GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 500,000 Max Cl/Cd: 74.14 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe512-il-500000-n5.txt Download as CSV file: xf-goe512-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6548 0.04705 0.04397 -0.1066 0.9758 0.0106
-12.750 -0.7029 0.03739 0.03389 -0.1085 0.9663 0.0105
-12.500 -0.6957 0.03262 0.02886 -0.1106 0.9632 0.0107
-12.250 -0.6791 0.02991 0.02594 -0.1116 0.9615 0.0109
-12.000 -0.6752 0.02833 0.02421 -0.1087 0.9558 0.0110
-11.750 -0.6612 0.02671 0.02243 -0.1076 0.9518 0.0112
-11.500 -0.6398 0.02534 0.02090 -0.1076 0.9496 0.0114
-11.250 -0.6165 0.02405 0.01945 -0.1078 0.9480 0.0118
-11.000 -0.5902 0.02292 0.01816 -0.1083 0.9468 0.0122
-10.750 -0.5860 0.02213 0.01725 -0.1040 0.9387 0.0124
-10.500 -0.5630 0.02116 0.01613 -0.1035 0.9358 0.0128
-10.250 -0.5379 0.02012 0.01497 -0.1035 0.9337 0.0132
-10.000 -0.5079 0.01919 0.01394 -0.1044 0.9320 0.0137
-9.750 -0.4993 0.01869 0.01337 -0.1006 0.9242 0.0141
-9.500 -0.4741 0.01801 0.01259 -0.1002 0.9200 0.0146
-9.250 -0.4435 0.01728 0.01175 -0.1009 0.9172 0.0152
-9.000 -0.4235 0.01675 0.01111 -0.0993 0.9118 0.0158
-8.750 -0.4043 0.01618 0.01046 -0.0975 0.9050 0.0164
-8.500 -0.3706 0.01557 0.00979 -0.0989 0.9015 0.0172
-8.250 -0.3510 0.01517 0.00934 -0.0971 0.8933 0.0180
-8.000 -0.3193 0.01471 0.00878 -0.0978 0.8881 0.0193
-7.750 -0.2890 0.01424 0.00826 -0.0984 0.8820 0.0204
-7.500 -0.2600 0.01386 0.00782 -0.0985 0.8740 0.0217
-7.250 -0.2276 0.01347 0.00734 -0.0994 0.8658 0.0232
-7.000 -0.1939 0.01307 0.00687 -0.1006 0.8554 0.0247
-6.750 -0.1638 0.01279 0.00651 -0.1009 0.8432 0.0265
-6.500 -0.1333 0.01255 0.00615 -0.1013 0.8298 0.0283
-6.250 -0.1052 0.01229 0.00583 -0.1013 0.8166 0.0302
-6.000 -0.0782 0.01210 0.00555 -0.1010 0.8039 0.0320
-5.750 -0.0528 0.01195 0.00529 -0.1003 0.7903 0.0337
-5.500 -0.0293 0.01175 0.00504 -0.0992 0.7754 0.0357
-5.250 -0.0062 0.01164 0.00484 -0.0981 0.7584 0.0375
-5.000 0.0157 0.01155 0.00463 -0.0966 0.7399 0.0393
-4.750 0.0367 0.01144 0.00442 -0.0950 0.7208 0.0413
-4.500 0.0573 0.01135 0.00426 -0.0933 0.7019 0.0434
-4.250 0.0778 0.01130 0.00410 -0.0916 0.6845 0.0456
-4.000 0.0985 0.01127 0.00396 -0.0899 0.6690 0.0476
-3.750 0.1184 0.01117 0.00379 -0.0880 0.6534 0.0502
-3.500 0.1385 0.01113 0.00367 -0.0863 0.6386 0.0528
-3.250 0.1587 0.01111 0.00355 -0.0845 0.6234 0.0555
-3.000 0.1794 0.01106 0.00343 -0.0828 0.6094 0.0586
-2.750 0.2001 0.01099 0.00332 -0.0812 0.5962 0.0625
-2.500 0.2211 0.01096 0.00322 -0.0796 0.5858 0.0665
-2.250 0.2425 0.01090 0.00312 -0.0781 0.5745 0.0714
-2.000 0.2628 0.01084 0.00302 -0.0764 0.5615 0.0781
-1.750 0.2814 0.01079 0.00294 -0.0743 0.5456 0.0877
-1.500 0.2964 0.01070 0.00287 -0.0715 0.5256 0.1126
-1.250 0.3108 0.01063 0.00282 -0.0686 0.5060 0.1492
-1.000 0.3251 0.01062 0.00282 -0.0658 0.4855 0.1801
-0.750 0.3420 0.01070 0.00291 -0.0634 0.4679 0.2175
-0.250 0.3819 0.01094 0.00303 -0.0599 0.4454 0.2441
0.000 0.4020 0.01106 0.00309 -0.0582 0.4371 0.2501
0.250 0.4240 0.01116 0.00314 -0.0569 0.4299 0.2567
0.500 0.4449 0.01126 0.00320 -0.0554 0.4231 0.2605
0.750 0.4666 0.01136 0.00327 -0.0541 0.4176 0.2658
1.000 0.4888 0.01147 0.00334 -0.0529 0.4118 0.2710
1.250 0.5095 0.01157 0.00340 -0.0514 0.4059 0.2746
1.500 0.5308 0.01166 0.00348 -0.0500 0.4002 0.2781
1.750 0.5529 0.01176 0.00356 -0.0488 0.3945 0.2830
2.000 0.5737 0.01188 0.00363 -0.0473 0.3886 0.2852
2.250 0.5952 0.01197 0.00369 -0.0460 0.3839 0.2869
2.500 0.6166 0.01202 0.00375 -0.0447 0.3785 0.2884
2.750 0.6372 0.01212 0.00384 -0.0433 0.3729 0.2905
3.000 0.6578 0.01223 0.00394 -0.0419 0.3677 0.2934
3.250 0.6796 0.01233 0.00403 -0.0407 0.3617 0.2974
3.500 0.7000 0.01246 0.00413 -0.0393 0.3555 0.2989
3.750 0.7208 0.01258 0.00424 -0.0379 0.3493 0.3003
4.000 0.7410 0.01269 0.00434 -0.0365 0.3423 0.3018
4.250 0.7602 0.01283 0.00447 -0.0349 0.3353 0.3037
4.500 0.7804 0.01296 0.00460 -0.0335 0.3271 0.3054
4.750 0.7994 0.01313 0.00475 -0.0319 0.3189 0.3075
5.000 0.8185 0.01331 0.00491 -0.0303 0.3092 0.3093
5.250 0.8369 0.01352 0.00509 -0.0286 0.2998 0.3119
5.500 0.8545 0.01377 0.00529 -0.0269 0.2903 0.3141
6.000 0.8899 0.01425 0.00574 -0.0235 0.2731 0.3196
6.250 0.9073 0.01450 0.00599 -0.0217 0.2653 0.3234
6.500 0.9242 0.01479 0.00626 -0.0199 0.2595 0.3277
6.750 0.9426 0.01501 0.00652 -0.0184 0.2552 0.3350
7.250 0.9690 0.01500 0.00711 -0.0136 0.2468 0.6257
7.750 1.1774 0.01588 0.00887 -0.0486 0.2320 0.9959
8.000 1.2088 0.01636 0.00934 -0.0501 0.2285 0.9989
8.250 1.2349 0.01677 0.00976 -0.0505 0.2255 1.0000
8.500 1.2505 0.01706 0.01008 -0.0486 0.2229 1.0000
8.750 1.2652 0.01740 0.01045 -0.0466 0.2205 1.0000
9.000 1.2795 0.01777 0.01085 -0.0445 0.2184 1.0000
9.250 1.2935 0.01817 0.01127 -0.0425 0.2164 1.0000
9.500 1.3069 0.01862 0.01174 -0.0404 0.2145 1.0000
9.750 1.3193 0.01912 0.01225 -0.0382 0.2118 1.0000
10.000 1.3332 0.01958 0.01274 -0.0364 0.2093 1.0000
10.250 1.3489 0.01997 0.01319 -0.0348 0.2062 1.0000
10.500 1.3632 0.02044 0.01370 -0.0331 0.2029 1.0000
10.750 1.3761 0.02100 0.01428 -0.0312 0.1999 1.0000
11.000 1.3879 0.02163 0.01493 -0.0293 0.1968 1.0000
11.250 1.4002 0.02226 0.01560 -0.0275 0.1937 1.0000
11.500 1.4154 0.02276 0.01616 -0.0261 0.1899 1.0000
11.750 1.4273 0.02344 0.01687 -0.0244 0.1844 1.0000
12.000 1.4368 0.02431 0.01773 -0.0225 0.1801 1.0000
12.250 1.4505 0.02495 0.01843 -0.0212 0.1740 1.0000
12.500 1.4595 0.02591 0.01939 -0.0194 0.1671 1.0000
12.750 1.4700 0.02680 0.02032 -0.0179 0.1604 1.0000
13.000 1.4754 0.02807 0.02156 -0.0160 0.1486 1.0000
13.250 1.4754 0.02979 0.02320 -0.0139 0.1337 1.0000
13.500 1.4743 0.03168 0.02506 -0.0118 0.1222 1.0000
13.750 1.4683 0.03406 0.02739 -0.0097 0.1094 1.0000
14.000 1.4680 0.03610 0.02945 -0.0081 0.1036 1.0000
14.250 1.4597 0.03894 0.03227 -0.0064 0.0903 1.0000
14.500 1.4433 0.04271 0.03597 -0.0048 0.0713 1.0000
14.750 1.4077 0.04870 0.04184 -0.0031 0.0449 1.0000
15.000 1.3898 0.05320 0.04635 -0.0024 0.0317 1.0000
15.250 1.3702 0.05811 0.05130 -0.0021 0.0214 1.0000
15.500 1.3548 0.06275 0.05602 -0.0022 0.0173 1.0000
15.750 1.3452 0.06681 0.06018 -0.0024 0.0157 1.0000
16.000 1.3373 0.07081 0.06428 -0.0028 0.0148 1.0000
16.250 1.3303 0.07476 0.06834 -0.0032 0.0141 1.0000
16.500 1.3221 0.07891 0.07259 -0.0039 0.0135 1.0000
16.750 1.3114 0.08348 0.07727 -0.0047 0.0128 1.0000
17.000 1.3013 0.08805 0.08195 -0.0055 0.0125 1.0000
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