GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.88 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe391-il-1000000-n5.txt Download as CSV file: xf-goe391-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4158 0.10011 0.09847 -0.0201 1.0000 0.0040
-8.500 -0.4148 0.09742 0.09580 -0.0201 1.0000 0.0039
-8.250 -0.4154 0.09482 0.09323 -0.0198 1.0000 0.0040
-8.000 -0.4131 0.09174 0.09016 -0.0207 0.9997 0.0047
-7.500 -0.3916 0.08271 0.08114 -0.0298 0.9945 0.0027
-7.250 -0.2930 0.05793 0.05646 -0.0419 0.9879 0.0029
-7.000 -0.2841 0.05299 0.05151 -0.0471 0.9836 0.0029
-6.750 -0.2705 0.04780 0.04631 -0.0533 0.9806 0.0031
-6.500 -0.2514 0.04277 0.04124 -0.0595 0.9787 0.0031
-6.250 -0.2822 0.05723 0.05553 -0.0642 0.9796 0.0027
-6.000 -0.2505 0.05095 0.04915 -0.0720 0.9779 0.0030
-5.750 -0.2261 0.04750 0.04563 -0.0754 0.9736 0.0032
-5.500 -0.1972 0.04429 0.04233 -0.0792 0.9706 0.0036
-5.250 -0.1643 0.03938 0.03726 -0.0839 0.9677 0.0039
-5.000 -0.1385 0.03487 0.03258 -0.0859 0.9606 0.0040
-4.500 -0.1006 0.01098 0.00662 -0.0842 0.9438 0.0041
-4.250 -0.0743 0.00974 0.00510 -0.0839 0.9392 0.0045
-4.000 -0.0485 0.00911 0.00431 -0.0835 0.9334 0.0049
-3.750 -0.0216 0.00833 0.00334 -0.0833 0.9277 0.0055
-3.500 0.0041 0.00796 0.00290 -0.0828 0.9192 0.0064
-3.250 0.0311 0.00768 0.00254 -0.0826 0.9118 0.0075
-3.000 0.0571 0.00730 0.00206 -0.0821 0.9038 0.0090
-2.750 0.0840 0.00714 0.00190 -0.0819 0.8967 0.0116
-2.500 0.1112 0.00709 0.00188 -0.0817 0.8892 0.0153
-2.250 0.1392 0.00722 0.00201 -0.0817 0.8825 0.0199
-2.000 0.1665 0.00727 0.00202 -0.0816 0.8742 0.0223
-1.750 0.1939 0.00744 0.00215 -0.0814 0.8626 0.0236
-1.500 0.2203 0.00747 0.00212 -0.0811 0.8484 0.0240
-1.250 0.2451 0.00712 0.00168 -0.0804 0.8338 0.0252
-1.000 0.2706 0.00688 0.00137 -0.0799 0.8224 0.0261
-0.750 0.2965 0.00674 0.00117 -0.0795 0.8113 0.0262
-0.500 0.3223 0.00664 0.00101 -0.0790 0.7977 0.0260
-0.250 0.3477 0.00658 0.00086 -0.0784 0.7800 0.0259
0.000 0.3708 0.00664 0.00074 -0.0773 0.7365 0.0258
0.250 0.3888 0.00703 0.00070 -0.0752 0.6371 0.0259
0.500 0.4103 0.00732 0.00070 -0.0739 0.5695 0.0263
0.750 0.4340 0.00749 0.00067 -0.0731 0.5230 0.0280
1.000 0.4568 0.00777 0.00071 -0.0721 0.4580 0.0316
1.250 0.4768 0.00838 0.00086 -0.0708 0.3409 0.0352
1.750 0.5257 0.00850 0.00106 -0.0697 0.2827 0.1742
2.250 0.6035 0.00757 0.00156 -0.0762 0.1537 1.0000
2.500 0.6271 0.00777 0.00169 -0.0753 0.1359 1.0000
2.750 0.6486 0.00819 0.00187 -0.0742 0.0816 1.0000
3.000 0.6707 0.00857 0.00207 -0.0731 0.0429 1.0000
3.250 0.6945 0.00877 0.00225 -0.0723 0.0361 1.0000
3.500 0.7188 0.00893 0.00240 -0.0716 0.0330 1.0000
3.750 0.7431 0.00910 0.00258 -0.0709 0.0313 1.0000
4.000 0.7670 0.00931 0.00280 -0.0702 0.0290 1.0000
4.250 0.7910 0.00953 0.00304 -0.0694 0.0278 1.0000
4.500 0.8148 0.00977 0.00330 -0.0686 0.0264 1.0000
4.750 0.8380 0.01009 0.00367 -0.0678 0.0241 1.0000
5.250 0.8868 0.01042 0.00405 -0.0666 0.0229 1.0000
5.500 0.9115 0.01057 0.00421 -0.0661 0.0215 1.0000
5.750 0.9357 0.01077 0.00442 -0.0655 0.0171 1.0000
6.000 0.9582 0.01117 0.00471 -0.0646 0.0087 1.0000
6.250 0.9811 0.01154 0.00512 -0.0637 0.0063 1.0000
6.500 1.0032 0.01202 0.00565 -0.0627 0.0049 1.0000
6.750 1.0259 0.01240 0.00610 -0.0618 0.0043 1.0000
7.000 1.0483 0.01284 0.00659 -0.0609 0.0038 1.0000
7.250 1.0695 0.01342 0.00723 -0.0598 0.0032 1.0000
7.500 1.0903 0.01407 0.00797 -0.0586 0.0030 1.0000
7.750 1.1117 0.01462 0.00861 -0.0575 0.0027 1.0000
8.000 1.1333 0.01511 0.00917 -0.0566 0.0025 1.0000
8.250 1.1543 0.01569 0.00982 -0.0555 0.0022 1.0000
8.500 1.1743 0.01640 0.01066 -0.0543 0.0021 1.0000
8.750 1.1937 0.01717 0.01152 -0.0530 0.0019 1.0000
9.000 1.2111 0.01821 0.01269 -0.0514 0.0018 1.0000
9.250 1.2270 0.01943 0.01409 -0.0495 0.0017 1.0000
9.500 1.2455 0.02026 0.01504 -0.0482 0.0016 1.0000
9.750 1.2618 0.02139 0.01635 -0.0465 0.0016 1.0000
10.000 1.2772 0.02260 0.01774 -0.0447 0.0014 1.0000
10.250 1.2914 0.02389 0.01922 -0.0427 0.0014 1.0000
10.500 1.3036 0.02538 0.02092 -0.0406 0.0013 1.0000
10.750 1.3125 0.02718 0.02296 -0.0380 0.0013 1.0000
11.000 1.3198 0.02899 0.02500 -0.0353 0.0012 1.0000
11.250 1.3223 0.03093 0.02717 -0.0319 0.0012 1.0000
11.500 1.3273 0.03216 0.02854 -0.0288 0.0011 1.0000
11.750 1.3134 0.03529 0.03200 -0.0237 0.0011 1.0000
12.000 1.3113 0.03715 0.03402 -0.0205 0.0010 1.0000
12.250 1.2953 0.04048 0.03763 -0.0166 0.0011 1.0000
12.500 1.2887 0.04294 0.04024 -0.0142 0.0010 1.0000
12.750 1.2516 0.04913 0.04679 -0.0115 0.0011 1.0000
13.000 1.2266 0.05468 0.05257 -0.0114 0.0011 1.0000
13.250 1.2237 0.05775 0.05571 -0.0121 0.0010 1.0000
13.500 1.1885 0.06698 0.06517 -0.0167 0.0011 1.0000
13.750 1.1642 0.07652 0.07487 -0.0232 0.0010 1.0000
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Polar data table (+)
Polar graphs
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