GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 500,000 Max Cl/Cd: 106.71 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe546-il-500000.txt Download as CSV file: xf-goe546-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 546 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3900 0.10902 0.10657 -0.0357 1.0000 0.0261
-10.500 -0.3885 0.10570 0.10328 -0.0365 1.0000 0.0268
-10.250 -0.3911 0.10152 0.09911 -0.0384 1.0000 0.0283
-10.000 -0.3329 0.08465 0.08250 -0.0437 1.0000 0.0297
-9.750 -0.3350 0.08246 0.08034 -0.0421 1.0000 0.0300
-9.500 -0.3396 0.08127 0.07919 -0.0395 0.9998 0.0303
-9.250 -0.3275 0.07759 0.07550 -0.0419 0.9984 0.0310
-9.000 -0.3193 0.07298 0.07090 -0.0452 0.9965 0.0317
-8.750 -0.3130 0.06782 0.06574 -0.0493 0.9943 0.0332
-8.500 -0.3972 0.03694 0.03466 -0.0811 0.9808 0.0300
-8.250 -0.3882 0.03163 0.02919 -0.0864 0.9751 0.0303
-8.000 -0.4319 0.03595 0.03282 -0.0913 0.9732 0.0264
-7.750 -0.4233 0.02772 0.02380 -0.0937 0.9652 0.0267
-7.500 -0.3984 0.02372 0.01923 -0.0954 0.9619 0.0279
-7.250 -0.3657 0.02227 0.01735 -0.0970 0.9600 0.0292
-7.000 -0.3404 0.01951 0.01436 -0.0980 0.9564 0.0307
-6.750 -0.3113 0.01879 0.01359 -0.0987 0.9522 0.0318
-6.500 -0.2797 0.01775 0.01240 -0.0998 0.9493 0.0330
-6.250 -0.2466 0.01682 0.01129 -0.1011 0.9468 0.0345
-6.000 -0.2131 0.01643 0.01072 -0.1022 0.9439 0.0357
-5.750 -0.1882 0.01451 0.00865 -0.1021 0.9380 0.0370
-5.500 -0.1572 0.01378 0.00789 -0.1029 0.9340 0.0383
-5.250 -0.1238 0.01327 0.00733 -0.1042 0.9309 0.0400
-5.000 -0.0973 0.01276 0.00677 -0.1039 0.9246 0.0413
-4.750 -0.0680 0.01224 0.00617 -0.1041 0.9193 0.0424
-4.500 -0.0370 0.01188 0.00572 -0.1047 0.9147 0.0435
-4.250 -0.0132 0.01111 0.00492 -0.1039 0.9078 0.0452
-4.000 0.0146 0.01063 0.00441 -0.1039 0.9021 0.0469
-3.750 0.0408 0.01033 0.00408 -0.1035 0.8953 0.0487
-3.500 0.0676 0.01006 0.00376 -0.1031 0.8878 0.0507
-3.250 0.0942 0.00986 0.00352 -0.1027 0.8800 0.0529
-3.000 0.1199 0.00949 0.00310 -0.1021 0.8723 0.0563
-2.750 0.1465 0.00926 0.00285 -0.1018 0.8657 0.0608
-2.500 0.1726 0.00905 0.00261 -0.1012 0.8582 0.0670
-2.250 0.1994 0.00875 0.00236 -0.1009 0.8517 0.0859
-2.000 0.2217 0.00797 0.00215 -0.1001 0.8435 0.2453
-1.750 0.2469 0.00756 0.00208 -0.0997 0.8365 0.3619
-1.500 0.2717 0.00734 0.00206 -0.0990 0.8277 0.4303
-1.250 0.2981 0.00721 0.00202 -0.0986 0.8199 0.4803
-1.000 0.3235 0.00707 0.00199 -0.0979 0.8106 0.5235
-0.750 0.3493 0.00695 0.00196 -0.0973 0.8016 0.5648
-0.500 0.3741 0.00677 0.00194 -0.0966 0.7921 0.6265
-0.250 0.3956 0.00643 0.00196 -0.0950 0.7804 0.7274
0.000 0.4165 0.00603 0.00201 -0.0928 0.7684 0.8887
0.250 0.4809 0.00596 0.00195 -0.1005 0.7562 0.9765
0.500 0.5264 0.00601 0.00191 -0.1043 0.7421 1.0000
0.750 0.5495 0.00607 0.00189 -0.1032 0.7270 1.0000
1.000 0.5728 0.00616 0.00188 -0.1021 0.7124 1.0000
1.250 0.5962 0.00626 0.00189 -0.1011 0.6975 1.0000
1.500 0.6196 0.00638 0.00192 -0.1000 0.6827 1.0000
1.750 0.6429 0.00651 0.00196 -0.0989 0.6673 1.0000
2.000 0.6659 0.00666 0.00202 -0.0978 0.6494 1.0000
2.250 0.6887 0.00682 0.00209 -0.0966 0.6304 1.0000
2.500 0.7123 0.00698 0.00218 -0.0956 0.6151 1.0000
2.750 0.7361 0.00713 0.00227 -0.0947 0.6006 1.0000
3.000 0.7602 0.00727 0.00237 -0.0939 0.5864 1.0000
3.250 0.7843 0.00742 0.00248 -0.0930 0.5721 1.0000
3.500 0.8078 0.00758 0.00258 -0.0920 0.5529 1.0000
3.750 0.8302 0.00778 0.00269 -0.0908 0.5274 1.0000
4.000 0.8525 0.00800 0.00282 -0.0897 0.5009 1.0000
4.250 0.8745 0.00827 0.00298 -0.0885 0.4722 1.0000
4.500 0.8951 0.00862 0.00317 -0.0870 0.4393 1.0000
4.750 0.9154 0.00901 0.00341 -0.0856 0.4013 1.0000
5.000 0.9346 0.00950 0.00369 -0.0840 0.3549 1.0000
5.250 0.9520 0.01013 0.00402 -0.0821 0.2953 1.0000
5.500 0.9678 0.01091 0.00447 -0.0801 0.2356 1.0000
5.750 0.9841 0.01168 0.00495 -0.0781 0.1809 1.0000
6.000 0.9939 0.01293 0.00567 -0.0752 0.0905 1.0000
6.250 1.0102 0.01370 0.00624 -0.0733 0.0565 1.0000
6.500 1.0301 0.01419 0.00668 -0.0719 0.0492 1.0000
6.750 1.0499 0.01468 0.00715 -0.0704 0.0457 1.0000
7.000 1.0684 0.01523 0.00774 -0.0688 0.0429 1.0000
7.250 1.0879 0.01568 0.00824 -0.0673 0.0418 1.0000
7.500 1.1064 0.01618 0.00879 -0.0657 0.0406 1.0000
7.750 1.1233 0.01671 0.00937 -0.0639 0.0394 1.0000
8.000 1.1377 0.01730 0.01001 -0.0616 0.0380 1.0000
8.250 1.1499 0.01799 0.01073 -0.0589 0.0368 1.0000
8.500 1.1585 0.01891 0.01169 -0.0558 0.0357 1.0000
8.750 1.1660 0.01995 0.01281 -0.0526 0.0347 1.0000
9.000 1.1812 0.02053 0.01345 -0.0507 0.0341 1.0000
9.250 1.1950 0.02122 0.01421 -0.0486 0.0332 1.0000
9.500 1.2073 0.02205 0.01510 -0.0465 0.0324 1.0000
9.750 1.2192 0.02292 0.01603 -0.0444 0.0315 1.0000
10.000 1.2310 0.02382 0.01697 -0.0423 0.0305 1.0000
10.250 1.2414 0.02488 0.01805 -0.0403 0.0295 1.0000
10.500 1.2482 0.02669 0.01990 -0.0380 0.0283 1.0000
10.750 1.2607 0.02800 0.02129 -0.0363 0.0276 1.0000
11.000 1.2737 0.02885 0.02224 -0.0347 0.0270 1.0000
11.250 1.2859 0.02984 0.02332 -0.0331 0.0261 1.0000
11.500 1.2978 0.03094 0.02449 -0.0316 0.0253 1.0000
11.750 1.3085 0.03205 0.02567 -0.0301 0.0244 1.0000
12.000 1.3186 0.03324 0.02690 -0.0287 0.0237 1.0000
12.250 1.3295 0.03476 0.02843 -0.0274 0.0229 1.0000
12.500 1.3430 0.03700 0.03076 -0.0263 0.0221 1.0000
12.750 1.3490 0.03834 0.03226 -0.0247 0.0216 1.0000
13.000 1.3549 0.03981 0.03387 -0.0232 0.0210 1.0000
13.250 1.3602 0.04135 0.03552 -0.0219 0.0203 1.0000
13.500 1.3660 0.04306 0.03735 -0.0208 0.0198 1.0000
13.750 1.3700 0.04481 0.03919 -0.0198 0.0193 1.0000
14.000 1.3738 0.04674 0.04120 -0.0189 0.0189 1.0000
14.250 1.3777 0.04869 0.04321 -0.0182 0.0185 1.0000
14.500 1.3817 0.05098 0.04554 -0.0175 0.0180 1.0000
14.750 1.3797 0.05442 0.04916 -0.0167 0.0176 1.0000
15.000 1.3756 0.05740 0.05233 -0.0164 0.0174 1.0000
15.250 1.3705 0.06067 0.05580 -0.0164 0.0171 1.0000
15.500 1.3641 0.06438 0.05970 -0.0166 0.0168 1.0000
15.750 1.3567 0.06834 0.06384 -0.0172 0.0165 1.0000
16.000 1.3480 0.07271 0.06840 -0.0182 0.0162 1.0000
16.250 1.3390 0.07730 0.07316 -0.0195 0.0160 1.0000
16.500 1.3288 0.08224 0.07826 -0.0212 0.0158 1.0000
16.750 1.3204 0.08709 0.08324 -0.0232 0.0155 1.0000
17.000 1.3099 0.09251 0.08881 -0.0256 0.0154 1.0000
17.250 1.3008 0.09788 0.09431 -0.0283 0.0152 1.0000
17.500 1.2847 0.10480 0.10140 -0.0319 0.0151 1.0000
17.750 1.2706 0.11164 0.10839 -0.0357 0.0150 1.0000
18.000 1.2438 0.12153 0.11850 -0.0415 0.0150 1.0000
18.250 1.2317 0.12853 0.12563 -0.0459 0.0149 1.0000
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Polar data table (+)
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