GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.36 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe650-il-1000000-n5.txt Download as CSV file: xf-goe650-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8270 0.08575 0.08279 -0.0698 1.0000 0.0222
-16.250 -0.8425 0.08047 0.07745 -0.0723 1.0000 0.0223
-16.000 -0.8591 0.07519 0.07211 -0.0748 1.0000 0.0225
-15.750 -0.8795 0.06966 0.06651 -0.0774 1.0000 0.0226
-15.500 -0.9115 0.06308 0.05985 -0.0804 1.0000 0.0226
-15.250 -0.9441 0.05645 0.05313 -0.0838 0.9998 0.0226
-15.000 -0.9703 0.04769 0.04423 -0.0927 0.9978 0.0226
-14.500 -1.0124 0.02952 0.02566 -0.1155 0.9848 0.0227
-14.250 -0.9889 0.02487 0.02080 -0.1247 0.9825 0.0230
-14.000 -0.9733 0.02337 0.01920 -0.1254 0.9769 0.0233
-13.750 -0.9488 0.02221 0.01795 -0.1270 0.9741 0.0236
-13.500 -0.9220 0.02121 0.01687 -0.1285 0.9720 0.0239
-13.250 -0.8940 0.02028 0.01585 -0.1301 0.9704 0.0241
-13.000 -0.8766 0.01923 0.01473 -0.1297 0.9640 0.0245
-12.750 -0.8496 0.01830 0.01375 -0.1309 0.9610 0.0250
-12.250 -0.7874 0.01684 0.01217 -0.1341 0.9570 0.0259
-12.000 -0.7629 0.01627 0.01155 -0.1340 0.9514 0.0263
-11.750 -0.7328 0.01571 0.01093 -0.1351 0.9473 0.0267
-11.500 -0.7005 0.01519 0.01034 -0.1365 0.9438 0.0272
-11.250 -0.6728 0.01472 0.00980 -0.1369 0.9379 0.0275
-11.000 -0.6436 0.01428 0.00930 -0.1375 0.9319 0.0278
-10.750 -0.6135 0.01388 0.00883 -0.1382 0.9266 0.0281
-10.500 -0.5887 0.01336 0.00824 -0.1380 0.9192 0.0287
-10.250 -0.5616 0.01291 0.00772 -0.1382 0.9125 0.0292
-10.000 -0.5360 0.01253 0.00729 -0.1379 0.9057 0.0297
-9.750 -0.5101 0.01218 0.00689 -0.1376 0.8985 0.0302
-9.500 -0.4839 0.01188 0.00652 -0.1374 0.8920 0.0308
-9.250 -0.4585 0.01159 0.00618 -0.1369 0.8848 0.0313
-9.000 -0.4322 0.01134 0.00586 -0.1366 0.8776 0.0320
-8.750 -0.4065 0.01110 0.00557 -0.1361 0.8705 0.0324
-8.500 -0.3809 0.01084 0.00525 -0.1357 0.8624 0.0331
-8.250 -0.3555 0.01056 0.00493 -0.1351 0.8543 0.0342
-8.000 -0.3301 0.01033 0.00464 -0.1346 0.8450 0.0353
-7.750 -0.3043 0.01012 0.00438 -0.1341 0.8366 0.0365
-7.500 -0.2785 0.00992 0.00413 -0.1336 0.8279 0.0381
-7.250 -0.2529 0.00969 0.00387 -0.1330 0.8203 0.0409
-7.000 -0.2274 0.00943 0.00360 -0.1325 0.8123 0.0463
-6.750 -0.2026 0.00911 0.00331 -0.1319 0.8046 0.0597
-6.500 -0.1769 0.00889 0.00311 -0.1314 0.7966 0.0711
-6.250 -0.1509 0.00873 0.00294 -0.1308 0.7891 0.0786
-6.000 -0.1242 0.00859 0.00280 -0.1305 0.7820 0.0839
-5.750 -0.0976 0.00849 0.00267 -0.1300 0.7754 0.0885
-5.500 -0.0707 0.00838 0.00255 -0.1296 0.7696 0.0930
-5.250 -0.0438 0.00827 0.00243 -0.1293 0.7627 0.0977
-4.750 0.0100 0.00810 0.00223 -0.1285 0.7507 0.1065
-4.500 0.0374 0.00802 0.00214 -0.1282 0.7456 0.1111
-4.250 0.0647 0.00796 0.00206 -0.1279 0.7409 0.1146
-4.000 0.0918 0.00788 0.00198 -0.1275 0.7367 0.1195
-3.750 0.1195 0.00780 0.00190 -0.1273 0.7325 0.1238
-3.500 0.1468 0.00775 0.00184 -0.1269 0.7265 0.1277
-3.000 0.2006 0.00764 0.00172 -0.1261 0.7125 0.1383
-2.750 0.2274 0.00762 0.00167 -0.1257 0.7051 0.1425
-2.500 0.2543 0.00756 0.00162 -0.1252 0.6985 0.1496
-2.250 0.2813 0.00752 0.00157 -0.1248 0.6906 0.1552
-2.000 0.3078 0.00752 0.00153 -0.1243 0.6816 0.1592
-1.750 0.3341 0.00747 0.00150 -0.1238 0.6707 0.1667
-1.500 0.3605 0.00747 0.00147 -0.1232 0.6594 0.1730
-1.250 0.3862 0.00746 0.00144 -0.1226 0.6470 0.1809
-1.000 0.4119 0.00747 0.00142 -0.1219 0.6326 0.1890
-0.750 0.4369 0.00748 0.00141 -0.1211 0.6143 0.1992
-0.500 0.4613 0.00754 0.00142 -0.1202 0.5915 0.2111
0.000 0.5078 0.00775 0.00150 -0.1180 0.5427 0.2392
0.250 0.5322 0.00783 0.00155 -0.1171 0.5262 0.2541
0.500 0.5566 0.00791 0.00162 -0.1163 0.5109 0.2696
0.750 0.5815 0.00798 0.00168 -0.1155 0.4972 0.2825
1.250 0.6314 0.00814 0.00181 -0.1140 0.4712 0.3095
1.500 0.6558 0.00824 0.00189 -0.1131 0.4560 0.3214
1.750 0.6802 0.00836 0.00197 -0.1122 0.4401 0.3312
2.000 0.7035 0.00851 0.00207 -0.1112 0.4174 0.3432
2.250 0.7251 0.00874 0.00220 -0.1098 0.3878 0.3541
2.500 0.7460 0.00901 0.00235 -0.1083 0.3578 0.3640
2.750 0.7673 0.00926 0.00251 -0.1069 0.3327 0.3741
3.000 0.7891 0.00949 0.00266 -0.1056 0.3124 0.3845
3.250 0.8116 0.00966 0.00280 -0.1044 0.2984 0.3948
3.750 0.8571 0.00998 0.00308 -0.1021 0.2754 0.4154
4.000 0.8794 0.01013 0.00323 -0.1009 0.2647 0.4327
4.250 0.9010 0.01028 0.00339 -0.0996 0.2551 0.4500
4.500 0.9224 0.01041 0.00353 -0.0982 0.2465 0.4644
5.000 0.9638 0.01070 0.00383 -0.0951 0.2307 0.4928
5.250 0.9835 0.01089 0.00401 -0.0934 0.2211 0.5081
5.500 1.0037 0.01107 0.00420 -0.0918 0.2118 0.5264
5.750 1.0229 0.01127 0.00442 -0.0900 0.2028 0.5484
6.000 1.0430 0.01144 0.00463 -0.0885 0.1957 0.5724
6.250 1.0619 0.01163 0.00487 -0.0867 0.1882 0.6055
6.500 1.0805 0.01178 0.00511 -0.0849 0.1805 0.6530
6.750 1.0927 0.01174 0.00539 -0.0817 0.1733 0.7896
7.250 1.1843 0.01229 0.00614 -0.0901 0.1515 1.0000
7.500 1.2030 0.01263 0.00643 -0.0884 0.1438 1.0000
7.750 1.2229 0.01291 0.00670 -0.0870 0.1380 1.0000
8.000 1.2413 0.01327 0.00702 -0.0853 0.1314 1.0000
8.250 1.2610 0.01358 0.00733 -0.0839 0.1266 1.0000
8.500 1.2792 0.01397 0.00768 -0.0822 0.1199 1.0000
8.750 1.2981 0.01433 0.00802 -0.0807 0.1154 1.0000
9.000 1.3165 0.01472 0.00840 -0.0792 0.1101 1.0000
9.250 1.3340 0.01517 0.00882 -0.0776 0.1044 1.0000
9.500 1.3528 0.01554 0.00920 -0.0762 0.1013 1.0000
9.750 1.3702 0.01602 0.00965 -0.0746 0.0965 1.0000
10.000 1.3876 0.01649 0.01012 -0.0731 0.0925 1.0000
10.250 1.4048 0.01698 0.01061 -0.0716 0.0875 1.0000
10.500 1.4204 0.01757 0.01117 -0.0699 0.0824 1.0000
10.750 1.4371 0.01811 0.01171 -0.0685 0.0778 1.0000
11.000 1.4513 0.01881 0.01238 -0.0667 0.0709 1.0000
11.250 1.4618 0.01975 0.01323 -0.0646 0.0579 1.0000
11.500 1.4624 0.02135 0.01468 -0.0614 0.0367 1.0000
11.750 1.4732 0.02234 0.01566 -0.0595 0.0325 1.0000
12.000 1.4864 0.02319 0.01653 -0.0580 0.0307 1.0000
12.250 1.4983 0.02414 0.01750 -0.0564 0.0291 1.0000
12.500 1.5109 0.02505 0.01845 -0.0549 0.0281 1.0000
12.750 1.5241 0.02595 0.01938 -0.0535 0.0275 1.0000
13.000 1.5363 0.02693 0.02041 -0.0521 0.0268 1.0000
13.250 1.5472 0.02801 0.02153 -0.0507 0.0259 1.0000
13.500 1.5572 0.02920 0.02275 -0.0493 0.0252 1.0000
13.750 1.5665 0.03045 0.02405 -0.0479 0.0245 1.0000
14.000 1.5763 0.03171 0.02535 -0.0466 0.0239 1.0000
14.250 1.5864 0.03296 0.02665 -0.0454 0.0236 1.0000
14.500 1.5961 0.03427 0.02802 -0.0443 0.0230 1.0000
14.750 1.6047 0.03569 0.02950 -0.0432 0.0226 1.0000
15.000 1.6121 0.03727 0.03113 -0.0421 0.0221 1.0000
15.250 1.6188 0.03894 0.03284 -0.0410 0.0216 1.0000
15.500 1.6243 0.04075 0.03471 -0.0400 0.0211 1.0000
15.750 1.6287 0.04273 0.03675 -0.0391 0.0208 1.0000
16.000 1.6325 0.04481 0.03889 -0.0383 0.0203 1.0000
16.250 1.6383 0.04673 0.04089 -0.0376 0.0200 1.0000
16.500 1.6427 0.04883 0.04305 -0.0370 0.0196 1.0000
16.750 1.6455 0.05115 0.04545 -0.0364 0.0193 1.0000
17.000 1.6475 0.05363 0.04800 -0.0360 0.0189 1.0000
17.250 1.6483 0.05631 0.05075 -0.0357 0.0186 1.0000
17.500 1.6482 0.05915 0.05365 -0.0355 0.0181 1.0000
17.750 1.6463 0.06226 0.05684 -0.0355 0.0178 1.0000
18.000 1.6425 0.06569 0.06036 -0.0356 0.0175 1.0000
18.250 1.6377 0.06934 0.06408 -0.0360 0.0171 1.0000
18.500 1.6330 0.07305 0.06789 -0.0364 0.0170 1.0000
18.750 1.6287 0.07673 0.07166 -0.0369 0.0167 1.0000
19.000 1.6218 0.08080 0.07583 -0.0376 0.0164 1.0000
19.250 1.6135 0.08515 0.08028 -0.0385 0.0162 1.0000
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