GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 500,000 Max Cl/Cd: 103.94 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe359-il-500000-n5.txt Download as CSV file: xf-goe359-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1375 0.08688 0.08479 -0.0458 0.9345 0.0077
-8.750 -0.2647 0.10309 0.10095 -0.0283 1.0000 0.0085
-8.250 -0.2373 0.09598 0.09385 -0.0343 0.9845 0.0074
-8.000 -0.2190 0.09151 0.08936 -0.0394 0.9483 0.0071
-7.500 -0.1818 0.08273 0.08034 -0.0499 0.8766 0.0068
-7.250 -0.1738 0.07965 0.07717 -0.0520 0.8539 0.0069
-7.000 -0.1616 0.07621 0.07366 -0.0554 0.8369 0.0070
-6.750 -0.1470 0.07259 0.06996 -0.0595 0.8220 0.0071
-6.500 -0.1300 0.06875 0.06606 -0.0641 0.8085 0.0075
-6.250 -0.1095 0.06386 0.06111 -0.0705 0.7962 0.0082
-6.000 -0.0859 0.05859 0.05575 -0.0775 0.7850 0.0085
-5.750 -0.0587 0.05294 0.05000 -0.0850 0.7744 0.0088
-5.250 -0.0041 0.04645 0.04329 -0.0939 0.7513 0.0096
-5.000 0.0266 0.04242 0.03911 -0.0989 0.7397 0.0104
-4.750 0.0683 0.03309 0.02940 -0.1083 0.7303 0.0127
-4.500 0.0954 0.03162 0.02779 -0.1096 0.7180 0.0133
-4.250 0.1348 0.01937 0.01455 -0.1155 0.7102 0.0183
-4.000 0.1611 0.01942 0.01454 -0.1156 0.6982 0.0189
-3.750 0.1875 0.01935 0.01436 -0.1155 0.6865 0.0196
-3.250 0.2416 0.01783 0.01243 -0.1157 0.6631 0.0228
-3.000 0.2697 0.01633 0.01055 -0.1158 0.6521 0.0248
-2.750 0.2973 0.01592 0.00990 -0.1156 0.6412 0.0261
-2.500 0.3247 0.01558 0.00936 -0.1155 0.6307 0.0267
-2.250 0.3522 0.01458 0.00807 -0.1155 0.6202 0.0272
-2.000 0.3793 0.01316 0.00637 -0.1155 0.6092 0.0283
-1.750 0.4064 0.01258 0.00561 -0.1154 0.5974 0.0289
-1.500 0.4336 0.01208 0.00495 -0.1152 0.5852 0.0292
-1.250 0.4609 0.01168 0.00444 -0.1151 0.5736 0.0298
-1.000 0.4881 0.01137 0.00402 -0.1149 0.5621 0.0306
-0.750 0.5153 0.01113 0.00369 -0.1148 0.5515 0.0316
-0.250 0.5699 0.01074 0.00316 -0.1144 0.5319 0.0333
0.000 0.5970 0.01060 0.00295 -0.1143 0.5222 0.0339
0.250 0.6240 0.01049 0.00277 -0.1141 0.5108 0.0343
0.500 0.6510 0.01041 0.00264 -0.1139 0.4992 0.0350
0.750 0.6782 0.01036 0.00255 -0.1138 0.4897 0.0360
1.000 0.7051 0.01031 0.00246 -0.1136 0.4801 0.0362
1.500 0.7585 0.01031 0.00232 -0.1132 0.4534 0.0362
1.750 0.7853 0.01034 0.00229 -0.1130 0.4403 0.0363
2.000 0.8122 0.01037 0.00229 -0.1128 0.4307 0.0366
2.250 0.8390 0.01044 0.00230 -0.1126 0.4214 0.0371
2.500 0.8658 0.01051 0.00233 -0.1125 0.4113 0.0379
2.750 0.8926 0.01059 0.00238 -0.1123 0.4018 0.0404
3.000 0.9192 0.01067 0.00244 -0.1121 0.3923 0.0533
3.250 0.9459 0.01053 0.00265 -0.1121 0.3809 0.2447
3.750 0.9947 0.00957 0.00304 -0.1112 0.3508 1.0000
4.000 1.0200 0.00985 0.00320 -0.1108 0.3267 1.0000
4.250 1.0414 0.01054 0.00355 -0.1099 0.2668 1.0000
4.500 1.0633 0.01119 0.00394 -0.1091 0.2275 1.0000
4.750 1.0862 0.01173 0.00430 -0.1084 0.1993 1.0000
5.000 1.1081 0.01236 0.00469 -0.1076 0.1586 1.0000
5.250 1.1229 0.01375 0.00557 -0.1058 0.0679 1.0000
5.500 1.1451 0.01432 0.00605 -0.1050 0.0504 1.0000
5.750 1.1685 0.01474 0.00644 -0.1044 0.0397 1.0000
6.000 1.1897 0.01537 0.00695 -0.1035 0.0164 1.0000
6.250 1.2133 0.01575 0.00740 -0.1028 0.0128 1.0000
6.500 1.2365 0.01614 0.00786 -0.1022 0.0115 1.0000
6.750 1.2590 0.01660 0.00841 -0.1014 0.0102 1.0000
7.000 1.2793 0.01725 0.00917 -0.1002 0.0088 1.0000
7.250 1.3012 0.01772 0.00969 -0.0994 0.0081 1.0000
7.500 1.3219 0.01827 0.01034 -0.0984 0.0075 1.0000
7.750 1.3416 0.01889 0.01104 -0.0972 0.0069 1.0000
8.000 1.3599 0.01960 0.01182 -0.0958 0.0065 1.0000
8.250 1.3744 0.02058 0.01290 -0.0940 0.0060 1.0000
8.500 1.3924 0.02121 0.01359 -0.0926 0.0055 1.0000
8.750 1.4066 0.02207 0.01454 -0.0907 0.0052 1.0000
9.000 1.4171 0.02301 0.01558 -0.0882 0.0049 1.0000
9.250 1.4257 0.02404 0.01669 -0.0855 0.0047 1.0000
9.500 1.4330 0.02517 0.01791 -0.0829 0.0045 1.0000
9.750 1.4387 0.02647 0.01930 -0.0803 0.0044 1.0000
10.000 1.4422 0.02801 0.02093 -0.0778 0.0042 1.0000
10.250 1.4421 0.02999 0.02301 -0.0754 0.0041 1.0000
10.500 1.4371 0.03259 0.02572 -0.0731 0.0040 1.0000
10.750 1.4377 0.03490 0.02814 -0.0716 0.0040 1.0000
11.000 1.4376 0.03741 0.03077 -0.0703 0.0039 1.0000
11.250 1.4374 0.04005 0.03351 -0.0692 0.0038 1.0000
11.500 1.4373 0.04275 0.03633 -0.0683 0.0037 1.0000
11.750 1.4372 0.04555 0.03923 -0.0675 0.0035 1.0000
12.000 1.4370 0.04841 0.04220 -0.0669 0.0033 1.0000
12.250 1.4361 0.05139 0.04531 -0.0664 0.0032 1.0000
12.500 1.4347 0.05448 0.04849 -0.0660 0.0031 1.0000
12.750 1.4326 0.05764 0.05175 -0.0655 0.0030 1.0000
13.000 1.4309 0.06082 0.05502 -0.0652 0.0030 1.0000
13.250 1.4292 0.06404 0.05834 -0.0649 0.0029 1.0000
13.500 1.4274 0.06734 0.06174 -0.0648 0.0028 1.0000
13.750 1.4256 0.07071 0.06521 -0.0648 0.0028 1.0000
14.000 1.4236 0.07421 0.06880 -0.0650 0.0027 1.0000
14.250 1.4214 0.07775 0.07244 -0.0651 0.0027 1.0000
14.500 1.4185 0.08142 0.07621 -0.0654 0.0027 1.0000
14.750 1.4155 0.08510 0.07999 -0.0656 0.0026 1.0000
15.000 1.4115 0.08886 0.08385 -0.0656 0.0026 1.0000
15.250 1.4083 0.09267 0.08779 -0.0657 0.0025 1.0000
15.500 1.4047 0.09664 0.09191 -0.0660 0.0025 1.0000
15.750 1.4002 0.10084 0.09626 -0.0665 0.0025 1.0000
16.000 1.3945 0.10539 0.10097 -0.0674 0.0024 1.0000
16.250 1.3876 0.11030 0.10604 -0.0686 0.0024 1.0000
16.500 1.3795 0.11553 0.11144 -0.0704 0.0024 1.0000
16.750 1.3705 0.12107 0.11714 -0.0725 0.0024 1.0000
17.000 1.3613 0.12684 0.12306 -0.0751 0.0024 1.0000
17.250 1.3514 0.13296 0.12935 -0.0780 0.0023 1.0000
17.500 1.3417 0.13922 0.13576 -0.0813 0.0023 1.0000
17.750 1.3312 0.14588 0.14257 -0.0850 0.0023 1.0000
18.000 1.3213 0.15257 0.14941 -0.0889 0.0024 1.0000
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