GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 100,000 Max Cl/Cd: 42.03 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe766-il-100000-n5.txt Download as CSV file: xf-goe766-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7192 0.07612 0.07025 -0.0291 1.0000 0.0498
-11.500 -0.7628 0.06664 0.06060 -0.0359 1.0000 0.0495
-11.250 -0.7958 0.06087 0.05463 -0.0378 1.0000 0.0494
-11.000 -0.8256 0.05659 0.05011 -0.0364 1.0000 0.0494
-10.750 -0.8496 0.05297 0.04621 -0.0334 1.0000 0.0496
-10.500 -0.8661 0.04929 0.04212 -0.0306 1.0000 0.0499
-10.250 -0.8709 0.04617 0.03867 -0.0281 1.0000 0.0503
-10.000 -0.8629 0.04397 0.03634 -0.0265 1.0000 0.0508
-9.750 -0.8520 0.04219 0.03445 -0.0250 1.0000 0.0516
-9.500 -0.8403 0.04052 0.03266 -0.0234 1.0000 0.0525
-9.250 -0.8284 0.03878 0.03073 -0.0217 1.0000 0.0536
-9.000 -0.8165 0.03689 0.02859 -0.0199 1.0000 0.0548
-8.750 -0.8036 0.03494 0.02634 -0.0180 1.0000 0.0558
-8.500 -0.7887 0.03309 0.02418 -0.0163 1.0000 0.0567
-8.250 -0.7723 0.03144 0.02220 -0.0146 1.0000 0.0577
-8.000 -0.7538 0.02999 0.02063 -0.0132 1.0000 0.0589
-7.750 -0.7343 0.02888 0.01954 -0.0120 1.0000 0.0603
-7.500 -0.7146 0.02784 0.01843 -0.0107 1.0000 0.0619
-7.250 -0.6945 0.02675 0.01723 -0.0094 1.0000 0.0634
-7.000 -0.6739 0.02566 0.01602 -0.0080 1.0000 0.0649
-6.750 -0.6530 0.02466 0.01488 -0.0067 1.0000 0.0665
-6.500 -0.6325 0.02370 0.01389 -0.0053 1.0000 0.0684
-6.250 -0.6127 0.02290 0.01315 -0.0039 1.0000 0.0706
-6.000 -0.5925 0.02216 0.01242 -0.0025 1.0000 0.0732
-5.750 -0.5723 0.02144 0.01166 -0.0010 1.0000 0.0759
-5.500 -0.5525 0.02072 0.01091 0.0006 1.0000 0.0785
-5.250 -0.5339 0.02006 0.01033 0.0022 1.0000 0.0818
-5.000 -0.5147 0.01951 0.00980 0.0039 1.0000 0.0863
-4.750 -0.4961 0.01895 0.00928 0.0056 1.0000 0.0914
-4.500 -0.4776 0.01845 0.00885 0.0073 1.0000 0.0978
-4.250 -0.4595 0.01798 0.00846 0.0091 1.0000 0.1056
-4.000 -0.4229 0.01744 0.00803 0.0071 0.9890 0.1220
-3.750 -0.3832 0.01689 0.00759 0.0046 0.9736 0.1463
-3.500 -0.3437 0.01633 0.00715 0.0022 0.9566 0.1759
-3.250 -0.3071 0.01573 0.00675 0.0004 0.9352 0.2109
-3.000 -0.2700 0.01505 0.00638 -0.0014 0.9110 0.2637
-2.500 -0.2062 0.01344 0.00588 -0.0025 0.8416 0.4992
-2.250 -0.1768 0.01300 0.00586 -0.0017 0.7946 0.6305
-2.000 -0.1463 0.01292 0.00578 -0.0008 0.7459 0.7019
-1.750 -0.1167 0.01298 0.00571 0.0000 0.7024 0.7439
-1.500 -0.0863 0.01312 0.00568 0.0004 0.6650 0.7788
-1.250 -0.0550 0.01328 0.00569 0.0006 0.6329 0.8082
-1.000 -0.0226 0.01347 0.00571 0.0005 0.6058 0.8357
-0.750 0.0138 0.01372 0.00583 -0.0002 0.5809 0.8641
-0.500 0.0490 0.01399 0.00593 -0.0009 0.5593 0.8907
-0.250 0.0870 0.01426 0.00603 -0.0022 0.5395 0.9097
0.000 0.1262 0.01450 0.00611 -0.0039 0.5214 0.9253
0.250 0.1697 0.01472 0.00617 -0.0066 0.5038 0.9362
0.500 0.2072 0.01488 0.00619 -0.0084 0.4878 0.9466
0.750 0.2444 0.01504 0.00622 -0.0101 0.4726 0.9582
1.000 0.2854 0.01519 0.00625 -0.0126 0.4579 0.9692
1.250 0.3265 0.01531 0.00625 -0.0153 0.4442 0.9787
1.500 0.3641 0.01540 0.00623 -0.0174 0.4310 0.9868
1.750 0.4013 0.01548 0.00625 -0.0194 0.4172 0.9944
2.000 0.4360 0.01556 0.00625 -0.0210 0.4050 1.0000
2.250 0.4564 0.01568 0.00629 -0.0198 0.3959 1.0000
2.500 0.4772 0.01580 0.00641 -0.0186 0.3859 1.0000
2.750 0.4978 0.01598 0.00648 -0.0173 0.3774 1.0000
3.000 0.5190 0.01614 0.00666 -0.0161 0.3673 1.0000
3.250 0.5400 0.01634 0.00678 -0.0148 0.3595 1.0000
3.500 0.5615 0.01655 0.00701 -0.0136 0.3506 1.0000
4.000 0.6044 0.01703 0.00745 -0.0112 0.3349 1.0000
4.250 0.6258 0.01729 0.00765 -0.0100 0.3278 1.0000
4.500 0.6476 0.01756 0.00796 -0.0089 0.3196 1.0000
4.750 0.6691 0.01783 0.00819 -0.0077 0.3121 1.0000
5.000 0.6908 0.01812 0.00851 -0.0065 0.3039 1.0000
5.250 0.7123 0.01840 0.00877 -0.0053 0.2962 1.0000
5.500 0.7339 0.01872 0.00913 -0.0041 0.2884 1.0000
5.750 0.7553 0.01903 0.00943 -0.0029 0.2806 1.0000
6.000 0.7767 0.01936 0.00979 -0.0018 0.2723 1.0000
6.250 0.7977 0.01967 0.01010 -0.0005 0.2636 1.0000
6.500 0.8187 0.02001 0.01051 0.0007 0.2544 1.0000
6.750 0.8392 0.02035 0.01080 0.0020 0.2458 1.0000
7.000 0.8600 0.02072 0.01130 0.0032 0.2361 1.0000
7.250 0.8801 0.02110 0.01166 0.0045 0.2276 1.0000
7.500 0.9003 0.02149 0.01216 0.0057 0.2176 1.0000
7.750 0.9200 0.02191 0.01265 0.0071 0.2079 1.0000
8.000 0.9389 0.02234 0.01308 0.0085 0.1982 1.0000
8.250 0.9582 0.02280 0.01366 0.0098 0.1864 1.0000
8.500 0.9766 0.02330 0.01423 0.0112 0.1748 1.0000
8.750 0.9942 0.02387 0.01484 0.0127 0.1630 1.0000
9.000 1.0107 0.02450 0.01548 0.0142 0.1515 1.0000
9.250 1.0257 0.02524 0.01619 0.0159 0.1410 1.0000
9.500 1.0402 0.02607 0.01706 0.0176 0.1313 1.0000
9.750 1.0532 0.02700 0.01802 0.0194 0.1233 1.0000
10.000 1.0640 0.02801 0.01901 0.0213 0.1168 1.0000
10.250 1.0751 0.02906 0.02013 0.0233 0.1109 1.0000
10.500 1.0836 0.03018 0.02127 0.0254 0.1061 1.0000
10.750 1.0903 0.03138 0.02249 0.0276 0.1023 1.0000
11.000 1.0958 0.03256 0.02379 0.0300 0.0984 1.0000
11.250 1.0983 0.03385 0.02513 0.0325 0.0953 1.0000
11.500 1.0994 0.03532 0.02659 0.0346 0.0928 1.0000
11.750 1.1022 0.03691 0.02826 0.0363 0.0905 1.0000
12.000 1.1046 0.03867 0.03017 0.0376 0.0882 1.0000
12.250 1.1060 0.04063 0.03224 0.0384 0.0860 1.0000
12.500 1.1071 0.04274 0.03442 0.0389 0.0840 1.0000
12.750 1.1079 0.04499 0.03671 0.0391 0.0822 1.0000
13.000 1.1112 0.04717 0.03889 0.0394 0.0807 1.0000
13.250 1.1086 0.05016 0.04208 0.0388 0.0791 1.0000
13.500 1.1061 0.05329 0.04538 0.0380 0.0776 1.0000
13.750 1.1034 0.05654 0.04877 0.0371 0.0763 1.0000
14.000 1.0997 0.05999 0.05235 0.0360 0.0750 1.0000
14.250 1.0965 0.06344 0.05592 0.0348 0.0737 1.0000
14.500 1.0943 0.06681 0.05936 0.0337 0.0726 1.0000
14.750 1.0965 0.06952 0.06208 0.0330 0.0713 1.0000
15.000 1.0949 0.07291 0.06552 0.0320 0.0703 1.0000
15.250 1.0750 0.07925 0.07210 0.0285 0.0696 1.0000
15.500 1.0492 0.08684 0.07994 0.0242 0.0690 1.0000
15.750 1.0098 0.09741 0.09076 0.0179 0.0686 1.0000
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