GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 411 AIRFOIL (goe411-il) Reynolds number: 1,000,000 Max Cl/Cd: 48.68 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe411-il-1000000.txt Download as CSV file: xf-goe411-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 411 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7000 0.08704 0.08492 -0.0438 1.0000 0.0079
-13.250 -0.7131 0.08155 0.07936 -0.0469 1.0000 0.0079
-13.000 -0.7329 0.07559 0.07330 -0.0502 1.0000 0.0079
-12.750 -0.7494 0.07066 0.06826 -0.0525 1.0000 0.0079
-12.500 -0.7714 0.06595 0.06342 -0.0543 1.0000 0.0079
-12.250 -0.7921 0.06193 0.05927 -0.0548 1.0000 0.0079
-12.000 -0.8104 0.05868 0.05589 -0.0541 1.0000 0.0079
-11.750 -0.8219 0.05581 0.05293 -0.0528 1.0000 0.0079
-11.500 -0.8404 0.05330 0.05029 -0.0501 1.0000 0.0079
-11.250 -0.8665 0.05129 0.04811 -0.0453 1.0000 0.0080
-11.000 -0.8840 0.04956 0.04627 -0.0404 1.0000 0.0080
-10.750 -0.9074 0.04833 0.04492 -0.0333 1.0000 0.0080
-10.500 -0.9212 0.04679 0.04328 -0.0275 1.0000 0.0080
-10.250 -0.9356 0.04492 0.04126 -0.0216 1.0000 0.0080
-10.000 -0.9469 0.04324 0.03941 -0.0160 1.0000 0.0080
-9.750 -0.9521 0.04132 0.03735 -0.0113 1.0000 0.0080
-9.500 -0.9606 0.03962 0.03545 -0.0058 1.0000 0.0080
-8.750 -0.9139 0.02658 0.02171 -0.0035 0.9961 0.0073
-8.500 -0.8859 0.02452 0.01946 -0.0043 0.9948 0.0073
-8.250 -0.8573 0.02309 0.01790 -0.0050 0.9931 0.0075
-8.000 -0.8301 0.02106 0.01574 -0.0053 0.9913 0.0074
-7.750 -0.8030 0.01934 0.01394 -0.0056 0.9896 0.0074
-7.500 -0.7738 0.01823 0.01274 -0.0064 0.9876 0.0076
-7.250 -0.7432 0.01744 0.01189 -0.0074 0.9859 0.0079
-7.000 -0.7197 0.01554 0.00992 -0.0074 0.9841 0.0084
-6.750 -0.6934 0.01449 0.00884 -0.0078 0.9819 0.0090
-6.500 -0.6711 0.01386 0.00817 -0.0070 0.9771 0.0094
-6.250 -0.6417 0.01323 0.00750 -0.0077 0.9744 0.0100
-6.000 -0.6107 0.01259 0.00680 -0.0087 0.9725 0.0106
-5.750 -0.5773 0.01218 0.00637 -0.0103 0.9712 0.0115
-5.500 -0.5438 0.01174 0.00590 -0.0117 0.9701 0.0121
-5.250 -0.5241 0.01107 0.00513 -0.0101 0.9645 0.0130
-5.000 -0.4956 0.01050 0.00449 -0.0105 0.9614 0.0147
-4.750 -0.4622 0.01011 0.00405 -0.0119 0.9593 0.0164
-4.500 -0.4263 0.00980 0.00372 -0.0139 0.9576 0.0182
-4.250 -0.3907 0.00944 0.00331 -0.0157 0.9558 0.0252
-4.000 -0.3802 0.00821 0.00270 -0.0126 0.9461 0.1729
-3.750 -0.3505 0.00749 0.00235 -0.0136 0.9421 0.2540
-3.500 -0.3321 0.00695 0.00212 -0.0119 0.9324 0.3293
-3.250 -0.3043 0.00654 0.00192 -0.0122 0.9253 0.3882
-3.000 -0.2783 0.00627 0.00178 -0.0119 0.9159 0.4307
-2.750 -0.2528 0.00606 0.00167 -0.0115 0.9052 0.4652
-2.500 -0.2260 0.00591 0.00157 -0.0114 0.8940 0.4912
-2.250 -0.1994 0.00580 0.00148 -0.0112 0.8816 0.5123
-2.000 -0.1730 0.00573 0.00140 -0.0109 0.8681 0.5256
-1.750 -0.1476 0.00569 0.00133 -0.0104 0.8531 0.5384
-1.500 -0.1232 0.00566 0.00127 -0.0096 0.8345 0.5510
-1.250 -0.0997 0.00564 0.00122 -0.0086 0.8157 0.5660
-1.000 -0.0774 0.00561 0.00118 -0.0074 0.7953 0.5838
-0.750 -0.0556 0.00561 0.00114 -0.0061 0.7717 0.5989
-0.500 -0.0348 0.00562 0.00110 -0.0046 0.7417 0.6141
-0.250 -0.0166 0.00567 0.00107 -0.0024 0.6993 0.6318
0.000 -0.0001 0.00572 0.00105 0.0000 0.6573 0.6579
0.250 0.0167 0.00567 0.00107 0.0024 0.6317 0.6983
0.500 0.0346 0.00561 0.00110 0.0046 0.6140 0.7431
0.750 0.0555 0.00561 0.00114 0.0061 0.5988 0.7722
1.000 0.0773 0.00561 0.00118 0.0075 0.5832 0.7951
1.500 0.1231 0.00566 0.00127 0.0096 0.5506 0.8349
1.750 0.1476 0.00569 0.00133 0.0104 0.5380 0.8524
2.000 0.1730 0.00573 0.00140 0.0109 0.5256 0.8680
2.250 0.1992 0.00580 0.00148 0.0112 0.5110 0.8816
2.500 0.2260 0.00591 0.00157 0.0114 0.4911 0.8940
2.750 0.2528 0.00606 0.00167 0.0115 0.4649 0.9051
3.000 0.2781 0.00627 0.00178 0.0120 0.4302 0.9158
3.250 0.3041 0.00655 0.00192 0.0122 0.3864 0.9253
3.500 0.3320 0.00695 0.00212 0.0119 0.3294 0.9324
3.750 0.3512 0.00743 0.00233 0.0135 0.2629 0.9420
4.000 0.3806 0.00819 0.00270 0.0125 0.1761 0.9461
4.250 0.3910 0.00943 0.00331 0.0156 0.0259 0.9558
4.500 0.4266 0.00980 0.00371 0.0138 0.0183 0.9576
4.750 0.4620 0.01012 0.00407 0.0119 0.0161 0.9593
5.000 0.4956 0.01051 0.00449 0.0105 0.0144 0.9614
5.250 0.5242 0.01107 0.00512 0.0101 0.0130 0.9644
5.500 0.5442 0.01169 0.00584 0.0117 0.0120 0.9701
5.750 0.5776 0.01215 0.00634 0.0102 0.0113 0.9712
6.000 0.6106 0.01259 0.00680 0.0088 0.0102 0.9725
6.250 0.6417 0.01322 0.00748 0.0077 0.0099 0.9744
6.500 0.6718 0.01380 0.00808 0.0068 0.0092 0.9770
6.750 0.6943 0.01446 0.00879 0.0076 0.0088 0.9818
7.000 0.7206 0.01545 0.00983 0.0073 0.0086 0.9840
7.250 0.7408 0.01796 0.01239 0.0078 0.0080 0.9858
7.500 0.7709 0.01902 0.01351 0.0068 0.0079 0.9874
7.750 0.8029 0.01933 0.01393 0.0057 0.0073 0.9895
8.000 0.8303 0.02105 0.01573 0.0053 0.0074 0.9913
8.250 0.8572 0.02325 0.01807 0.0050 0.0075 0.9930
8.500 0.8863 0.02429 0.01923 0.0043 0.0072 0.9948
8.750 0.9133 0.02697 0.02212 0.0037 0.0074 0.9961
9.250 0.9500 0.03703 0.03263 0.0042 0.0080 0.9987
9.500 0.9605 0.03968 0.03551 0.0058 0.0080 1.0000
9.750 0.9550 0.04137 0.03737 0.0108 0.0080 1.0000
10.000 0.9492 0.04326 0.03941 0.0156 0.0080 1.0000
10.250 0.9353 0.04508 0.04141 0.0217 0.0080 1.0000
10.500 0.9258 0.04685 0.04331 0.0267 0.0080 1.0000
10.750 0.8947 0.04789 0.04453 0.0356 0.0079 1.0000
11.000 0.8894 0.04966 0.04635 0.0395 0.0080 1.0000
11.250 0.8670 0.05133 0.04815 0.0453 0.0080 1.0000
11.500 0.8427 0.05331 0.05030 0.0499 0.0079 1.0000
11.750 0.8251 0.05581 0.05292 0.0525 0.0079 1.0000
12.000 0.8048 0.05888 0.05613 0.0542 0.0079 1.0000
12.250 0.7913 0.06211 0.05945 0.0547 0.0079 1.0000
12.500 0.7755 0.06587 0.06332 0.0544 0.0079 1.0000
12.750 0.7567 0.07020 0.06777 0.0530 0.0079 1.0000
13.000 0.7317 0.07585 0.07357 0.0499 0.0079 1.0000
13.250 0.7157 0.08129 0.07910 0.0470 0.0079 1.0000
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