GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 500,000 Max Cl/Cd: 92.4 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe654-il-500000-n5.txt Download as CSV file: xf-goe654-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2469 0.11571 0.11336 -0.0410 0.9906 0.0186
-11.500 -0.2407 0.11076 0.10840 -0.0444 0.9769 0.0191
-11.250 -0.2407 0.10222 0.09984 -0.0515 0.9570 0.0199
-11.000 -0.2077 0.09806 0.09562 -0.0594 0.9385 0.0202
-10.750 -0.1650 0.09312 0.09060 -0.0702 0.9224 0.0206
-10.500 -0.1212 0.08731 0.08463 -0.0827 0.8968 0.0213
-10.250 -0.1005 0.08204 0.07916 -0.0903 0.8603 0.0221
-10.000 -0.0992 0.07773 0.07470 -0.0931 0.8283 0.0223
-9.500 -0.2143 0.04786 0.04470 -0.1107 0.7909 0.0232
-9.250 -0.2966 0.03612 0.03236 -0.1145 0.7713 0.0231
-9.000 -0.3153 0.03118 0.02685 -0.1127 0.7573 0.0233
-8.750 -0.3128 0.02845 0.02367 -0.1110 0.7440 0.0235
-8.500 -0.3033 0.02627 0.02117 -0.1095 0.7315 0.0237
-8.250 -0.2885 0.02465 0.01933 -0.1084 0.7192 0.0239
-8.000 -0.2702 0.02359 0.01809 -0.1073 0.7064 0.0241
-7.750 -0.2504 0.02268 0.01704 -0.1064 0.6928 0.0243
-7.500 -0.2296 0.02189 0.01608 -0.1055 0.6788 0.0246
-7.250 -0.2079 0.02125 0.01531 -0.1047 0.6646 0.0249
-7.000 -0.1866 0.02037 0.01423 -0.1038 0.6513 0.0251
-6.750 -0.1649 0.01952 0.01319 -0.1029 0.6379 0.0253
-6.250 -0.1199 0.01805 0.01131 -0.1011 0.6084 0.0258
-6.000 -0.0967 0.01741 0.01048 -0.1003 0.5938 0.0260
-5.750 -0.0729 0.01682 0.00972 -0.0995 0.5816 0.0262
-5.500 -0.0488 0.01629 0.00903 -0.0988 0.5714 0.0265
-5.250 -0.0239 0.01577 0.00838 -0.0982 0.5631 0.0267
-5.000 0.0009 0.01533 0.00781 -0.0975 0.5550 0.0269
-4.750 0.0263 0.01490 0.00728 -0.0970 0.5469 0.0272
-4.250 0.0777 0.01431 0.00649 -0.0959 0.5342 0.0278
-4.000 0.1038 0.01402 0.00613 -0.0955 0.5294 0.0280
-3.750 0.1285 0.01349 0.00555 -0.0948 0.5245 0.0284
-3.500 0.1539 0.01313 0.00516 -0.0943 0.5201 0.0287
-3.250 0.1799 0.01282 0.00483 -0.0938 0.5156 0.0290
-3.000 0.2059 0.01257 0.00456 -0.0934 0.5114 0.0294
-2.750 0.2318 0.01236 0.00432 -0.0929 0.5073 0.0298
-2.500 0.2579 0.01218 0.00410 -0.0925 0.5036 0.0302
-2.250 0.2845 0.01198 0.00390 -0.0921 0.4997 0.0306
-2.000 0.3109 0.01182 0.00371 -0.0917 0.4949 0.0310
-1.750 0.3372 0.01169 0.00355 -0.0913 0.4903 0.0315
-1.500 0.3636 0.01158 0.00340 -0.0909 0.4862 0.0320
-1.250 0.3906 0.01147 0.00328 -0.0906 0.4820 0.0327
-1.000 0.4173 0.01136 0.00315 -0.0902 0.4774 0.0335
-0.750 0.4436 0.01126 0.00302 -0.0898 0.4728 0.0346
-0.500 0.4703 0.01119 0.00294 -0.0895 0.4682 0.0357
-0.250 0.4973 0.01113 0.00286 -0.0892 0.4625 0.0368
0.000 0.5236 0.01111 0.00280 -0.0888 0.4561 0.0382
0.250 0.5503 0.01108 0.00276 -0.0884 0.4501 0.0405
0.750 0.6010 0.01072 0.00272 -0.0875 0.4367 0.1565
1.000 0.6245 0.01027 0.00276 -0.0869 0.4290 0.3298
1.250 0.6484 0.01010 0.00282 -0.0862 0.4207 0.4323
1.500 0.6716 0.00989 0.00291 -0.0853 0.4107 0.5419
1.750 0.6938 0.00974 0.00298 -0.0842 0.3999 0.6335
2.000 0.7111 0.00944 0.00309 -0.0819 0.3892 0.7852
2.250 0.7978 0.00948 0.00334 -0.0944 0.3718 1.0000
2.500 0.8203 0.00966 0.00343 -0.0933 0.3627 1.0000
2.750 0.8430 0.00983 0.00354 -0.0923 0.3554 1.0000
3.000 0.8656 0.01002 0.00365 -0.0912 0.3480 1.0000
3.250 0.8881 0.01021 0.00378 -0.0902 0.3418 1.0000
3.500 0.9112 0.01039 0.00391 -0.0892 0.3357 1.0000
3.750 0.9337 0.01059 0.00406 -0.0882 0.3303 1.0000
4.000 0.9566 0.01078 0.00421 -0.0873 0.3262 1.0000
4.250 0.9801 0.01095 0.00435 -0.0864 0.3220 1.0000
4.500 1.0031 0.01114 0.00451 -0.0855 0.3178 1.0000
4.750 1.0253 0.01137 0.00470 -0.0845 0.3135 1.0000
5.000 1.0482 0.01156 0.00487 -0.0836 0.3102 1.0000
5.250 1.0716 0.01173 0.00505 -0.0828 0.3070 1.0000
5.500 1.0945 0.01193 0.00523 -0.0819 0.3033 1.0000
5.750 1.1165 0.01215 0.00544 -0.0809 0.2996 1.0000
6.000 1.1377 0.01241 0.00567 -0.0798 0.2959 1.0000
6.250 1.1605 0.01259 0.00586 -0.0790 0.2924 1.0000
6.500 1.1827 0.01280 0.00607 -0.0780 0.2877 1.0000
6.750 1.2032 0.01306 0.00631 -0.0768 0.2828 1.0000
7.000 1.2230 0.01334 0.00656 -0.0755 0.2790 1.0000
7.250 1.2444 0.01352 0.00678 -0.0744 0.2767 1.0000
7.500 1.2643 0.01373 0.00701 -0.0731 0.2733 1.0000
7.750 1.2829 0.01398 0.00727 -0.0715 0.2693 1.0000
8.000 1.2994 0.01431 0.00757 -0.0696 0.2647 1.0000
8.250 1.3186 0.01456 0.00785 -0.0683 0.2605 1.0000
8.500 1.3372 0.01483 0.00815 -0.0669 0.2559 1.0000
8.750 1.3534 0.01520 0.00850 -0.0651 0.2502 1.0000
9.000 1.3709 0.01553 0.00885 -0.0636 0.2448 1.0000
9.250 1.3879 0.01590 0.00922 -0.0621 0.2386 1.0000
9.500 1.4025 0.01637 0.00968 -0.0603 0.2319 1.0000
9.750 1.4179 0.01683 0.01014 -0.0587 0.2235 1.0000
10.000 1.4314 0.01739 0.01069 -0.0569 0.2164 1.0000
10.250 1.4442 0.01801 0.01130 -0.0551 0.2073 1.0000
10.500 1.4553 0.01874 0.01202 -0.0532 0.1974 1.0000
10.750 1.4632 0.01969 0.01292 -0.0511 0.1852 1.0000
11.000 1.4674 0.02091 0.01407 -0.0488 0.1705 1.0000
11.250 1.4699 0.02234 0.01543 -0.0465 0.1562 1.0000
11.500 1.4717 0.02391 0.01696 -0.0445 0.1434 1.0000
11.750 1.4734 0.02561 0.01864 -0.0427 0.1321 1.0000
12.000 1.4718 0.02766 0.02065 -0.0409 0.1196 1.0000
12.250 1.4692 0.02993 0.02289 -0.0394 0.1077 1.0000
12.500 1.4649 0.03246 0.02539 -0.0381 0.0953 1.0000
12.750 1.4386 0.03718 0.02996 -0.0364 0.0657 1.0000
13.000 1.4141 0.04209 0.03482 -0.0354 0.0442 1.0000
13.250 1.3925 0.04705 0.03979 -0.0349 0.0242 1.0000
13.500 1.3825 0.05097 0.04375 -0.0348 0.0190 1.0000
13.750 1.3780 0.05436 0.04723 -0.0349 0.0170 1.0000
14.000 1.3764 0.05747 0.05042 -0.0350 0.0163 1.0000
14.250 1.3725 0.06090 0.05394 -0.0352 0.0154 1.0000
14.500 1.3680 0.06448 0.05761 -0.0355 0.0148 1.0000
14.750 1.3634 0.06811 0.06134 -0.0359 0.0143 1.0000
15.000 1.3599 0.07165 0.06498 -0.0363 0.0140 1.0000
15.250 1.3557 0.07536 0.06878 -0.0368 0.0137 1.0000
15.500 1.3512 0.07918 0.07270 -0.0375 0.0134 1.0000
15.750 1.3452 0.08326 0.07688 -0.0382 0.0130 1.0000
16.000 1.3394 0.08735 0.08107 -0.0391 0.0127 1.0000
16.250 1.3324 0.09172 0.08554 -0.0401 0.0125 1.0000
16.500 1.3239 0.09640 0.09032 -0.0412 0.0121 1.0000
16.750 1.3163 0.10099 0.09501 -0.0425 0.0120 1.0000
17.000 1.3072 0.10588 0.10000 -0.0439 0.0118 1.0000
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