GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.45 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe488-il-1000000.txt Download as CSV file: xf-goe488-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4237 0.08471 0.08313 -0.0255 1.0000 0.0189
-8.000 -0.4341 0.08239 0.08084 -0.0239 1.0000 0.0180
-7.750 -0.4454 0.07805 0.07655 -0.0277 0.9987 0.0197
-7.500 -0.4304 0.07296 0.07144 -0.0331 0.9964 0.0187
-7.250 -0.4081 0.06572 0.06414 -0.0435 0.9931 0.0186
-7.000 -0.3950 0.03185 0.02952 -0.0725 0.9839 0.0205
-6.750 -0.3591 0.03740 0.03524 -0.0720 0.9836 0.0208
-6.500 -0.3244 0.04786 0.04599 -0.0671 0.9837 0.0220
-6.250 -0.2973 0.04371 0.04173 -0.0709 0.9788 0.0242
-6.000 -0.2771 0.02507 0.02221 -0.0794 0.9729 0.0239
-5.750 -0.2483 0.02112 0.01779 -0.0810 0.9703 0.0253
-5.500 -0.2307 0.01727 0.01337 -0.0801 0.9624 0.0266
-5.250 -0.2037 0.01556 0.01146 -0.0806 0.9582 0.0274
-5.000 -0.1760 0.01512 0.01097 -0.0807 0.9528 0.0282
-4.750 -0.1493 0.01486 0.01070 -0.0806 0.9462 0.0292
-4.500 -0.1227 0.01347 0.00907 -0.0804 0.9406 0.0293
-4.250 -0.0984 0.01243 0.00785 -0.0796 0.9328 0.0295
-4.000 -0.0717 0.01153 0.00678 -0.0793 0.9264 0.0298
-3.750 -0.0464 0.01082 0.00596 -0.0786 0.9190 0.0302
-3.500 -0.0192 0.01035 0.00541 -0.0784 0.9132 0.0310
-3.250 0.0066 0.00984 0.00482 -0.0778 0.9060 0.0316
-3.000 0.0332 0.00938 0.00428 -0.0774 0.8996 0.0321
-2.750 0.0594 0.00902 0.00386 -0.0769 0.8923 0.0326
-2.500 0.0859 0.00868 0.00346 -0.0764 0.8849 0.0330
-2.250 0.1121 0.00837 0.00311 -0.0760 0.8775 0.0332
-2.000 0.1385 0.00809 0.00278 -0.0755 0.8702 0.0335
-1.750 0.1646 0.00784 0.00250 -0.0750 0.8621 0.0337
-1.500 0.1909 0.00764 0.00225 -0.0745 0.8536 0.0339
-1.250 0.2158 0.00718 0.00172 -0.0737 0.8438 0.0353
-1.000 0.2418 0.00695 0.00145 -0.0732 0.8347 0.0371
-0.500 0.2947 0.00672 0.00118 -0.0722 0.8163 0.0408
-0.250 0.3211 0.00665 0.00107 -0.0718 0.8049 0.0427
0.000 0.3472 0.00661 0.00099 -0.0712 0.7896 0.0442
0.250 0.3726 0.00648 0.00088 -0.0705 0.7709 0.0646
0.500 0.3962 0.00622 0.00087 -0.0696 0.7444 0.1759
0.750 0.4189 0.00625 0.00087 -0.0684 0.6965 0.2333
1.000 0.4381 0.00654 0.00094 -0.0666 0.6156 0.2859
1.250 0.4473 0.00550 0.00105 -0.0631 0.5624 0.7765
1.750 0.5348 0.00628 0.00148 -0.0703 0.3756 0.9939
2.000 0.5841 0.00651 0.00156 -0.0752 0.3489 1.0000
2.250 0.6070 0.00665 0.00163 -0.0741 0.3362 1.0000
2.500 0.6300 0.00677 0.00170 -0.0730 0.3260 1.0000
2.750 0.6531 0.00691 0.00179 -0.0720 0.3161 1.0000
3.000 0.6765 0.00703 0.00187 -0.0710 0.3059 1.0000
3.250 0.6998 0.00717 0.00196 -0.0700 0.2942 1.0000
3.500 0.7231 0.00732 0.00205 -0.0690 0.2817 1.0000
3.750 0.7465 0.00747 0.00216 -0.0681 0.2676 1.0000
4.000 0.7700 0.00763 0.00226 -0.0672 0.2537 1.0000
4.250 0.7933 0.00782 0.00238 -0.0662 0.2348 1.0000
4.500 0.8145 0.00818 0.00254 -0.0649 0.1949 1.0000
4.750 0.8348 0.00864 0.00280 -0.0635 0.1550 1.0000
5.000 0.8562 0.00902 0.00305 -0.0623 0.1293 1.0000
5.250 0.8781 0.00939 0.00329 -0.0611 0.1066 1.0000
5.500 0.8972 0.01003 0.00367 -0.0596 0.0602 1.0000
5.750 0.9191 0.01044 0.00401 -0.0584 0.0437 1.0000
6.000 0.9395 0.01103 0.00444 -0.0570 0.0184 1.0000
6.250 0.9621 0.01142 0.00484 -0.0559 0.0153 1.0000
6.500 0.9850 0.01177 0.00523 -0.0550 0.0142 1.0000
6.750 1.0079 0.01213 0.00563 -0.0540 0.0135 1.0000
7.000 1.0304 0.01253 0.00609 -0.0530 0.0127 1.0000
7.250 1.0522 0.01300 0.00660 -0.0519 0.0118 1.0000
7.500 1.0718 0.01373 0.00741 -0.0504 0.0109 1.0000
7.750 1.0909 0.01449 0.00825 -0.0488 0.0104 1.0000
8.000 1.1124 0.01495 0.00876 -0.0477 0.0100 1.0000
8.250 1.1327 0.01552 0.00940 -0.0464 0.0097 1.0000
8.500 1.1526 0.01612 0.01005 -0.0451 0.0094 1.0000
8.750 1.1716 0.01677 0.01076 -0.0436 0.0090 1.0000
9.000 1.1898 0.01747 0.01152 -0.0420 0.0087 1.0000
9.250 1.2075 0.01820 0.01232 -0.0404 0.0084 1.0000
9.500 1.2238 0.01902 0.01318 -0.0386 0.0081 1.0000
9.750 1.2349 0.02027 0.01448 -0.0361 0.0077 1.0000
10.000 1.2408 0.02217 0.01651 -0.0329 0.0073 1.0000
10.250 1.2581 0.02272 0.01714 -0.0313 0.0072 1.0000
10.500 1.2705 0.02368 0.01819 -0.0290 0.0071 1.0000
10.750 1.2807 0.02465 0.01926 -0.0263 0.0069 1.0000
11.000 1.2896 0.02570 0.02042 -0.0235 0.0068 1.0000
11.250 1.2967 0.02701 0.02184 -0.0206 0.0067 1.0000
11.500 1.3032 0.02835 0.02330 -0.0178 0.0066 1.0000
11.750 1.3098 0.02954 0.02459 -0.0153 0.0064 1.0000
12.000 1.3138 0.03111 0.02629 -0.0126 0.0064 1.0000
12.250 1.3158 0.03289 0.02821 -0.0100 0.0063 1.0000
12.500 1.3144 0.03510 0.03059 -0.0073 0.0063 1.0000
12.750 1.3191 0.03626 0.03183 -0.0055 0.0061 1.0000
13.000 1.3146 0.03882 0.03456 -0.0033 0.0061 1.0000
13.250 1.3102 0.04138 0.03727 -0.0016 0.0060 1.0000
13.500 1.3031 0.04438 0.04045 -0.0002 0.0060 1.0000
13.750 1.2948 0.04766 0.04389 0.0006 0.0060 1.0000
14.000 1.2878 0.05095 0.04731 0.0007 0.0059 1.0000
14.250 1.2878 0.05347 0.04987 0.0004 0.0058 1.0000
14.500 1.2685 0.05918 0.05581 -0.0009 0.0058 1.0000
14.750 1.2583 0.06389 0.06065 -0.0028 0.0058 1.0000
15.000 1.2420 0.07006 0.06700 -0.0057 0.0058 1.0000
15.250 1.2327 0.07543 0.07246 -0.0087 0.0057 1.0000
15.500 1.2068 0.08454 0.08181 -0.0140 0.0058 1.0000
15.750 1.2095 0.08809 0.08536 -0.0163 0.0056 1.0000
16.000 1.1744 0.09997 0.09749 -0.0234 0.0057 1.0000
16.250 1.1289 0.11500 0.11279 -0.0325 0.0060 1.0000
16.500 1.0964 0.12776 0.12574 -0.0402 0.0062 1.0000
16.750 1.0755 0.13838 0.13647 -0.0466 0.0062 1.0000
17.000 1.0325 0.15653 0.15479 -0.0571 0.0066 1.0000
17.250 0.9782 0.18164 0.18000 -0.0695 0.0078 1.0000
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Polar data table (+)
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