GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.16 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe512-il-1000000-n5.txt Download as CSV file: xf-goe512-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4596 0.09880 0.09667 -0.0774 0.9891 0.0084
-14.750 -0.5267 0.08270 0.08042 -0.0875 0.9878 0.0084
-14.500 -0.8059 0.03675 0.03373 -0.1232 0.9754 0.0076
-14.250 -0.8099 0.03048 0.02716 -0.1259 0.9736 0.0076
-14.000 -0.8088 0.02781 0.02431 -0.1239 0.9688 0.0076
-13.750 -0.7955 0.02609 0.02245 -0.1232 0.9663 0.0077
-13.500 -0.7773 0.02474 0.02097 -0.1229 0.9645 0.0078
-13.250 -0.7582 0.02323 0.01932 -0.1228 0.9630 0.0079
-13.000 -0.7363 0.02177 0.01773 -0.1231 0.9617 0.0081
-12.750 -0.7112 0.02058 0.01643 -0.1237 0.9608 0.0083
-12.500 -0.7069 0.01995 0.01572 -0.1195 0.9552 0.0085
-12.250 -0.6857 0.01912 0.01480 -0.1187 0.9527 0.0087
-12.000 -0.6599 0.01835 0.01395 -0.1189 0.9507 0.0089
-11.750 -0.6329 0.01759 0.01310 -0.1192 0.9490 0.0091
-11.500 -0.6031 0.01690 0.01233 -0.1200 0.9474 0.0093
-11.250 -0.5844 0.01639 0.01174 -0.1184 0.9430 0.0096
-11.000 -0.5661 0.01589 0.01117 -0.1165 0.9373 0.0097
-10.750 -0.5371 0.01529 0.01048 -0.1170 0.9337 0.0100
-10.500 -0.5048 0.01478 0.00989 -0.1181 0.9309 0.0102
-10.250 -0.4940 0.01431 0.00936 -0.1146 0.9233 0.0105
-10.000 -0.4684 0.01380 0.00879 -0.1142 0.9189 0.0109
-9.750 -0.4396 0.01334 0.00826 -0.1145 0.9148 0.0114
-9.500 -0.4199 0.01301 0.00790 -0.1127 0.9068 0.0119
-9.250 -0.3906 0.01260 0.00741 -0.1130 0.8993 0.0124
-9.000 -0.3668 0.01230 0.00703 -0.1121 0.8905 0.0128
-8.750 -0.3399 0.01192 0.00659 -0.1119 0.8823 0.0136
-8.500 -0.3139 0.01160 0.00621 -0.1114 0.8716 0.0143
-8.250 -0.2881 0.01133 0.00585 -0.1109 0.8572 0.0151
-8.000 -0.2635 0.01112 0.00554 -0.1101 0.8407 0.0159
-7.750 -0.2404 0.01091 0.00524 -0.1089 0.8261 0.0168
-7.500 -0.2178 0.01073 0.00499 -0.1077 0.8120 0.0180
-7.250 -0.1958 0.01059 0.00477 -0.1063 0.7968 0.0192
-7.000 -0.1747 0.01045 0.00456 -0.1047 0.7799 0.0208
-6.750 -0.1541 0.01036 0.00438 -0.1030 0.7613 0.0223
-6.500 -0.1332 0.01027 0.00420 -0.1013 0.7442 0.0235
-6.250 -0.1144 0.01020 0.00404 -0.0992 0.7216 0.0250
-6.000 -0.0953 0.01015 0.00390 -0.0972 0.6984 0.0264
-5.750 -0.0763 0.01013 0.00376 -0.0951 0.6765 0.0276
-5.500 -0.0556 0.01008 0.00362 -0.0934 0.6603 0.0291
-5.250 -0.0341 0.01000 0.00349 -0.0919 0.6469 0.0305
-5.000 -0.0127 0.00995 0.00338 -0.0904 0.6336 0.0322
-4.750 0.0089 0.00991 0.00327 -0.0889 0.6218 0.0334
-4.500 0.0318 0.00982 0.00314 -0.0877 0.6119 0.0353
-4.250 0.0533 0.00977 0.00305 -0.0862 0.5985 0.0375
-4.000 0.0749 0.00974 0.00296 -0.0847 0.5862 0.0392
-3.750 0.0977 0.00969 0.00285 -0.0835 0.5750 0.0406
-3.500 0.1194 0.00963 0.00276 -0.0820 0.5621 0.0434
-3.250 0.1412 0.00959 0.00268 -0.0806 0.5504 0.0460
-3.000 0.1620 0.00959 0.00260 -0.0790 0.5337 0.0477
-2.750 0.1814 0.00957 0.00252 -0.0770 0.5144 0.0508
-2.500 0.1986 0.00962 0.00247 -0.0746 0.4889 0.0538
-2.250 0.2169 0.00968 0.00242 -0.0725 0.4682 0.0566
-2.000 0.2359 0.00971 0.00238 -0.0705 0.4511 0.0604
-1.500 0.2768 0.00973 0.00231 -0.0672 0.4280 0.0685
-1.250 0.2972 0.00972 0.00228 -0.0655 0.4194 0.0765
-1.000 0.3186 0.00968 0.00224 -0.0640 0.4130 0.0862
-0.750 0.3375 0.00953 0.00221 -0.0621 0.4076 0.1277
-0.500 0.3577 0.00949 0.00221 -0.0604 0.4027 0.1523
-0.250 0.3788 0.00943 0.00221 -0.0589 0.3985 0.1737
0.000 0.3994 0.00939 0.00228 -0.0574 0.3935 0.2151
0.250 0.4212 0.00947 0.00234 -0.0560 0.3876 0.2300
0.500 0.4440 0.00952 0.00240 -0.0549 0.3826 0.2391
0.750 0.4670 0.00959 0.00244 -0.0538 0.3781 0.2447
1.000 0.4890 0.00966 0.00250 -0.0525 0.3730 0.2485
1.250 0.5113 0.00974 0.00256 -0.0513 0.3685 0.2531
1.500 0.5344 0.00982 0.00262 -0.0503 0.3638 0.2579
1.750 0.5567 0.00989 0.00267 -0.0491 0.3585 0.2603
2.000 0.5784 0.00999 0.00275 -0.0478 0.3530 0.2643
2.250 0.6012 0.01006 0.00282 -0.0468 0.3479 0.2673
2.500 0.6231 0.01016 0.00289 -0.0455 0.3411 0.2701
2.750 0.6445 0.01027 0.00297 -0.0442 0.3347 0.2711
3.000 0.6661 0.01038 0.00304 -0.0430 0.3269 0.2721
3.250 0.6867 0.01050 0.00314 -0.0415 0.3187 0.2743
3.500 0.7073 0.01063 0.00323 -0.0401 0.3090 0.2757
3.750 0.7275 0.01079 0.00336 -0.0387 0.2980 0.2782
4.000 0.7470 0.01097 0.00349 -0.0371 0.2875 0.2804
4.250 0.7660 0.01117 0.00364 -0.0354 0.2763 0.2824
4.500 0.7858 0.01135 0.00378 -0.0339 0.2679 0.2835
4.750 0.8047 0.01156 0.00395 -0.0323 0.2588 0.2847
5.000 0.8249 0.01173 0.00410 -0.0309 0.2524 0.2855
5.250 0.8439 0.01194 0.00427 -0.0294 0.2453 0.2871
5.500 0.8634 0.01211 0.00444 -0.0279 0.2407 0.2888
5.750 0.8832 0.01227 0.00461 -0.0265 0.2367 0.2904
6.000 0.9027 0.01246 0.00479 -0.0251 0.2327 0.2923
6.250 0.9215 0.01268 0.00500 -0.0235 0.2279 0.2942
6.500 0.9416 0.01285 0.00519 -0.0222 0.2257 0.2962
6.750 0.9613 0.01303 0.00539 -0.0209 0.2230 0.2982
7.000 0.9808 0.01322 0.00559 -0.0196 0.2207 0.3000
7.250 0.9996 0.01344 0.00582 -0.0181 0.2175 0.3023
7.500 1.0185 0.01365 0.00605 -0.0167 0.2153 0.3056
7.750 1.0369 0.01389 0.00631 -0.0153 0.2130 0.3095
8.000 1.0548 0.01414 0.00658 -0.0137 0.2107 0.3131
8.250 1.0739 0.01434 0.00683 -0.0125 0.2097 0.3206
8.500 1.0936 0.01453 0.00708 -0.0113 0.2080 0.3282
8.750 1.1118 0.01472 0.00736 -0.0099 0.2065 0.3610
9.250 1.3083 0.01484 0.00889 -0.0429 0.1961 0.9931
9.500 1.3319 0.01521 0.00928 -0.0428 0.1934 0.9968
9.750 1.3640 0.01555 0.00965 -0.0445 0.1910 0.9986
10.000 1.3930 0.01597 0.01007 -0.0456 0.1854 0.9996
10.250 1.4132 0.01644 0.01052 -0.0451 0.1806 1.0000
10.500 1.4283 0.01679 0.01090 -0.0432 0.1774 1.0000
10.750 1.4421 0.01721 0.01132 -0.0413 0.1720 1.0000
11.000 1.4538 0.01777 0.01184 -0.0391 0.1648 1.0000
11.250 1.4656 0.01832 0.01238 -0.0370 0.1570 1.0000
11.500 1.4714 0.01921 0.01318 -0.0341 0.1422 1.0000
11.750 1.4699 0.02052 0.01437 -0.0305 0.1227 1.0000
12.000 1.4763 0.02147 0.01530 -0.0280 0.1153 1.0000
12.250 1.4802 0.02261 0.01642 -0.0253 0.1063 1.0000
12.500 1.4845 0.02379 0.01758 -0.0229 0.0974 1.0000
12.750 1.4846 0.02529 0.01904 -0.0201 0.0859 1.0000
13.000 1.4628 0.02836 0.02193 -0.0156 0.0573 1.0000
13.250 1.4332 0.03238 0.02583 -0.0113 0.0269 1.0000
13.500 1.4248 0.03507 0.02852 -0.0091 0.0169 1.0000
13.750 1.4260 0.03709 0.03059 -0.0078 0.0144 1.0000
14.000 1.4274 0.03917 0.03273 -0.0067 0.0128 1.0000
14.250 1.4291 0.04130 0.03493 -0.0057 0.0117 1.0000
14.500 1.4322 0.04338 0.03707 -0.0050 0.0114 1.0000
14.750 1.4327 0.04578 0.03954 -0.0043 0.0104 1.0000
15.000 1.4328 0.04829 0.04212 -0.0038 0.0100 1.0000
15.250 1.4315 0.05100 0.04489 -0.0034 0.0095 1.0000
15.500 1.4297 0.05383 0.04781 -0.0031 0.0089 1.0000
15.750 1.4271 0.05682 0.05088 -0.0029 0.0087 1.0000
16.000 1.4244 0.05992 0.05405 -0.0028 0.0085 1.0000
16.250 1.4199 0.06326 0.05748 -0.0029 0.0082 1.0000
16.500 1.4142 0.06684 0.06114 -0.0032 0.0079 1.0000
16.750 1.4064 0.07078 0.06517 -0.0035 0.0076 1.0000
17.000 1.3983 0.07485 0.06933 -0.0041 0.0074 1.0000
17.250 1.3899 0.07899 0.07356 -0.0047 0.0072 1.0000
17.500 1.3805 0.08333 0.07799 -0.0055 0.0070 1.0000
17.750 1.3719 0.08763 0.08238 -0.0063 0.0068 1.0000
18.000 1.3614 0.09222 0.08706 -0.0073 0.0069 1.0000
18.250 1.3529 0.09657 0.09150 -0.0083 0.0066 1.0000
18.500 1.3421 0.10129 0.09632 -0.0094 0.0063 1.0000
18.750 1.3310 0.10612 0.10124 -0.0107 0.0062 1.0000
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