GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.48 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe585-il-1000000-n5.txt Download as CSV file: xf-goe585-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9588 0.03279 0.03035 -0.0713 1.0000 0.0068
-12.250 -0.9643 0.02780 0.02500 -0.0704 1.0000 0.0069
-12.000 -0.9571 0.02528 0.02226 -0.0689 1.0000 0.0071
-11.750 -0.9439 0.02344 0.02023 -0.0678 0.9998 0.0073
-11.500 -0.9183 0.02171 0.01830 -0.0689 0.9985 0.0076
-11.250 -0.8908 0.02030 0.01669 -0.0701 0.9969 0.0079
-11.000 -0.8619 0.01910 0.01532 -0.0713 0.9952 0.0081
-10.750 -0.8342 0.01790 0.01397 -0.0721 0.9933 0.0086
-10.500 -0.8065 0.01694 0.01290 -0.0728 0.9910 0.0092
-10.250 -0.7774 0.01611 0.01196 -0.0735 0.9888 0.0098
-10.000 -0.7473 0.01538 0.01113 -0.0745 0.9870 0.0105
-9.750 -0.7166 0.01471 0.01036 -0.0754 0.9856 0.0113
-9.500 -0.6900 0.01426 0.00987 -0.0753 0.9823 0.0122
-9.250 -0.6613 0.01386 0.00943 -0.0757 0.9797 0.0131
-9.000 -0.6315 0.01341 0.00891 -0.0762 0.9777 0.0139
-8.750 -0.6008 0.01301 0.00845 -0.0770 0.9761 0.0147
-8.500 -0.5711 0.01288 0.00833 -0.0773 0.9735 0.0156
-8.250 -0.5425 0.01273 0.00817 -0.0774 0.9695 0.0163
-8.000 -0.5113 0.01256 0.00798 -0.0782 0.9668 0.0173
-7.750 -0.4789 0.01231 0.00768 -0.0791 0.9646 0.0181
-7.500 -0.4488 0.01205 0.00736 -0.0796 0.9609 0.0186
-7.250 -0.4187 0.01178 0.00703 -0.0801 0.9563 0.0189
-7.000 -0.3874 0.01135 0.00656 -0.0809 0.9523 0.0198
-6.750 -0.3561 0.01115 0.00634 -0.0817 0.9477 0.0204
-6.500 -0.3257 0.01095 0.00612 -0.0822 0.9416 0.0210
-6.250 -0.2943 0.01075 0.00588 -0.0829 0.9362 0.0217
-6.000 -0.2655 0.01052 0.00560 -0.0830 0.9291 0.0224
-5.750 -0.2362 0.01027 0.00528 -0.0832 0.9218 0.0231
-5.500 -0.2084 0.01004 0.00499 -0.0831 0.9146 0.0236
-5.250 -0.1808 0.00978 0.00466 -0.0830 0.9071 0.0240
-5.000 -0.1536 0.00958 0.00440 -0.0827 0.8988 0.0243
-4.750 -0.1266 0.00941 0.00415 -0.0824 0.8871 0.0246
-4.500 -0.1005 0.00920 0.00385 -0.0818 0.8716 0.0247
-4.250 -0.0747 0.00901 0.00357 -0.0812 0.8541 0.0248
-4.000 -0.0499 0.00858 0.00303 -0.0804 0.8367 0.0254
-3.750 -0.0248 0.00830 0.00263 -0.0797 0.8174 0.0260
-3.500 0.0002 0.00812 0.00233 -0.0789 0.7934 0.0267
-3.250 0.0250 0.00802 0.00211 -0.0781 0.7668 0.0276
-3.000 0.0501 0.00796 0.00193 -0.0773 0.7422 0.0282
-2.750 0.0758 0.00789 0.00177 -0.0767 0.7238 0.0288
-2.500 0.1020 0.00783 0.00163 -0.0762 0.7079 0.0294
-2.250 0.1282 0.00777 0.00151 -0.0757 0.6931 0.0299
-2.000 0.1546 0.00772 0.00140 -0.0752 0.6782 0.0304
-1.750 0.1810 0.00769 0.00129 -0.0748 0.6628 0.0309
-1.500 0.2074 0.00766 0.00121 -0.0743 0.6471 0.0314
-1.250 0.2337 0.00765 0.00113 -0.0738 0.6284 0.0320
-1.000 0.2598 0.00768 0.00107 -0.0733 0.6061 0.0325
-0.750 0.2856 0.00773 0.00102 -0.0728 0.5790 0.0330
-0.500 0.3111 0.00780 0.00098 -0.0722 0.5482 0.0368
-0.250 0.3356 0.00785 0.00097 -0.0714 0.5078 0.0579
0.000 0.3598 0.00798 0.00100 -0.0707 0.4609 0.0847
0.500 0.4103 0.00819 0.00109 -0.0695 0.4004 0.1233
0.750 0.4361 0.00825 0.00113 -0.0691 0.3808 0.1441
1.000 0.4618 0.00825 0.00117 -0.0686 0.3635 0.1844
1.250 0.4870 0.00820 0.00124 -0.0681 0.3472 0.2562
1.500 0.5127 0.00821 0.00132 -0.0676 0.3316 0.3052
1.750 0.5383 0.00818 0.00139 -0.0672 0.3191 0.3621
2.000 0.5628 0.00799 0.00148 -0.0666 0.3088 0.4812
2.500 0.6565 0.00713 0.00177 -0.0752 0.2840 1.0000
2.750 0.6809 0.00727 0.00185 -0.0744 0.2740 1.0000
3.000 0.7053 0.00740 0.00195 -0.0736 0.2642 1.0000
3.250 0.7296 0.00755 0.00204 -0.0728 0.2551 1.0000
3.500 0.7542 0.00768 0.00214 -0.0720 0.2470 1.0000
3.750 0.7788 0.00782 0.00226 -0.0713 0.2396 1.0000
4.000 0.8031 0.00798 0.00237 -0.0705 0.2301 1.0000
4.250 0.8271 0.00818 0.00250 -0.0697 0.2174 1.0000
4.500 0.8514 0.00835 0.00265 -0.0689 0.2090 1.0000
4.750 0.8757 0.00853 0.00279 -0.0681 0.2003 1.0000
5.000 0.8999 0.00871 0.00294 -0.0674 0.1909 1.0000
5.250 0.9240 0.00892 0.00311 -0.0666 0.1809 1.0000
5.500 0.9484 0.00911 0.00328 -0.0659 0.1741 1.0000
5.750 0.9727 0.00931 0.00345 -0.0652 0.1668 1.0000
6.000 0.9963 0.00956 0.00365 -0.0643 0.1556 1.0000
6.250 1.0204 0.00978 0.00386 -0.0636 0.1457 1.0000
6.500 1.0437 0.01007 0.00409 -0.0628 0.1325 1.0000
6.750 1.0652 0.01052 0.00440 -0.0617 0.1072 1.0000
7.000 1.0848 0.01117 0.00485 -0.0603 0.0766 1.0000
7.250 1.1066 0.01160 0.00522 -0.0593 0.0625 1.0000
7.500 1.1289 0.01199 0.00558 -0.0583 0.0536 1.0000
7.750 1.1518 0.01233 0.00590 -0.0575 0.0473 1.0000
8.000 1.1737 0.01275 0.00628 -0.0565 0.0389 1.0000
8.250 1.1945 0.01326 0.00673 -0.0553 0.0281 1.0000
8.500 1.2145 0.01385 0.00725 -0.0541 0.0176 1.0000
8.750 1.2358 0.01430 0.00770 -0.0530 0.0141 1.0000
9.000 1.2570 0.01474 0.00815 -0.0519 0.0123 1.0000
9.250 1.2778 0.01520 0.00863 -0.0508 0.0106 1.0000
9.500 1.2990 0.01560 0.00908 -0.0498 0.0098 1.0000
9.750 1.3194 0.01605 0.00956 -0.0486 0.0091 1.0000
10.000 1.3390 0.01656 0.01011 -0.0473 0.0084 1.0000
10.250 1.3578 0.01711 0.01070 -0.0459 0.0078 1.0000
10.500 1.3770 0.01758 0.01122 -0.0446 0.0074 1.0000
10.750 1.3955 0.01807 0.01176 -0.0433 0.0071 1.0000
11.000 1.4130 0.01861 0.01235 -0.0417 0.0066 1.0000
11.250 1.4291 0.01919 0.01297 -0.0400 0.0063 1.0000
11.500 1.4425 0.01979 0.01362 -0.0377 0.0059 1.0000
11.750 1.4532 0.02052 0.01442 -0.0351 0.0056 1.0000
12.000 1.4656 0.02113 0.01509 -0.0328 0.0054 1.0000
12.250 1.4770 0.02182 0.01585 -0.0305 0.0053 1.0000
12.500 1.4881 0.02254 0.01664 -0.0283 0.0051 1.0000
12.750 1.4982 0.02334 0.01752 -0.0260 0.0050 1.0000
13.000 1.5072 0.02422 0.01847 -0.0238 0.0048 1.0000
13.250 1.5154 0.02519 0.01952 -0.0216 0.0047 1.0000
13.500 1.5230 0.02624 0.02064 -0.0195 0.0045 1.0000
13.750 1.5292 0.02742 0.02190 -0.0175 0.0043 1.0000
14.000 1.5335 0.02882 0.02339 -0.0155 0.0043 1.0000
14.250 1.5373 0.03032 0.02498 -0.0138 0.0042 1.0000
14.500 1.5372 0.03225 0.02699 -0.0121 0.0040 1.0000
14.750 1.5352 0.03448 0.02934 -0.0106 0.0039 1.0000
15.000 1.5333 0.03689 0.03185 -0.0096 0.0039 1.0000
15.250 1.5295 0.03969 0.03478 -0.0090 0.0038 1.0000
15.500 1.5316 0.04201 0.03719 -0.0087 0.0038 1.0000
15.750 1.5290 0.04500 0.04030 -0.0088 0.0037 1.0000
16.000 1.5210 0.04888 0.04430 -0.0093 0.0036 1.0000
16.250 1.5103 0.05335 0.04891 -0.0104 0.0037 1.0000
16.500 1.5014 0.05786 0.05354 -0.0118 0.0036 1.0000
16.750 1.4892 0.06319 0.05901 -0.0139 0.0035 1.0000
17.000 1.4726 0.06951 0.06547 -0.0167 0.0036 1.0000
17.250 1.4478 0.07762 0.07375 -0.0205 0.0036 1.0000
17.500 1.4297 0.08464 0.08090 -0.0238 0.0036 1.0000
17.750 1.4044 0.09308 0.08948 -0.0279 0.0036 1.0000
18.000 1.3840 0.10071 0.09724 -0.0316 0.0035 1.0000
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