GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 200,000 Max Cl/Cd: 62.91 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe375-il-200000.txt Download as CSV file: xf-goe375-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3494 0.09222 0.08883 -0.0115 1.0000 0.0203
-7.500 -0.3468 0.08967 0.08632 -0.0122 1.0000 0.0205
-7.250 -0.3456 0.08719 0.08391 -0.0126 1.0000 0.0207
-7.000 -0.3412 0.08435 0.08110 -0.0143 1.0000 0.0212
-6.750 -0.3340 0.08155 0.07835 -0.0166 1.0000 0.0216
-6.500 -0.3249 0.07875 0.07557 -0.0191 1.0000 0.0218
-6.250 -0.3104 0.07612 0.07293 -0.0237 1.0000 0.0221
-6.000 -0.2928 0.07345 0.07020 -0.0284 1.0000 0.0222
-5.750 -0.2763 0.07072 0.06740 -0.0311 1.0000 0.0223
-5.250 -0.2616 0.06343 0.06015 -0.0301 1.0000 0.0226
-5.000 -0.2630 0.06031 0.05713 -0.0273 1.0000 0.0230
-4.750 -0.2609 0.05799 0.05482 -0.0255 1.0000 0.0234
-4.500 -0.2571 0.05581 0.05263 -0.0242 1.0000 0.0240
-4.250 -0.2248 0.05211 0.04882 -0.0287 0.9963 0.0251
-4.000 -0.1813 0.04815 0.04468 -0.0346 0.9907 0.0265
-3.750 -0.1218 0.04593 0.04198 -0.0409 0.9848 0.0279
-3.500 -0.0827 0.04207 0.03784 -0.0446 0.9779 0.0283
-3.250 -0.0528 0.03726 0.03310 -0.0483 0.9722 0.0292
-3.000 -0.0171 0.03420 0.02991 -0.0513 0.9647 0.0306
-2.750 0.0394 0.03415 0.02911 -0.0542 0.9575 0.0352
-2.500 0.0716 0.02868 0.02376 -0.0575 0.9477 0.0366
-2.250 0.1096 0.02613 0.02104 -0.0600 0.9368 0.0397
-2.000 0.1511 0.02480 0.01919 -0.0612 0.9263 0.0450
-1.750 0.1814 0.02221 0.01660 -0.0625 0.9127 0.0493
-1.500 0.2133 0.02063 0.01477 -0.0630 0.8976 0.0594
-1.250 0.2416 0.01926 0.01317 -0.0629 0.8794 0.0731
-1.000 0.2677 0.01810 0.01181 -0.0626 0.8599 0.0999
-0.750 -0.0860 0.01702 0.01387 -0.0395 1.0000 0.0349
-0.500 0.3152 0.01581 0.00933 -0.0614 0.8186 0.1724
-0.250 0.3390 0.01481 0.00828 -0.0604 0.7957 0.2070
0.000 0.3669 0.01433 0.00750 -0.0589 0.7702 0.1965
0.250 0.2227 0.02956 0.02636 -0.0648 0.8178 0.1708
0.500 0.4246 0.01342 0.00597 -0.0556 0.7109 0.1195
0.750 0.4504 0.01311 0.00541 -0.0541 0.6721 0.1050
1.000 0.4753 0.01294 0.00495 -0.0526 0.6298 0.0915
1.250 0.5001 0.01315 0.00482 -0.0512 0.5893 0.0821
1.500 0.5234 0.01276 0.00431 -0.0499 0.5549 0.0778
1.750 0.5471 0.01269 0.00407 -0.0488 0.5238 0.0742
2.000 0.5708 0.01268 0.00392 -0.0478 0.4948 0.0746
2.250 0.5948 0.01275 0.00382 -0.0469 0.4677 0.0749
2.500 0.6191 0.01288 0.00376 -0.0461 0.4415 0.0735
2.750 0.6438 0.01303 0.00376 -0.0453 0.4165 0.0728
3.000 0.6684 0.01324 0.00380 -0.0446 0.3940 0.0731
3.250 0.6933 0.01344 0.00387 -0.0439 0.3725 0.0749
3.500 0.7181 0.01368 0.00398 -0.0432 0.3542 0.0791
3.750 0.7634 0.01230 0.00430 -0.0474 0.3339 1.0000
4.000 0.7879 0.01264 0.00453 -0.0467 0.3199 1.0000
4.250 0.8122 0.01301 0.00475 -0.0460 0.3072 1.0000
4.500 0.8367 0.01336 0.00499 -0.0454 0.2951 1.0000
4.750 0.8613 0.01369 0.00527 -0.0448 0.2837 1.0000
5.000 0.8856 0.01409 0.00562 -0.0441 0.2735 1.0000
5.250 0.9096 0.01456 0.00595 -0.0435 0.2645 1.0000
5.500 0.9342 0.01490 0.00632 -0.0429 0.2550 1.0000
5.750 0.9583 0.01539 0.00675 -0.0423 0.2467 1.0000
6.000 0.9825 0.01582 0.00719 -0.0417 0.2385 1.0000
6.250 1.0067 0.01634 0.00771 -0.0411 0.2307 1.0000
6.500 1.0308 0.01683 0.00818 -0.0406 0.2236 1.0000
6.750 1.0548 0.01737 0.00876 -0.0400 0.2165 1.0000
7.000 1.0787 0.01785 0.00928 -0.0394 0.2101 1.0000
7.250 1.1028 0.01853 0.00999 -0.0389 0.2047 1.0000
7.500 1.1266 0.01902 0.01059 -0.0382 0.1991 1.0000
7.750 1.1502 0.01961 0.01111 -0.0377 0.1932 1.0000
8.000 1.1728 0.01989 0.01160 -0.0369 0.1863 1.0000
8.250 1.1952 0.02024 0.01192 -0.0363 0.1792 1.0000
8.500 1.2172 0.02044 0.01234 -0.0354 0.1719 1.0000
8.750 1.2391 0.02077 0.01267 -0.0347 0.1655 1.0000
9.000 1.2609 0.02096 0.01307 -0.0338 0.1580 1.0000
9.250 1.2818 0.02127 0.01342 -0.0330 0.1508 1.0000
9.500 1.3035 0.02125 0.01362 -0.0322 0.1401 1.0000
9.750 1.3243 0.02140 0.01384 -0.0313 0.1243 1.0000
10.000 1.3458 0.02181 0.01428 -0.0305 0.0925 1.0000
10.500 1.3585 0.02603 0.01807 -0.0258 0.0289 1.0000
10.750 1.3664 0.02771 0.01993 -0.0234 0.0259 1.0000
11.000 1.3741 0.02918 0.02162 -0.0212 0.0242 1.0000
11.250 1.3760 0.03078 0.02341 -0.0183 0.0229 1.0000
11.500 1.3732 0.03255 0.02536 -0.0151 0.0222 1.0000
11.750 1.3674 0.03466 0.02764 -0.0123 0.0216 1.0000
12.000 1.3602 0.03713 0.03027 -0.0104 0.0213 1.0000
12.250 1.3497 0.04029 0.03357 -0.0093 0.0209 1.0000
12.500 1.3397 0.04383 0.03725 -0.0091 0.0206 1.0000
12.750 1.3296 0.04779 0.04138 -0.0096 0.0205 1.0000
13.000 1.3201 0.05208 0.04579 -0.0107 0.0203 1.0000
13.250 1.3095 0.05674 0.05057 -0.0121 0.0201 1.0000
13.500 1.3022 0.06108 0.05502 -0.0133 0.0200 1.0000
13.750 1.2946 0.06538 0.05942 -0.0141 0.0198 1.0000
14.000 1.2896 0.06923 0.06335 -0.0142 0.0195 1.0000
14.250 1.2862 0.07319 0.06742 -0.0151 0.0194 1.0000
14.500 1.2815 0.07754 0.07192 -0.0167 0.0192 1.0000
14.750 1.2761 0.08205 0.07658 -0.0183 0.0191 1.0000
15.000 1.2687 0.08710 0.08179 -0.0206 0.0188 1.0000
15.250 1.2605 0.09246 0.08731 -0.0232 0.0186 1.0000
15.500 1.2537 0.09757 0.09258 -0.0253 0.0185 1.0000
15.750 1.2442 0.10344 0.09861 -0.0283 0.0183 1.0000
16.000 1.2357 0.10920 0.10452 -0.0311 0.0184 1.0000
16.250 1.2254 0.11552 0.11100 -0.0345 0.0184 1.0000
16.500 1.2139 0.12232 0.11796 -0.0383 0.0184 1.0000
16.750 1.2023 0.12935 0.12514 -0.0423 0.0185 1.0000
17.000 1.1893 0.13694 0.13288 -0.0468 0.0186 1.0000
17.250 1.1757 0.14489 0.14098 -0.0517 0.0188 1.0000
17.500 1.1617 0.15323 0.14945 -0.0569 0.0189 1.0000
17.750 1.1463 0.16226 0.15860 -0.0625 0.0191 1.0000
18.000 1.1300 0.17187 0.16832 -0.0684 0.0194 1.0000
18.250 1.1197 0.18038 0.17694 -0.0738 0.0197 1.0000
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