GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 200,000 Max Cl/Cd: 73.69 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe758-il-200000.txt Download as CSV file: xf-goe758-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2610 0.11254 0.10900 -0.0446 1.0000 0.0565
-10.500 -0.2745 0.10948 0.10602 -0.0481 1.0000 0.0592
-10.250 -0.2981 0.10637 0.10302 -0.0524 1.0000 0.0598
-10.000 -0.2852 0.10256 0.09924 -0.0491 1.0000 0.0607
-9.750 -0.2777 0.10080 0.09753 -0.0464 1.0000 0.0615
-9.500 -0.2834 0.09981 0.09662 -0.0431 1.0000 0.0624
-9.250 -0.2714 0.09696 0.09379 -0.0450 0.9969 0.0645
-8.750 -0.2535 0.08465 0.08150 -0.0639 0.9774 0.0716
-8.500 -0.2227 0.08229 0.07912 -0.0642 0.9722 0.0737
-8.250 -0.2013 0.07854 0.07537 -0.0689 0.9623 0.0770
-8.000 -0.2095 0.06465 0.06134 -0.0982 0.9409 0.0833
-7.750 -0.1751 0.06442 0.06118 -0.0934 0.9327 0.0849
-7.500 -0.1458 0.06187 0.05858 -0.0958 0.9210 0.0879
-7.250 -0.1698 0.05257 0.04862 -0.1106 0.8919 0.0966
-7.000 -0.1438 0.04986 0.04605 -0.1098 0.8779 0.0983
-6.750 -0.1252 0.04832 0.04449 -0.1088 0.8614 0.1006
-6.250 -0.1135 0.04227 0.03788 -0.1093 0.8269 0.1134
-6.000 -0.0954 0.04055 0.03612 -0.1085 0.8128 0.1164
-5.750 -0.0879 0.03805 0.03311 -0.1083 0.7986 0.1278
-5.500 -0.0788 0.02760 0.02128 -0.1064 0.7885 0.0730
-5.250 -0.0568 0.02470 0.01788 -0.1052 0.7793 0.0649
-5.000 -0.0355 0.02250 0.01513 -0.1038 0.7682 0.0622
-4.750 -0.0103 0.02131 0.01355 -0.1029 0.7595 0.0608
-4.500 0.0156 0.02064 0.01264 -0.1022 0.7504 0.0600
-4.250 0.0413 0.01959 0.01141 -0.1016 0.7423 0.0597
-4.000 0.0672 0.01861 0.01028 -0.1011 0.7343 0.0596
-3.750 0.0934 0.01784 0.00938 -0.1006 0.7271 0.0598
-3.500 0.1191 0.01702 0.00850 -0.1001 0.7196 0.0601
-3.250 0.1444 0.01622 0.00768 -0.0996 0.7133 0.0618
-3.000 0.1695 0.01575 0.00723 -0.0990 0.7060 0.0636
-2.750 0.1956 0.01535 0.00675 -0.0985 0.7001 0.0650
-2.500 0.2205 0.01502 0.00640 -0.0979 0.6931 0.0665
-2.250 0.2464 0.01474 0.00604 -0.0974 0.6868 0.0686
-2.000 0.2723 0.01451 0.00573 -0.0969 0.6809 0.0716
-1.750 0.2979 0.01429 0.00551 -0.0964 0.6742 0.0778
-1.500 0.3247 0.01407 0.00528 -0.0960 0.6686 0.0965
-1.250 0.3444 0.01306 0.00520 -0.0951 0.6624 0.3286
-1.000 0.3654 0.01256 0.00530 -0.0938 0.6563 0.5062
-0.750 0.3891 0.01242 0.00538 -0.0926 0.6512 0.6124
-0.500 0.4107 0.01225 0.00549 -0.0911 0.6448 0.6893
-0.250 0.4344 0.01204 0.00553 -0.0897 0.6392 0.7769
0.000 0.5146 0.01185 0.00554 -0.0997 0.6326 0.9666
0.250 0.5649 0.01196 0.00552 -0.1046 0.6256 1.0000
0.500 0.5895 0.01213 0.00552 -0.1040 0.6203 1.0000
0.750 0.6125 0.01232 0.00564 -0.1032 0.6145 1.0000
1.000 0.6360 0.01248 0.00572 -0.1024 0.6083 1.0000
1.250 0.6619 0.01267 0.00576 -0.1020 0.6032 1.0000
1.500 0.6847 0.01286 0.00593 -0.1011 0.5970 1.0000
1.750 0.7090 0.01302 0.00602 -0.1003 0.5909 1.0000
2.000 0.7356 0.01323 0.00608 -0.1001 0.5858 1.0000
2.250 0.7577 0.01339 0.00628 -0.0990 0.5790 1.0000
2.500 0.7828 0.01354 0.00636 -0.0984 0.5731 1.0000
2.750 0.8086 0.01373 0.00647 -0.0980 0.5677 1.0000
3.000 0.8312 0.01387 0.00665 -0.0970 0.5605 1.0000
3.250 0.8574 0.01401 0.00670 -0.0966 0.5549 1.0000
3.500 0.8811 0.01420 0.00689 -0.0959 0.5485 1.0000
3.750 0.9054 0.01432 0.00701 -0.0952 0.5417 1.0000
4.000 0.9320 0.01446 0.00706 -0.0949 0.5362 1.0000
4.250 0.9540 0.01461 0.00728 -0.0938 0.5283 1.0000
4.500 0.9802 0.01472 0.00733 -0.0935 0.5225 1.0000
4.750 1.0029 0.01490 0.00755 -0.0925 0.5150 1.0000
5.000 1.0278 0.01501 0.00763 -0.0920 0.5081 1.0000
5.250 1.0515 0.01519 0.00783 -0.0912 0.5011 1.0000
5.500 1.0754 0.01534 0.00799 -0.0905 0.4938 1.0000
5.750 1.0998 0.01553 0.00816 -0.0899 0.4871 1.0000
6.000 1.1226 0.01571 0.00837 -0.0890 0.4791 1.0000
6.250 1.1474 0.01592 0.00855 -0.0885 0.4725 1.0000
6.500 1.1692 0.01615 0.00885 -0.0875 0.4645 1.0000
6.750 1.1939 0.01636 0.00901 -0.0870 0.4575 1.0000
7.000 1.2145 0.01658 0.00931 -0.0858 0.4487 1.0000
7.250 1.2378 0.01682 0.00952 -0.0850 0.4411 1.0000
7.500 1.2586 0.01708 0.00984 -0.0839 0.4328 1.0000
7.750 1.2822 0.01740 0.01014 -0.0832 0.4261 1.0000
8.000 1.3023 0.01771 0.01055 -0.0820 0.4184 1.0000
8.250 1.3261 0.01804 0.01084 -0.0814 0.4118 1.0000
8.500 1.3434 0.01834 0.01125 -0.0798 0.4031 1.0000
8.750 1.3635 0.01864 0.01155 -0.0785 0.3947 1.0000
9.000 1.3797 0.01891 0.01187 -0.0766 0.3850 1.0000
9.250 1.3956 0.01926 0.01227 -0.0748 0.3757 1.0000
9.500 1.4136 0.01961 0.01258 -0.0733 0.3672 1.0000
9.750 1.4250 0.01998 0.01309 -0.0707 0.3579 1.0000
10.000 1.4386 0.02039 0.01350 -0.0685 0.3492 1.0000
10.250 1.4468 0.02080 0.01401 -0.0654 0.3405 1.0000
10.500 1.4556 0.02129 0.01455 -0.0625 0.3318 1.0000
10.750 1.4624 0.02184 0.01510 -0.0595 0.3220 1.0000
11.000 1.4667 0.02249 0.01587 -0.0563 0.3113 1.0000
11.250 1.4705 0.02327 0.01670 -0.0533 0.2999 1.0000
11.500 1.4726 0.02423 0.01769 -0.0504 0.2877 1.0000
11.750 1.4732 0.02538 0.01888 -0.0476 0.2745 1.0000
12.000 1.4727 0.02676 0.02031 -0.0451 0.2595 1.0000
12.250 1.4701 0.02845 0.02204 -0.0426 0.2410 1.0000
12.500 1.4588 0.03092 0.02444 -0.0400 0.2148 1.0000
12.750 1.4414 0.03420 0.02758 -0.0377 0.1819 1.0000
13.000 1.4177 0.03842 0.03160 -0.0358 0.1461 1.0000
13.250 1.3918 0.04328 0.03625 -0.0345 0.1129 1.0000
13.500 1.3697 0.04807 0.04092 -0.0337 0.0934 1.0000
13.750 1.3471 0.05321 0.04599 -0.0333 0.0780 1.0000
14.000 1.3279 0.05821 0.05097 -0.0332 0.0648 1.0000
14.250 1.3150 0.06270 0.05547 -0.0333 0.0555 1.0000
14.500 1.3037 0.06714 0.05994 -0.0336 0.0494 1.0000
14.750 1.2908 0.07194 0.06477 -0.0342 0.0458 1.0000
15.000 1.2832 0.07621 0.06914 -0.0348 0.0433 1.0000
15.250 1.2735 0.08083 0.07382 -0.0356 0.0412 1.0000
15.500 1.2636 0.08559 0.07864 -0.0365 0.0397 1.0000
15.750 1.2558 0.09009 0.08321 -0.0374 0.0385 1.0000
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