GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 500,000 Max Cl/Cd: 106.93 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe167-il-500000.txt Download as CSV file: xf-goe167-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3673 0.09650 0.09442 -0.0178 1.0000 0.0219
-8.250 -0.3673 0.09260 0.09056 -0.0228 1.0000 0.0221
-8.000 -0.3652 0.08862 0.08662 -0.0271 1.0000 0.0222
-7.750 -0.3557 0.08383 0.08184 -0.0336 1.0000 0.0223
-7.500 -0.3439 0.07733 0.07533 -0.0391 0.9805 0.0226
-7.250 -0.3280 0.07419 0.07216 -0.0403 0.9554 0.0230
-7.000 -0.3172 0.07128 0.06918 -0.0413 0.9171 0.0233
-6.750 -0.3076 0.06833 0.06605 -0.0425 0.8641 0.0238
-6.500 -0.2937 0.06499 0.06248 -0.0451 0.8201 0.0244
-6.250 -0.2754 0.06118 0.05846 -0.0490 0.7864 0.0254
-6.000 -0.2365 0.05497 0.05183 -0.0586 0.7599 0.0279
-5.750 -0.2120 0.05052 0.04704 -0.0617 0.7329 0.0281
-5.500 -0.1994 0.04460 0.04095 -0.0639 0.7083 0.0289
-5.250 -0.1785 0.04247 0.03864 -0.0647 0.6825 0.0294
-5.000 -0.1553 0.04031 0.03629 -0.0658 0.6606 0.0302
-4.750 -0.1297 0.03787 0.03362 -0.0672 0.6435 0.0315
-4.500 -0.0929 0.03629 0.03156 -0.0680 0.6299 0.0354
-4.250 -0.0684 0.03020 0.02503 -0.0701 0.6204 0.0366
-4.000 -0.0432 0.02845 0.02317 -0.0709 0.6102 0.0374
-3.750 -0.0165 0.02702 0.02162 -0.0715 0.6013 0.0385
-3.500 0.0112 0.02565 0.02005 -0.0721 0.5937 0.0403
-3.250 0.0434 0.02615 0.02024 -0.0717 0.5863 0.0452
-3.000 0.0711 0.02200 0.01570 -0.0731 0.5807 0.0475
-2.750 0.0990 0.02091 0.01455 -0.0736 0.5751 0.0491
-2.500 0.1277 0.02002 0.01354 -0.0740 0.5698 0.0517
-2.250 0.1579 0.02104 0.01430 -0.0737 0.5649 0.0572
-2.000 0.1864 0.01804 0.01112 -0.0747 0.5609 0.0610
-1.750 0.2151 0.01745 0.01048 -0.0751 0.5564 0.0651
-1.500 0.2444 0.01676 0.00959 -0.0755 0.5523 0.0741
-1.250 0.2772 0.01446 0.00682 -0.0746 0.5486 0.0444
-1.000 0.3065 0.01349 0.00577 -0.0748 0.5443 0.0434
-0.750 0.3355 0.01288 0.00510 -0.0749 0.5397 0.0429
-0.500 0.3642 0.01251 0.00465 -0.0750 0.5355 0.0433
-0.250 0.3931 0.01221 0.00431 -0.0752 0.5321 0.0439
0.000 0.4222 0.01184 0.00394 -0.0755 0.5288 0.0440
0.250 0.4512 0.01158 0.00366 -0.0757 0.5253 0.0444
0.500 0.4802 0.01142 0.00346 -0.0759 0.5216 0.0451
0.750 0.5091 0.01129 0.00328 -0.0762 0.5180 0.0461
1.000 0.5384 0.01109 0.00309 -0.0765 0.5146 0.0485
1.250 0.5676 0.01101 0.00301 -0.0768 0.5112 0.0519
1.500 0.5966 0.01098 0.00297 -0.0770 0.5082 0.0572
1.750 0.6189 0.00903 0.00317 -0.0766 0.5048 0.8599
2.000 0.6478 0.00879 0.00304 -0.0766 0.5002 1.0000
2.250 0.6767 0.00884 0.00305 -0.0768 0.4953 1.0000
2.500 0.7055 0.00894 0.00309 -0.0770 0.4917 1.0000
2.750 0.7340 0.00911 0.00319 -0.0772 0.4881 1.0000
3.000 0.7629 0.00914 0.00325 -0.0775 0.4843 1.0000
3.250 0.7917 0.00920 0.00330 -0.0777 0.4793 1.0000
3.500 0.8200 0.00931 0.00335 -0.0779 0.4736 1.0000
3.750 0.8487 0.00934 0.00342 -0.0782 0.4679 1.0000
4.000 0.8772 0.00940 0.00347 -0.0784 0.4619 1.0000
4.250 0.9056 0.00951 0.00357 -0.0786 0.4568 1.0000
4.500 0.9342 0.00955 0.00366 -0.0788 0.4504 1.0000
4.750 0.9623 0.00967 0.00374 -0.0790 0.4442 1.0000
5.000 0.9908 0.00973 0.00386 -0.0792 0.4375 1.0000
5.250 1.0188 0.00984 0.00396 -0.0794 0.4287 1.0000
5.500 1.0468 0.00991 0.00404 -0.0795 0.4126 1.0000
5.750 1.0746 0.01005 0.00416 -0.0797 0.3926 1.0000
6.000 1.1015 0.01031 0.00433 -0.0797 0.3632 1.0000
6.500 1.1461 0.01229 0.00553 -0.0791 0.2249 1.0000
6.750 1.1704 0.01294 0.00605 -0.0789 0.1979 1.0000
7.000 1.1920 0.01391 0.00670 -0.0785 0.1352 1.0000
7.250 1.2098 0.01530 0.00774 -0.0776 0.0749 1.0000
7.500 1.2338 0.01582 0.00827 -0.0772 0.0673 1.0000
7.750 1.2566 0.01643 0.00887 -0.0768 0.0596 1.0000
8.000 1.2810 0.01682 0.00932 -0.0765 0.0542 1.0000
8.250 1.3038 0.01737 0.00986 -0.0760 0.0451 1.0000
8.500 1.3240 0.01816 0.01048 -0.0752 0.0247 1.0000
8.750 1.3427 0.01904 0.01134 -0.0741 0.0198 1.0000
9.000 1.3612 0.01989 0.01226 -0.0730 0.0178 1.0000
9.250 1.3794 0.02069 0.01316 -0.0718 0.0170 1.0000
9.500 1.3951 0.02162 0.01419 -0.0703 0.0163 1.0000
9.750 1.4080 0.02267 0.01534 -0.0684 0.0156 1.0000
10.000 1.4163 0.02389 0.01665 -0.0660 0.0150 1.0000
10.250 1.4168 0.02534 0.01820 -0.0624 0.0146 1.0000
10.500 1.4120 0.02734 0.02032 -0.0589 0.0141 1.0000
10.750 1.4060 0.02986 0.02297 -0.0563 0.0138 1.0000
11.000 1.4120 0.03167 0.02488 -0.0551 0.0135 1.0000
11.250 1.4151 0.03393 0.02726 -0.0542 0.0132 1.0000
11.500 1.4167 0.03652 0.02995 -0.0536 0.0130 1.0000
11.750 1.4174 0.03930 0.03283 -0.0531 0.0127 1.0000
12.000 1.4178 0.04217 0.03581 -0.0527 0.0125 1.0000
12.250 1.4178 0.04509 0.03882 -0.0522 0.0123 1.0000
12.500 1.4177 0.04802 0.04183 -0.0518 0.0121 1.0000
12.750 1.4177 0.05092 0.04483 -0.0514 0.0119 1.0000
13.000 1.4176 0.05379 0.04780 -0.0509 0.0117 1.0000
13.250 1.4177 0.05663 0.05071 -0.0503 0.0115 1.0000
13.500 1.4179 0.05942 0.05357 -0.0497 0.0114 1.0000
13.750 1.4182 0.06214 0.05637 -0.0490 0.0112 1.0000
14.000 1.4193 0.06475 0.05904 -0.0482 0.0110 1.0000
14.250 1.4216 0.06721 0.06155 -0.0471 0.0109 1.0000
14.500 1.4254 0.06930 0.06371 -0.0452 0.0107 1.0000
14.750 1.4303 0.07148 0.06601 -0.0421 0.0104 1.0000
15.000 1.4254 0.07536 0.07006 -0.0432 0.0103 1.0000
15.250 1.4210 0.07928 0.07416 -0.0443 0.0102 1.0000
15.500 1.4170 0.08322 0.07826 -0.0451 0.0101 1.0000
15.750 1.4122 0.08737 0.08258 -0.0460 0.0100 1.0000
16.000 1.4066 0.09169 0.08706 -0.0469 0.0099 1.0000
16.250 1.3996 0.09628 0.09182 -0.0479 0.0099 1.0000
16.500 1.3912 0.10122 0.09694 -0.0493 0.0098 1.0000
16.750 1.3815 0.10650 0.10239 -0.0510 0.0098 1.0000
17.000 1.3708 0.11214 0.10821 -0.0531 0.0098 1.0000
17.250 1.3590 0.11810 0.11434 -0.0556 0.0099 1.0000
17.500 1.3462 0.12447 0.12089 -0.0585 0.0099 1.0000
17.750 1.3325 0.13124 0.12783 -0.0619 0.0099 1.0000
18.000 1.3184 0.13841 0.13517 -0.0658 0.0099 1.0000
18.250 1.3035 0.14602 0.14295 -0.0702 0.0100 1.0000
18.500 1.2882 0.15404 0.15113 -0.0750 0.0101 1.0000
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Polar data table (+)
Polar graphs
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