GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 500,000 Max Cl/Cd: 103.08 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe591-il-500000-n5.txt Download as CSV file: xf-goe591-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3102 0.12265 0.12029 -0.0390 1.0000 0.0087
-10.000 -0.4906 0.02591 0.02257 -0.1140 0.9457 0.0138
-9.750 -0.4750 0.02234 0.01847 -0.1149 0.9358 0.0145
-9.500 -0.4461 0.02221 0.01835 -0.1153 0.9282 0.0150
-9.250 -0.4154 0.02222 0.01836 -0.1160 0.9201 0.0155
-9.000 -0.3885 0.02184 0.01789 -0.1162 0.9100 0.0161
-8.750 -0.3639 0.02085 0.01668 -0.1163 0.8991 0.0169
-8.500 -0.3423 0.01933 0.01481 -0.1160 0.8870 0.0179
-8.250 -0.3196 0.01820 0.01336 -0.1155 0.8748 0.0186
-8.000 -0.2949 0.01774 0.01282 -0.1152 0.8633 0.0192
-7.750 -0.2688 0.01763 0.01265 -0.1149 0.8526 0.0198
-7.500 -0.2433 0.01738 0.01228 -0.1146 0.8422 0.0205
-7.250 -0.2187 0.01693 0.01168 -0.1141 0.8317 0.0214
-7.000 -0.1945 0.01634 0.01090 -0.1135 0.8219 0.0223
-6.750 -0.1697 0.01590 0.01026 -0.1130 0.8126 0.0231
-6.500 -0.1443 0.01557 0.00977 -0.1125 0.8035 0.0237
-6.250 -0.1211 0.01461 0.00861 -0.1119 0.7954 0.0246
-6.000 -0.0965 0.01405 0.00795 -0.1114 0.7872 0.0254
-5.750 -0.0710 0.01370 0.00751 -0.1109 0.7798 0.0262
-5.500 -0.0454 0.01334 0.00706 -0.1105 0.7719 0.0270
-5.250 -0.0198 0.01293 0.00653 -0.1101 0.7646 0.0277
-5.000 0.0061 0.01258 0.00608 -0.1096 0.7566 0.0285
-4.750 0.0319 0.01225 0.00564 -0.1092 0.7492 0.0293
-4.500 0.0578 0.01190 0.00521 -0.1087 0.7410 0.0298
-4.250 0.0837 0.01159 0.00479 -0.1083 0.7330 0.0302
-4.000 0.1097 0.01131 0.00444 -0.1078 0.7245 0.0306
-3.750 0.1358 0.01107 0.00412 -0.1074 0.7165 0.0309
-3.500 0.1610 0.01069 0.00365 -0.1068 0.7075 0.0319
-3.250 0.1867 0.01040 0.00331 -0.1063 0.6983 0.0330
-3.000 0.2126 0.01020 0.00305 -0.1058 0.6894 0.0339
-2.750 0.2388 0.01003 0.00283 -0.1054 0.6798 0.0346
-2.500 0.2649 0.00991 0.00263 -0.1050 0.6701 0.0356
-2.250 0.2908 0.00981 0.00247 -0.1045 0.6597 0.0365
-2.000 0.3171 0.00972 0.00231 -0.1041 0.6494 0.0375
-1.750 0.3433 0.00965 0.00219 -0.1037 0.6396 0.0388
-1.500 0.3693 0.00961 0.00208 -0.1032 0.6291 0.0407
-1.250 0.3953 0.00953 0.00200 -0.1028 0.6179 0.0475
-1.000 0.4210 0.00945 0.00197 -0.1023 0.6071 0.0695
-0.750 0.4469 0.00943 0.00193 -0.1019 0.5969 0.0821
-0.500 0.4728 0.00943 0.00189 -0.1014 0.5858 0.0916
-0.250 0.4985 0.00940 0.00188 -0.1010 0.5748 0.1076
0.000 0.5240 0.00937 0.00188 -0.1005 0.5644 0.1353
0.250 0.5493 0.00935 0.00191 -0.1000 0.5537 0.1701
0.500 0.5750 0.00934 0.00193 -0.0996 0.5433 0.1983
0.750 0.6003 0.00933 0.00197 -0.0992 0.5329 0.2341
1.000 0.6232 0.00908 0.00205 -0.0984 0.5212 0.3735
1.250 0.6365 0.00817 0.00219 -0.0956 0.5094 0.7572
1.750 0.7399 0.00816 0.00244 -0.1059 0.4827 1.0000
2.000 0.7630 0.00829 0.00251 -0.1049 0.4750 1.0000
2.250 0.7862 0.00842 0.00258 -0.1040 0.4659 1.0000
2.500 0.8092 0.00857 0.00266 -0.1030 0.4567 1.0000
2.750 0.8320 0.00873 0.00276 -0.1020 0.4476 1.0000
3.000 0.8556 0.00886 0.00285 -0.1011 0.4394 1.0000
3.250 0.8783 0.00904 0.00296 -0.1001 0.4303 1.0000
3.500 0.9020 0.00918 0.00308 -0.0993 0.4219 1.0000
3.750 0.9251 0.00935 0.00320 -0.0984 0.4146 1.0000
4.000 0.9491 0.00949 0.00333 -0.0977 0.4079 1.0000
4.500 0.9962 0.00981 0.00362 -0.0961 0.3934 1.0000
5.000 1.0427 0.01017 0.00394 -0.0944 0.3774 1.0000
5.250 1.0652 0.01038 0.00412 -0.0935 0.3689 1.0000
5.500 1.0885 0.01056 0.00430 -0.0927 0.3603 1.0000
5.750 1.1109 0.01078 0.00449 -0.0917 0.3515 1.0000
6.000 1.1325 0.01103 0.00472 -0.0906 0.3407 1.0000
6.250 1.1548 0.01125 0.00493 -0.0897 0.3302 1.0000
6.500 1.1740 0.01160 0.00520 -0.0882 0.3119 1.0000
6.750 1.1921 0.01200 0.00551 -0.0866 0.2894 1.0000
7.000 1.2080 0.01251 0.00587 -0.0846 0.2645 1.0000
7.250 1.2242 0.01296 0.00624 -0.0827 0.2451 1.0000
7.500 1.2390 0.01342 0.00662 -0.0805 0.2276 1.0000
7.750 1.2529 0.01392 0.00704 -0.0782 0.2101 1.0000
8.000 1.2665 0.01445 0.00750 -0.0759 0.1931 1.0000
8.250 1.2796 0.01502 0.00799 -0.0736 0.1726 1.0000
8.500 1.2883 0.01583 0.00863 -0.0706 0.1444 1.0000
8.750 1.2963 0.01669 0.00935 -0.0677 0.1220 1.0000
9.000 1.3064 0.01747 0.01006 -0.0652 0.1065 1.0000
9.250 1.3165 0.01826 0.01081 -0.0628 0.0898 1.0000
9.500 1.3117 0.01991 0.01219 -0.0586 0.0503 1.0000
9.750 1.3100 0.02149 0.01364 -0.0550 0.0218 1.0000
10.000 1.3170 0.02262 0.01477 -0.0527 0.0161 1.0000
10.250 1.3271 0.02358 0.01579 -0.0509 0.0146 1.0000
10.500 1.3354 0.02472 0.01700 -0.0490 0.0129 1.0000
10.750 1.3458 0.02575 0.01810 -0.0474 0.0122 1.0000
11.000 1.3555 0.02687 0.01931 -0.0459 0.0116 1.0000
11.250 1.3639 0.02813 0.02065 -0.0444 0.0109 1.0000
11.500 1.3708 0.02954 0.02213 -0.0428 0.0102 1.0000
11.750 1.3764 0.03112 0.02379 -0.0414 0.0098 1.0000
12.000 1.3791 0.03301 0.02577 -0.0399 0.0093 1.0000
12.250 1.3853 0.03466 0.02751 -0.0387 0.0090 1.0000
12.500 1.3907 0.03643 0.02937 -0.0377 0.0087 1.0000
12.750 1.3947 0.03839 0.03142 -0.0367 0.0083 1.0000
13.000 1.3976 0.04053 0.03366 -0.0359 0.0080 1.0000
13.250 1.3993 0.04287 0.03609 -0.0351 0.0078 1.0000
13.500 1.4008 0.04532 0.03863 -0.0345 0.0075 1.0000
13.750 1.3993 0.04819 0.04159 -0.0341 0.0074 1.0000
14.000 1.3984 0.05108 0.04458 -0.0338 0.0072 1.0000
14.250 1.3947 0.05444 0.04804 -0.0337 0.0071 1.0000
14.500 1.3888 0.05818 0.05188 -0.0339 0.0069 1.0000
14.750 1.3830 0.06203 0.05584 -0.0342 0.0067 1.0000
15.000 1.3789 0.06579 0.05971 -0.0346 0.0066 1.0000
15.250 1.3763 0.06942 0.06345 -0.0352 0.0065 1.0000
15.500 1.3739 0.07310 0.06723 -0.0359 0.0063 1.0000
15.750 1.3655 0.07770 0.07195 -0.0368 0.0063 1.0000
16.000 1.3623 0.08165 0.07602 -0.0377 0.0060 1.0000
16.250 1.3568 0.08602 0.08049 -0.0389 0.0059 1.0000
16.500 1.3519 0.09036 0.08493 -0.0401 0.0058 1.0000
16.750 1.3442 0.09520 0.08988 -0.0415 0.0057 1.0000
17.000 1.3401 0.09955 0.09432 -0.0430 0.0055 1.0000
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