GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 565 AIRFOIL (goe565-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.08 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe565-il-1000000.txt Download as CSV file: xf-goe565-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 565 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.9191 0.03268 0.03018 -0.0716 1.0000 0.0085
-11.750 -0.9307 0.02870 0.02589 -0.0698 1.0000 0.0086
-11.500 -0.9345 0.02576 0.02267 -0.0673 1.0000 0.0088
-11.250 -0.9288 0.02397 0.02071 -0.0650 1.0000 0.0091
-11.000 -0.9181 0.02273 0.01935 -0.0630 1.0000 0.0093
-10.750 -0.8986 0.02174 0.01826 -0.0625 0.9996 0.0096
-10.500 -0.8693 0.02068 0.01706 -0.0638 0.9983 0.0100
-10.250 -0.8403 0.01955 0.01578 -0.0651 0.9968 0.0104
-10.000 -0.8110 0.01842 0.01447 -0.0663 0.9954 0.0107
-9.750 -0.7806 0.01749 0.01338 -0.0675 0.9943 0.0110
-9.500 -0.7539 0.01633 0.01203 -0.0681 0.9924 0.0114
-9.250 -0.7272 0.01496 0.01048 -0.0687 0.9901 0.0122
-9.000 -0.6971 0.01430 0.00974 -0.0696 0.9884 0.0128
-8.750 -0.6660 0.01374 0.00911 -0.0706 0.9869 0.0136
-8.500 -0.6344 0.01321 0.00848 -0.0716 0.9857 0.0143
-8.250 -0.6030 0.01252 0.00767 -0.0727 0.9846 0.0152
-8.000 -0.5706 0.01202 0.00715 -0.0739 0.9838 0.0168
-7.750 -0.5401 0.01169 0.00678 -0.0746 0.9821 0.0181
-7.500 -0.5121 0.01126 0.00629 -0.0747 0.9791 0.0194
-7.250 -0.4810 0.01093 0.00597 -0.0755 0.9772 0.0216
-7.000 -0.4484 0.01078 0.00579 -0.0766 0.9757 0.0235
-6.750 -0.4158 0.01041 0.00540 -0.0777 0.9745 0.0258
-6.500 -0.3816 0.01041 0.00544 -0.0790 0.9734 0.0279
-6.250 -0.3475 0.01041 0.00544 -0.0803 0.9723 0.0298
-6.000 -0.3144 0.01014 0.00512 -0.0814 0.9709 0.0314
-5.750 -0.2863 0.00982 0.00480 -0.0816 0.9677 0.0335
-5.500 -0.2572 0.00974 0.00473 -0.0818 0.9639 0.0352
-5.250 -0.2263 0.00961 0.00458 -0.0823 0.9605 0.0369
-5.000 -0.1950 0.00946 0.00440 -0.0829 0.9570 0.0381
-4.750 -0.1674 0.00945 0.00437 -0.0827 0.9515 0.0388
-4.500 -0.1425 0.00869 0.00354 -0.0821 0.9456 0.0413
-4.250 -0.1142 0.00842 0.00325 -0.0821 0.9405 0.0432
-4.000 -0.0885 0.00822 0.00304 -0.0815 0.9335 0.0449
-3.750 -0.0609 0.00801 0.00279 -0.0813 0.9279 0.0464
-3.500 -0.0344 0.00783 0.00257 -0.0809 0.9216 0.0476
-3.250 -0.0074 0.00767 0.00237 -0.0805 0.9150 0.0486
-3.000 0.0196 0.00756 0.00224 -0.0802 0.9075 0.0494
-2.750 0.0458 0.00728 0.00188 -0.0797 0.8979 0.0516
-2.500 0.0718 0.00707 0.00162 -0.0790 0.8857 0.0546
-2.250 0.0982 0.00693 0.00145 -0.0786 0.8735 0.0574
-2.000 0.1252 0.00682 0.00131 -0.0782 0.8628 0.0600
-1.750 0.1522 0.00674 0.00117 -0.0778 0.8527 0.0630
-1.500 0.1788 0.00657 0.00109 -0.0775 0.8414 0.0834
-1.250 0.2053 0.00642 0.00100 -0.0771 0.8289 0.1165
-1.000 0.2306 0.00610 0.00091 -0.0766 0.8143 0.2006
-0.750 0.2564 0.00590 0.00088 -0.0761 0.8001 0.2750
-0.500 0.2827 0.00581 0.00086 -0.0757 0.7858 0.3135
-0.250 0.3087 0.00570 0.00084 -0.0752 0.7708 0.3606
0.000 0.3335 0.00548 0.00084 -0.0746 0.7549 0.4589
0.250 0.3581 0.00527 0.00088 -0.0739 0.7393 0.5630
0.500 0.3831 0.00517 0.00092 -0.0732 0.7237 0.6322
0.750 0.4080 0.00507 0.00095 -0.0725 0.7089 0.6952
1.000 0.4284 0.00472 0.00100 -0.0707 0.6939 0.8305
1.250 0.4862 0.00459 0.00108 -0.0771 0.6702 0.9852
1.500 0.5262 0.00478 0.00111 -0.0798 0.6317 1.0000
1.750 0.5478 0.00505 0.00116 -0.0784 0.5792 1.0000
2.000 0.5690 0.00538 0.00126 -0.0770 0.5288 1.0000
2.250 0.5917 0.00565 0.00136 -0.0758 0.4887 1.0000
2.500 0.6150 0.00589 0.00146 -0.0749 0.4558 1.0000
2.750 0.6381 0.00616 0.00157 -0.0739 0.4167 1.0000
3.000 0.6608 0.00648 0.00170 -0.0728 0.3749 1.0000
3.250 0.6838 0.00679 0.00186 -0.0718 0.3383 1.0000
3.500 0.7071 0.00710 0.00201 -0.0709 0.3043 1.0000
3.750 0.7304 0.00741 0.00217 -0.0700 0.2690 1.0000
4.000 0.7531 0.00779 0.00236 -0.0690 0.2260 1.0000
4.250 0.7753 0.00823 0.00260 -0.0680 0.1857 1.0000
4.500 0.7994 0.00851 0.00280 -0.0672 0.1687 1.0000
4.750 0.8238 0.00877 0.00300 -0.0666 0.1545 1.0000
5.000 0.8483 0.00901 0.00320 -0.0659 0.1401 1.0000
5.250 0.8707 0.00947 0.00345 -0.0649 0.1001 1.0000
5.500 0.8896 0.01030 0.00395 -0.0634 0.0454 1.0000
5.750 0.9130 0.01068 0.00428 -0.0625 0.0369 1.0000
6.000 0.9372 0.01097 0.00459 -0.0618 0.0346 1.0000
6.250 0.9608 0.01133 0.00496 -0.0610 0.0320 1.0000
6.500 0.9833 0.01181 0.00548 -0.0600 0.0288 1.0000
6.750 1.0076 0.01208 0.00577 -0.0594 0.0278 1.0000
7.000 1.0315 0.01238 0.00611 -0.0586 0.0263 1.0000
7.250 1.0548 0.01274 0.00649 -0.0578 0.0247 1.0000
7.500 1.0759 0.01333 0.00710 -0.0567 0.0224 1.0000
7.750 1.0983 0.01375 0.00757 -0.0557 0.0211 1.0000
8.000 1.1223 0.01402 0.00785 -0.0551 0.0200 1.0000
8.250 1.1453 0.01435 0.00821 -0.0543 0.0186 1.0000
8.500 1.1669 0.01483 0.00869 -0.0533 0.0174 1.0000
8.750 1.1855 0.01558 0.00951 -0.0518 0.0162 1.0000
9.000 1.2082 0.01590 0.00986 -0.0509 0.0154 1.0000
9.250 1.2304 0.01625 0.01024 -0.0501 0.0145 1.0000
9.500 1.2517 0.01667 0.01069 -0.0490 0.0138 1.0000
9.750 1.2703 0.01730 0.01133 -0.0476 0.0128 1.0000
10.000 1.2856 0.01819 0.01231 -0.0457 0.0121 1.0000
10.250 1.3048 0.01871 0.01289 -0.0444 0.0118 1.0000
10.500 1.3229 0.01928 0.01352 -0.0429 0.0113 1.0000
10.750 1.3396 0.01992 0.01423 -0.0412 0.0109 1.0000
11.000 1.3560 0.02047 0.01482 -0.0395 0.0104 1.0000
11.250 1.3697 0.02108 0.01547 -0.0373 0.0101 1.0000
11.500 1.3791 0.02192 0.01637 -0.0346 0.0097 1.0000
11.750 1.3774 0.02352 0.01810 -0.0303 0.0092 1.0000
12.000 1.3853 0.02453 0.01922 -0.0277 0.0090 1.0000
12.250 1.3964 0.02534 0.02011 -0.0256 0.0088 1.0000
12.500 1.4059 0.02626 0.02112 -0.0235 0.0087 1.0000
12.750 1.4150 0.02725 0.02221 -0.0214 0.0084 1.0000
13.000 1.4226 0.02838 0.02342 -0.0194 0.0081 1.0000
13.250 1.4283 0.02968 0.02482 -0.0173 0.0080 1.0000
13.500 1.4320 0.03121 0.02645 -0.0153 0.0078 1.0000
13.750 1.4376 0.03263 0.02796 -0.0137 0.0076 1.0000
14.000 1.4418 0.03424 0.02965 -0.0122 0.0074 1.0000
14.250 1.4442 0.03610 0.03159 -0.0109 0.0073 1.0000
14.500 1.4429 0.03842 0.03402 -0.0098 0.0071 1.0000
14.750 1.4377 0.04134 0.03707 -0.0089 0.0071 1.0000
15.000 1.4294 0.04477 0.04062 -0.0084 0.0069 1.0000
15.250 1.4174 0.04893 0.04494 -0.0086 0.0068 1.0000
15.500 1.4005 0.05405 0.05024 -0.0094 0.0067 1.0000
15.750 1.3898 0.05877 0.05511 -0.0108 0.0067 1.0000
16.000 1.3703 0.06514 0.06167 -0.0132 0.0067 1.0000
16.250 1.3466 0.07273 0.06945 -0.0167 0.0066 1.0000
16.500 1.3313 0.07934 0.07622 -0.0200 0.0066 1.0000
16.750 1.3232 0.08506 0.08205 -0.0231 0.0065 1.0000
17.000 1.3014 0.09346 0.09062 -0.0277 0.0065 1.0000
17.250 1.2803 0.10209 0.09940 -0.0326 0.0065 1.0000
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