GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 500,000 Max Cl/Cd: 98.36 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe399-il-500000-n5.txt Download as CSV file: xf-goe399-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3515 0.08857 0.08638 -0.0279 1.0000 0.0063
-8.000 -0.3535 0.08578 0.08363 -0.0279 1.0000 0.0064
-7.750 -0.3603 0.08330 0.08120 -0.0269 1.0000 0.0064
-7.500 -0.3519 0.07957 0.07750 -0.0305 0.9950 0.0066
-7.000 -0.3113 0.06879 0.06669 -0.0460 0.9802 0.0074
-6.500 -0.2694 0.01884 0.01488 -0.0898 0.9506 0.0083
-6.250 -0.2459 0.01562 0.01113 -0.0900 0.9418 0.0092
-6.000 -0.2185 0.01443 0.00970 -0.0902 0.9328 0.0100
-5.750 -0.1908 0.01349 0.00850 -0.0903 0.9217 0.0111
-5.500 -0.1638 0.01266 0.00742 -0.0901 0.9084 0.0122
-5.250 -0.1369 0.01213 0.00679 -0.0899 0.8935 0.0143
-5.000 -0.1096 0.01198 0.00655 -0.0896 0.8770 0.0162
-4.750 -0.0831 0.01167 0.00606 -0.0892 0.8595 0.0183
-4.500 -0.0567 0.01149 0.00576 -0.0888 0.8419 0.0203
-4.250 -0.0300 0.01167 0.00586 -0.0884 0.8239 0.0223
-4.000 -0.0038 0.01156 0.00561 -0.0880 0.8058 0.0246
-3.750 0.0224 0.01144 0.00533 -0.0875 0.7901 0.0267
-3.500 0.0488 0.01130 0.00504 -0.0871 0.7770 0.0279
-3.250 0.0755 0.01128 0.00490 -0.0868 0.7655 0.0286
-2.750 0.1270 0.01021 0.00359 -0.0859 0.7450 0.0330
-2.500 0.1534 0.00996 0.00324 -0.0855 0.7363 0.0343
-2.250 0.1798 0.00972 0.00291 -0.0851 0.7272 0.0353
-2.000 0.2063 0.00950 0.00262 -0.0848 0.7185 0.0362
-1.750 0.2326 0.00932 0.00234 -0.0844 0.7098 0.0369
-1.500 0.2592 0.00914 0.00210 -0.0840 0.7011 0.0375
-1.250 0.2858 0.00899 0.00189 -0.0837 0.6933 0.0381
-1.000 0.3125 0.00889 0.00174 -0.0834 0.6847 0.0390
-0.750 0.3392 0.00880 0.00160 -0.0831 0.6758 0.0397
-0.500 0.3656 0.00867 0.00140 -0.0827 0.6667 0.0416
-0.250 0.3923 0.00857 0.00131 -0.0824 0.6572 0.0454
0.250 0.4454 0.00850 0.00122 -0.0817 0.6338 0.0663
0.500 0.4716 0.00850 0.00120 -0.0813 0.6181 0.0788
0.750 0.4976 0.00851 0.00118 -0.0809 0.5999 0.0906
1.000 0.5232 0.00853 0.00118 -0.0805 0.5784 0.1101
1.250 0.5484 0.00846 0.00122 -0.0800 0.5571 0.1868
1.500 0.5679 0.00758 0.00137 -0.0788 0.5395 0.6104
2.000 0.6513 0.00715 0.00153 -0.0851 0.4886 1.0000
2.250 0.6755 0.00739 0.00162 -0.0844 0.4648 1.0000
2.500 0.7004 0.00758 0.00172 -0.0838 0.4484 1.0000
2.750 0.7255 0.00776 0.00183 -0.0833 0.4351 1.0000
3.000 0.7505 0.00795 0.00196 -0.0827 0.4210 1.0000
3.250 0.7753 0.00815 0.00210 -0.0821 0.4049 1.0000
3.500 0.8003 0.00835 0.00224 -0.0816 0.3907 1.0000
3.750 0.8256 0.00852 0.00239 -0.0811 0.3794 1.0000
4.000 0.8506 0.00871 0.00255 -0.0805 0.3651 1.0000
4.250 0.8754 0.00892 0.00271 -0.0800 0.3477 1.0000
4.500 0.9000 0.00915 0.00291 -0.0794 0.3283 1.0000
4.750 0.9240 0.00944 0.00312 -0.0787 0.3038 1.0000
5.000 0.9467 0.00984 0.00338 -0.0779 0.2692 1.0000
5.250 0.9671 0.01049 0.00377 -0.0768 0.2202 1.0000
5.500 0.9818 0.01174 0.00445 -0.0749 0.1125 1.0000
5.750 1.0011 0.01252 0.00503 -0.0736 0.0677 1.0000
6.000 1.0237 0.01295 0.00542 -0.0728 0.0569 1.0000
6.250 1.0470 0.01329 0.00579 -0.0720 0.0511 1.0000
6.500 1.0695 0.01371 0.00620 -0.0712 0.0440 1.0000
6.750 1.0921 0.01409 0.00660 -0.0704 0.0352 1.0000
7.000 1.1129 0.01466 0.00707 -0.0693 0.0195 1.0000
7.250 1.1335 0.01523 0.00764 -0.0682 0.0138 1.0000
7.500 1.1531 0.01589 0.00836 -0.0669 0.0104 1.0000
7.750 1.1739 0.01640 0.00894 -0.0658 0.0095 1.0000
8.000 1.1935 0.01699 0.00962 -0.0645 0.0087 1.0000
8.250 1.2121 0.01765 0.01038 -0.0631 0.0079 1.0000
8.500 1.2286 0.01847 0.01127 -0.0614 0.0072 1.0000
8.750 1.2438 0.01933 0.01224 -0.0595 0.0067 1.0000
9.000 1.2610 0.01999 0.01297 -0.0580 0.0061 1.0000
9.250 1.2759 0.02078 0.01386 -0.0561 0.0057 1.0000
9.500 1.2885 0.02168 0.01485 -0.0539 0.0054 1.0000
9.750 1.2996 0.02250 0.01574 -0.0514 0.0051 1.0000
10.000 1.3075 0.02348 0.01681 -0.0485 0.0050 1.0000
10.250 1.3144 0.02456 0.01797 -0.0457 0.0048 1.0000
10.500 1.3161 0.02607 0.01958 -0.0425 0.0046 1.0000
10.750 1.3185 0.02765 0.02128 -0.0396 0.0045 1.0000
11.000 1.3255 0.02896 0.02277 -0.0374 0.0043 1.0000
11.250 1.3293 0.03061 0.02456 -0.0352 0.0042 1.0000
11.500 1.3333 0.03234 0.02644 -0.0332 0.0041 1.0000
11.750 1.3362 0.03426 0.02850 -0.0314 0.0040 1.0000
12.000 1.3445 0.03562 0.02997 -0.0303 0.0037 1.0000
12.250 1.3422 0.03832 0.03284 -0.0286 0.0037 1.0000
12.500 1.3471 0.04018 0.03482 -0.0277 0.0035 1.0000
12.750 1.3479 0.04262 0.03739 -0.0269 0.0034 1.0000
13.000 1.3485 0.04515 0.04006 -0.0263 0.0033 1.0000
13.250 1.3487 0.04782 0.04285 -0.0259 0.0032 1.0000
13.500 1.3450 0.05111 0.04630 -0.0257 0.0032 1.0000
13.750 1.3428 0.05427 0.04957 -0.0259 0.0031 1.0000
14.000 1.3367 0.05813 0.05361 -0.0263 0.0031 1.0000
14.250 1.3286 0.06240 0.05802 -0.0271 0.0030 1.0000
14.500 1.3236 0.06640 0.06215 -0.0282 0.0030 1.0000
14.750 1.3113 0.07175 0.06767 -0.0298 0.0029 1.0000
15.000 1.2999 0.07728 0.07338 -0.0317 0.0030 1.0000
15.250 1.2857 0.08353 0.07979 -0.0343 0.0029 1.0000
15.500 1.2720 0.08998 0.08641 -0.0372 0.0029 1.0000
15.750 1.2593 0.09660 0.09320 -0.0403 0.0029 1.0000
16.000 1.2446 0.10381 0.10057 -0.0440 0.0029 1.0000
16.250 1.2299 0.11129 0.10820 -0.0479 0.0029 1.0000
16.500 1.2133 0.11952 0.11659 -0.0524 0.0029 1.0000
16.750 1.1962 0.12831 0.12554 -0.0573 0.0029 1.0000
17.000 1.1822 0.13673 0.13410 -0.0621 0.0029 1.0000
17.250 1.1634 0.14691 0.14445 -0.0679 0.0030 1.0000
17.500 1.1345 0.16105 0.15879 -0.0760 0.0031 1.0000
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Polar data table (+)
Polar graphs
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