GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 500,000 Max Cl/Cd: 88.88 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe613-il-500000-n5.txt Download as CSV file: xf-goe613-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3511 0.10738 0.10510 -0.0340 1.0000 0.0102
-10.250 -0.3524 0.10440 0.10215 -0.0340 1.0000 0.0108
-10.000 -0.3528 0.09945 0.09723 -0.0365 0.9993 0.0114
-9.750 -0.3530 0.09219 0.08997 -0.0420 0.9971 0.0121
-9.250 -0.3299 0.08519 0.08297 -0.0490 0.9915 0.0126
-9.000 -0.3156 0.08220 0.07998 -0.0525 0.9882 0.0131
-8.750 -0.3040 0.07828 0.07606 -0.0569 0.9844 0.0138
-8.500 -0.3018 0.07199 0.06979 -0.0638 0.9766 0.0147
-8.250 -0.3133 0.05750 0.05523 -0.0820 0.9616 0.0159
-8.000 -0.2939 0.05407 0.05173 -0.0866 0.9549 0.0162
-7.750 -0.2678 0.04995 0.04749 -0.0927 0.9511 0.0167
-7.250 -0.2524 0.02930 0.02582 -0.1027 0.9306 0.0210
-7.000 -0.2236 0.02877 0.02519 -0.1039 0.9250 0.0214
-6.750 -0.1968 0.02771 0.02401 -0.1047 0.9193 0.0219
-6.500 -0.1730 0.02663 0.02279 -0.1048 0.9121 0.0225
-6.250 -0.1499 0.02439 0.02026 -0.1050 0.9056 0.0236
-6.000 -0.1328 0.02153 0.01700 -0.1037 0.8974 0.0249
-5.750 -0.1103 0.01944 0.01451 -0.1031 0.8906 0.0260
-5.500 -0.0884 0.01820 0.01300 -0.1021 0.8823 0.0265
-5.250 -0.0631 0.01734 0.01192 -0.1017 0.8756 0.0267
-5.000 -0.0426 0.01559 0.00994 -0.1007 0.8674 0.0277
-4.750 -0.0172 0.01500 0.00924 -0.1003 0.8596 0.0283
-4.500 0.0076 0.01436 0.00846 -0.0997 0.8503 0.0287
-4.250 0.0328 0.01380 0.00779 -0.0992 0.8415 0.0291
-4.000 0.0583 0.01328 0.00714 -0.0986 0.8306 0.0296
-3.750 0.0832 0.01276 0.00648 -0.0979 0.8162 0.0300
-3.500 0.1080 0.01230 0.00589 -0.0972 0.7994 0.0304
-3.250 0.1329 0.01187 0.00534 -0.0965 0.7838 0.0307
-3.000 0.1580 0.01150 0.00486 -0.0958 0.7712 0.0312
-2.500 0.2081 0.01094 0.00411 -0.0945 0.7459 0.0324
-2.250 0.2329 0.01067 0.00376 -0.0938 0.7333 0.0330
-2.000 0.2574 0.01042 0.00343 -0.0930 0.7204 0.0334
-1.750 0.2820 0.01023 0.00316 -0.0922 0.7071 0.0339
-1.500 0.3064 0.01007 0.00292 -0.0914 0.6926 0.0343
-1.250 0.3310 0.00996 0.00274 -0.0907 0.6775 0.0347
-1.000 0.3545 0.00974 0.00245 -0.0897 0.6597 0.0357
-0.750 0.3780 0.00962 0.00225 -0.0887 0.6391 0.0367
-0.500 0.4008 0.00960 0.00211 -0.0876 0.6099 0.0377
-0.250 0.4223 0.00968 0.00203 -0.0863 0.5744 0.0387
0.000 0.4446 0.00977 0.00198 -0.0851 0.5471 0.0400
0.250 0.4681 0.00984 0.00195 -0.0841 0.5273 0.0419
0.500 0.4921 0.00991 0.00194 -0.0834 0.5112 0.0441
0.750 0.5164 0.00996 0.00192 -0.0826 0.4967 0.0468
1.000 0.5407 0.01000 0.00191 -0.0819 0.4825 0.0529
1.250 0.5649 0.01005 0.00193 -0.0811 0.4671 0.0651
1.500 0.5735 0.00857 0.00209 -0.0779 0.4548 0.6730
1.750 0.6603 0.00827 0.00239 -0.0907 0.4291 0.9913
2.000 0.6973 0.00848 0.00248 -0.0929 0.4113 1.0000
2.250 0.7186 0.00865 0.00255 -0.0916 0.3959 1.0000
2.500 0.7398 0.00884 0.00264 -0.0903 0.3811 1.0000
3.250 0.8041 0.00941 0.00297 -0.0864 0.3415 1.0000
3.500 0.8261 0.00959 0.00310 -0.0852 0.3321 1.0000
4.000 0.8702 0.00995 0.00338 -0.0829 0.3159 1.0000
4.250 0.8918 0.01015 0.00354 -0.0817 0.3085 1.0000
4.500 0.9142 0.01033 0.00370 -0.0807 0.3011 1.0000
4.750 0.9355 0.01056 0.00388 -0.0794 0.2921 1.0000
5.000 0.9572 0.01077 0.00406 -0.0783 0.2809 1.0000
5.250 0.9786 0.01101 0.00425 -0.0771 0.2689 1.0000
5.500 0.9998 0.01126 0.00445 -0.0759 0.2579 1.0000
5.750 1.0205 0.01154 0.00466 -0.0746 0.2439 1.0000
6.000 1.0414 0.01180 0.00488 -0.0734 0.2336 1.0000
6.250 1.0627 0.01205 0.00511 -0.0722 0.2228 1.0000
6.500 1.0825 0.01238 0.00537 -0.0709 0.2071 1.0000
6.750 1.1021 0.01273 0.00565 -0.0694 0.1913 1.0000
7.000 1.1185 0.01327 0.00601 -0.0675 0.1607 1.0000
7.250 1.1275 0.01426 0.00667 -0.0645 0.1099 1.0000
7.750 1.1364 0.01659 0.00848 -0.0566 0.0164 1.0000
8.000 1.1531 0.01702 0.00895 -0.0548 0.0144 1.0000
8.250 1.1701 0.01744 0.00944 -0.0530 0.0135 1.0000
8.500 1.1863 0.01792 0.00998 -0.0512 0.0124 1.0000
8.750 1.2012 0.01848 0.01061 -0.0492 0.0113 1.0000
9.000 1.2142 0.01917 0.01139 -0.0469 0.0105 1.0000
9.250 1.2281 0.01980 0.01209 -0.0449 0.0101 1.0000
9.500 1.2421 0.02043 0.01280 -0.0430 0.0097 1.0000
9.750 1.2556 0.02109 0.01352 -0.0411 0.0091 1.0000
10.000 1.2671 0.02189 0.01440 -0.0389 0.0088 1.0000
10.250 1.2789 0.02267 0.01525 -0.0370 0.0083 1.0000
10.500 1.2891 0.02357 0.01621 -0.0349 0.0080 1.0000
10.750 1.2956 0.02474 0.01746 -0.0326 0.0076 1.0000
11.000 1.2994 0.02613 0.01894 -0.0300 0.0073 1.0000
11.250 1.3065 0.02734 0.02024 -0.0281 0.0072 1.0000
11.500 1.3114 0.02875 0.02175 -0.0260 0.0071 1.0000
11.750 1.3164 0.03023 0.02333 -0.0242 0.0068 1.0000
12.000 1.3201 0.03187 0.02507 -0.0225 0.0067 1.0000
12.250 1.3219 0.03377 0.02708 -0.0209 0.0064 1.0000
12.500 1.3229 0.03583 0.02924 -0.0195 0.0063 1.0000
12.750 1.3231 0.03809 0.03160 -0.0184 0.0061 1.0000
13.000 1.3225 0.04054 0.03415 -0.0175 0.0060 1.0000
13.250 1.3212 0.04319 0.03690 -0.0168 0.0059 1.0000
13.500 1.3214 0.04583 0.03963 -0.0165 0.0057 1.0000
13.750 1.3201 0.04875 0.04264 -0.0164 0.0056 1.0000
14.000 1.3150 0.05227 0.04627 -0.0165 0.0055 1.0000
14.250 1.3088 0.05617 0.05027 -0.0170 0.0054 1.0000
14.500 1.3021 0.06028 0.05449 -0.0179 0.0053 1.0000
14.750 1.2926 0.06491 0.05923 -0.0188 0.0053 1.0000
15.000 1.2853 0.06935 0.06378 -0.0200 0.0051 1.0000
15.250 1.2759 0.07411 0.06864 -0.0212 0.0051 1.0000
15.500 1.2713 0.07833 0.07299 -0.0224 0.0050 1.0000
15.750 1.2642 0.08289 0.07766 -0.0237 0.0050 1.0000
16.000 1.2572 0.08749 0.08235 -0.0251 0.0050 1.0000
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