.4768 0.0409
-2.500 -0.0535 0.01037 0.00323 -0.0051 0.4752 0.0426
-2.250 -0.0255 0.01020 0.00307 -0.0049 0.4733 0.0447
-2.000 0.0025 0.01004 0.00293 -0.0046 0.4710 0.0475
-1.750 0.0304 0.00988 0.00279 -0.0044 0.4685 0.0519
-1.500 0.0580 0.00973 0.00267 -0.0041 0.4660 0.0597
-1.250 0.0855 0.00959 0.00260 -0.0038 0.4634 0.0746
-1.000 0.1132 0.00955 0.00258 -0.0036 0.4601 0.0884
-0.750 0.1416 0.00948 0.00255 -0.0034 0.4582 0.0969
-0.500 0.1696 0.00937 0.00249 -0.0033 0.4562 0.1058
-0.250 0.1979 0.00929 0.00243 -0.0031 0.4536 0.1131
0.000 0.2260 0.00920 0.00237 -0.0029 0.4505 0.1214
0.250 0.2537 0.00911 0.00231 -0.0027 0.4468 0.1346
0.500 0.2808 0.00905 0.00233 -0.0025 0.4422 0.1663
0.750 0.3089 0.00896 0.00234 -0.0023 0.4399 0.1914
1.000 0.3373 0.00892 0.00234 -0.0022 0.4375 0.2060
1.250 0.3655 0.00888 0.00234 -0.0021 0.4351 0.2198
1.500 0.3935 0.00883 0.00234 -0.0020 0.4324 0.2365
1.750 0.4213 0.00880 0.00235 -0.0019 0.4296 0.2532
2.000 0.4488 0.00880 0.00237 -0.0017 0.4263 0.2712
2.250 0.4761 0.00874 0.00241 -0.0015 0.4237 0.3041
2.500 0.4946 0.00805 0.00240 0.0002 0.4216 0.5402
2.750 0.5017 0.00697 0.00251 0.0049 0.4193 0.9166
3.000 0.5390 0.00710 0.00266 0.0033 0.4159 0.9429
3.250 0.5705 0.00724 0.00278 0.0028 0.4124 0.9545
3.500 0.6094 0.00748 0.00296 0.0007 0.4082 0.9610
3.750 0.6360 0.00759 0.00308 0.0012 0.4058 0.9673
4.000 0.6820 0.00774 0.00322 -0.0024 0.4025 0.9688
4.250 0.7277 0.00792 0.00337 -0.0060 0.3985 0.9705
4.500 0.7726 0.00812 0.00353 -0.0095 0.3941 0.9729
4.750 0.8091 0.00828 0.00366 -0.0112 0.3902 0.9752
5.000 0.8421 0.00839 0.00377 -0.0122 0.3866 0.9782
5.250 0.8756 0.00854 0.00390 -0.0133 0.3814 0.9812
5.500 0.9142 0.00869 0.00399 -0.0157 0.3748 0.9822
5.750 0.9509 0.00875 0.00407 -0.0175 0.3709 0.9832
6.000 0.9845 0.00885 0.00415 -0.0188 0.3655 0.9841
6.250 1.0160 0.00900 0.00426 -0.0197 0.3596 0.9850
6.500 1.0496 0.00909 0.00436 -0.0210 0.3546 0.9862
6.750 1.0814 0.00922 0.00448 -0.0220 0.3485 0.9874
7.000 1.1104 0.00941 0.00463 -0.0225 0.3422 0.9886
7.250 1.1395 0.00953 0.00476 -0.0229 0.3364 0.9896
7.500 1.1683 0.00976 0.00495 -0.0234 0.3286 0.9912
7.750 1.1992 0.00995 0.00514 -0.0243 0.3221 0.9930
8.000 1.2316 0.01015 0.00531 -0.0256 0.3142 0.9937
8.250 1.2671 0.01035 0.00549 -0.0275 0.3068 0.9949
8.500 1.2983 0.01062 0.00573 -0.0287 0.2980 0.9959
8.750 1.3275 0.01086 0.00596 -0.0294 0.2900 0.9968
9.000 1.3546 0.01122 0.00627 -0.0299 0.2809 0.9977
9.250 1.3825 0.01148 0.00652 -0.0304 0.2739 0.9984
9.500 1.4095 0.01187 0.00688 -0.0309 0.2659 0.9992
9.750 1.4378 0.01214 0.00716 -0.0315 0.2611 0.9999
10.000 1.4598 0.01246 0.00748 -0.0310 0.2561 1.0000
10.250 1.4779 0.01288 0.00789 -0.0298 0.2510 1.0000
10.500 1.4964 0.01321 0.00824 -0.0286 0.2470 1.0000
10.750 1.5138 0.01357 0.00861 -0.0273 0.2424 1.0000
11.000 1.5283 0.01403 0.00908 -0.0255 0.2382 1.0000
11.250 1.5389 0.01459 0.00964 -0.0233 0.2339 1.0000
11.500 1.5524 0.01495 0.01005 -0.0213 0.2318 1.0000
11.750 1.5613 0.01542 0.01056 -0.0188 0.2288 1.0000
12.000 1.5513 0.01617 0.01135 -0.0135 0.2261 1.0000
12.250 1.5369 0.01744 0.01266 -0.0088 0.2235 1.0000
12.500 1.5314 0.01898 0.01420 -0.0060 0.2195 1.0000
12.750 1.5391 0.01997 0.01525 -0.0046 0.2163 1.0000
13.000 1.5450 0.02118 0.01650 -0.0032 0.2132 1.0000
13.250 1.5481 0.02268 0.01802 -0.0019 0.2098 1.0000
13.500 1.5476 0.02456 0.01991 -0.0006 0.2059 1.0000
13.750 1.5529 0.02606 0.02146 0.0003 0.2025 1.0000
14.000 1.5590 0.02755 0.02299 0.0011 0.1986 1.0000
14.250 1.5577 0.02971 0.02516 0.0019 0.1936 1.0000
14.500 1.5560 0.03195 0.02743 0.0026 0.1894 1.0000
14.750 1.5607 0.03368 0.02920 0.0031 0.1848 1.0000
15.000 1.5579 0.03611 0.03165 0.0037 0.1795 1.0000
15.250 1.5537 0.03876 0.03431 0.0041 0.1729 1.0000
15.500 1.5469 0.04177 0.03732 0.0044 0.1649 1.0000
15.750 1.5434 0.04449 0.04006 0.0046 0.1583 1.0000
16.000 1.5319 0.04807 0.04362 0.0048 0.1492 1.0000
16.250 1.5198 0.05181 0.04733 0.0048 0.1402 1.0000
16.500 1.5108 0.05530 0.05084 0.0047 0.1338 1.0000
16.750 1.5009 0.05893 0.05447 0.0045 0.1277 1.0000
17.000 1.4959 0.06211 0.05767 0.0043 0.1231 1.0000
17.250 1.4889 0.06556 0.06114 0.0040 0.1186 1.0000
17.500 1.4828 0.06898 0.06457 0.0036 0.1147 1.0000
17.750 1.4817 0.07185 0.06749 0.0033 0.1115 1.0000
18.000 1.4770 0.07516 0.07083 0.0028 0.1078 1.0000
18.250 1.4681 0.07908 0.07477 0.0022 0.1038 1.0000
18.500 1.4689 0.08181 0.07755 0.0017 0.1004 1.0000
18.750 1.4596 0.08584 0.08159 0.0009 0.0952 1.0000
19.000 1.4537 0.08950 0.08527 0.0001 0.0886 1.0000
19.250 1.4399 0.09424 0.09001 -0.0010 0.0804 1.0000
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Polar data table (+)
Polar graphs
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