GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 100,000 Max Cl/Cd: 46.62 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe375-il-100000.txt Download as CSV file: xf-goe375-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3557 0.09783 0.09302 -0.0112 1.0000 0.0329
-7.750 -0.3533 0.09537 0.09063 -0.0125 1.0000 0.0337
-7.500 -0.3523 0.09322 0.08856 -0.0138 1.0000 0.0342
-7.250 -0.3478 0.09100 0.08639 -0.0169 1.0000 0.0346
-7.000 -0.3383 0.08977 0.08517 -0.0248 1.0000 0.0351
-6.750 -0.3276 0.08678 0.08218 -0.0282 1.0000 0.0353
-6.500 -0.3255 0.08116 0.07669 -0.0227 1.0000 0.0361
-6.250 -0.3190 0.07766 0.07324 -0.0218 1.0000 0.0372
-6.000 -0.3102 0.07456 0.07016 -0.0226 1.0000 0.0383
-5.750 -0.2999 0.07155 0.06717 -0.0240 1.0000 0.0393
-5.500 -0.2880 0.06861 0.06424 -0.0255 1.0000 0.0406
-5.250 -0.2726 0.06584 0.06143 -0.0278 1.0000 0.0423
-5.000 -0.2448 0.06489 0.06016 -0.0327 1.0000 0.0438
-4.750 -0.2350 0.06126 0.05653 -0.0326 1.0000 0.0444
-4.500 -0.2336 0.05725 0.05267 -0.0302 1.0000 0.0455
-4.250 -0.2271 0.05451 0.04997 -0.0289 1.0000 0.0471
-4.000 -0.2162 0.05213 0.04754 -0.0283 1.0000 0.0493
-3.750 -0.1996 0.05011 0.04537 -0.0285 1.0000 0.0526
-3.500 -0.1771 0.04838 0.04331 -0.0294 1.0000 0.0558
-3.250 -0.1710 0.04501 0.04008 -0.0281 1.0000 0.0586
-2.750 -0.1372 0.04070 0.03550 -0.0279 1.0000 0.0717
-2.500 -0.1138 0.04030 0.03465 -0.0279 1.0000 0.0827
-2.250 -0.0788 0.03658 0.03089 -0.0317 0.9942 0.0981
-2.000 -0.0348 0.03346 0.02767 -0.0369 0.9847 0.1278
-1.500 0.0385 0.02781 0.02227 -0.0444 0.9602 0.3037
-1.250 0.0740 0.02474 0.01954 -0.0456 0.9463 0.4007
-1.000 0.1237 0.02233 0.01704 -0.0488 0.9322 0.4484
-0.750 0.2057 0.02100 0.01461 -0.0575 0.9191 0.3278
-0.500 0.2729 0.02044 0.01299 -0.0606 0.9049 0.1950
-0.250 0.3222 0.01925 0.01133 -0.0617 0.8882 0.1477
0.000 0.3651 0.01816 0.00999 -0.0625 0.8691 0.1305
0.250 0.3990 0.01743 0.00910 -0.0618 0.8439 0.1204
0.500 0.4302 0.01699 0.00843 -0.0606 0.8162 0.1112
0.750 0.4569 0.01632 0.00772 -0.0591 0.7856 0.1075
1.000 0.4816 0.01583 0.00716 -0.0573 0.7527 0.1048
1.250 0.5058 0.01551 0.00669 -0.0555 0.7169 0.1071
1.500 0.5303 0.01531 0.00625 -0.0539 0.6794 0.1074
1.750 0.5551 0.01524 0.00591 -0.0524 0.6418 0.1073
2.000 0.5797 0.01533 0.00567 -0.0511 0.6054 0.1084
2.250 0.6042 0.01555 0.00557 -0.0498 0.5705 0.1112
2.500 0.6286 0.01581 0.00560 -0.0487 0.5377 0.1197
2.750 0.6699 0.01445 0.00582 -0.0515 0.5023 1.0000
3.000 0.6936 0.01495 0.00603 -0.0504 0.4745 1.0000
3.250 0.7174 0.01546 0.00626 -0.0493 0.4498 1.0000
3.500 0.7413 0.01596 0.00651 -0.0484 0.4279 1.0000
3.750 0.7655 0.01646 0.00681 -0.0476 0.4083 1.0000
4.000 0.7896 0.01696 0.00719 -0.0468 0.3901 1.0000
4.250 0.8139 0.01746 0.00756 -0.0461 0.3740 1.0000
4.500 0.8382 0.01798 0.00796 -0.0454 0.3592 1.0000
4.750 0.8626 0.01853 0.00841 -0.0447 0.3459 1.0000
5.000 0.8872 0.01912 0.00894 -0.0441 0.3339 1.0000
5.500 0.9360 0.02033 0.01005 -0.0429 0.3108 1.0000
5.750 0.9599 0.02099 0.01073 -0.0423 0.2997 1.0000
6.000 0.9843 0.02171 0.01142 -0.0417 0.2900 1.0000
6.250 1.0088 0.02245 0.01217 -0.0412 0.2810 1.0000
6.500 1.0325 0.02333 0.01319 -0.0406 0.2726 1.0000
6.750 1.0575 0.02420 0.01398 -0.0402 0.2657 1.0000
7.000 1.0802 0.02520 0.01523 -0.0395 0.2583 1.0000
7.250 1.1047 0.02608 0.01613 -0.0390 0.2518 1.0000
7.500 1.1268 0.02721 0.01751 -0.0383 0.2454 1.0000
7.750 1.1498 0.02827 0.01873 -0.0377 0.2400 1.0000
8.000 1.1748 0.02955 0.01998 -0.0375 0.2359 1.0000
8.250 1.1931 0.03103 0.02198 -0.0363 0.2312 1.0000
8.500 1.2145 0.03222 0.02338 -0.0356 0.2261 1.0000
8.750 1.2368 0.03311 0.02432 -0.0350 0.2196 1.0000
9.000 1.2572 0.03326 0.02459 -0.0340 0.2099 1.0000
9.250 1.2756 0.03369 0.02525 -0.0329 0.2006 1.0000
9.500 1.3012 0.03368 0.02507 -0.0325 0.1928 1.0000
9.750 1.3151 0.03449 0.02638 -0.0309 0.1855 1.0000
10.000 1.3348 0.03382 0.02573 -0.0297 0.1747 1.0000
10.250 1.3530 0.03292 0.02487 -0.0283 0.1635 1.0000
10.500 1.3640 0.03207 0.02432 -0.0260 0.1494 1.0000
10.750 1.3726 0.03146 0.02406 -0.0235 0.1288 1.0000
11.000 1.3795 0.03204 0.02471 -0.0213 0.0882 1.0000
11.250 1.3758 0.03449 0.02687 -0.0184 0.0595 1.0000
11.500 1.3663 0.03704 0.02938 -0.0150 0.0526 1.0000
11.750 1.3577 0.03960 0.03209 -0.0123 0.0489 1.0000
12.000 1.3470 0.04256 0.03519 -0.0104 0.0468 1.0000
12.250 1.3330 0.04621 0.03897 -0.0097 0.0453 1.0000
12.500 1.3180 0.05048 0.04339 -0.0101 0.0444 1.0000
12.750 1.3030 0.05530 0.04836 -0.0114 0.0438 1.0000
13.000 1.2903 0.06034 0.05356 -0.0132 0.0433 1.0000
13.250 1.2774 0.06583 0.05923 -0.0156 0.0427 1.0000
13.500 1.2652 0.07135 0.06492 -0.0179 0.0422 1.0000
13.750 1.2541 0.07682 0.07054 -0.0201 0.0417 1.0000
14.000 1.2434 0.08225 0.07611 -0.0223 0.0410 1.0000
14.250 1.2341 0.08748 0.08148 -0.0243 0.0403 1.0000
14.500 1.2249 0.09279 0.08692 -0.0264 0.0395 1.0000
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Polar data table (+)
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