GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 500,000 Max Cl/Cd: 94.81 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe369-il-500000-n5.txt Download as CSV file: xf-goe369-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 -0.2827 0.09799 0.09585 -0.0182 1.0000 0.0048
-8.000 -0.2781 0.09556 0.09343 -0.0186 1.0000 0.0048
-7.750 -0.2728 0.09291 0.09081 -0.0191 0.9988 0.0051
-7.500 -0.2551 0.08937 0.08727 -0.0232 0.9730 0.0052
-7.250 -0.2176 0.08439 0.08225 -0.0331 0.9410 0.0056
-7.000 -0.1614 0.07868 0.07628 -0.0482 0.8660 0.0067
-6.750 -0.1499 0.07624 0.07360 -0.0503 0.8152 0.0067
-6.500 -0.1386 0.07376 0.07099 -0.0523 0.7889 0.0067
-6.250 -0.1252 0.07112 0.06825 -0.0548 0.7702 0.0067
-6.000 -0.1096 0.06838 0.06544 -0.0575 0.7546 0.0067
-5.750 -0.0923 0.06558 0.06256 -0.0602 0.7411 0.0068
-5.500 -0.0726 0.06264 0.05955 -0.0633 0.7292 0.0068
-5.250 -0.0503 0.05960 0.05643 -0.0667 0.7186 0.0068
-5.000 -0.0262 0.05654 0.05327 -0.0701 0.7095 0.0068
-4.750 -0.0010 0.05346 0.05009 -0.0731 0.7006 0.0068
-4.500 0.0199 0.04994 0.04651 -0.0750 0.6927 0.0069
-4.250 0.0347 0.04708 0.04361 -0.0755 0.6849 0.0072
-4.000 0.0595 0.04447 0.04091 -0.0777 0.6777 0.0075
-3.750 0.0861 0.04195 0.03829 -0.0797 0.6711 0.0082
-3.500 0.1181 0.03961 0.03582 -0.0819 0.6647 0.0092
-3.250 0.1492 0.03723 0.03329 -0.0836 0.6584 0.0094
-3.000 0.1800 0.03491 0.03081 -0.0850 0.6523 0.0095
-2.750 0.2096 0.03268 0.02839 -0.0859 0.6454 0.0095
-2.500 0.2385 0.03055 0.02609 -0.0865 0.6384 0.0095
-2.250 0.2674 0.02849 0.02383 -0.0868 0.6307 0.0096
-2.000 0.2960 0.02654 0.02168 -0.0869 0.6234 0.0096
-1.750 0.3243 0.02471 0.01964 -0.0869 0.6159 0.0096
-1.500 0.3485 0.02199 0.01679 -0.0875 0.6098 0.0100
-1.250 0.3739 0.02056 0.01525 -0.0877 0.6040 0.0105
-1.000 0.4011 0.01934 0.01384 -0.0876 0.5988 0.0115
-0.750 0.4294 0.01812 0.01245 -0.0873 0.5928 0.0120
-0.500 0.4576 0.01712 0.01125 -0.0868 0.5864 0.0126
-0.250 0.4864 0.01646 0.01040 -0.0861 0.5794 0.0132
0.000 0.5141 0.01573 0.00945 -0.0856 0.5722 0.0133
0.250 0.5416 0.01496 0.00850 -0.0852 0.5649 0.0134
0.500 0.5688 0.01424 0.00760 -0.0848 0.5578 0.0134
0.750 0.5961 0.01355 0.00674 -0.0844 0.5503 0.0135
1.000 0.6231 0.01291 0.00595 -0.0840 0.5424 0.0135
1.250 0.6502 0.01229 0.00521 -0.0836 0.5332 0.0135
1.500 0.6769 0.01138 0.00425 -0.0832 0.5241 0.0133
1.750 0.7030 0.01064 0.00344 -0.0827 0.5139 0.0144
2.000 0.7284 0.01028 0.00311 -0.0825 0.4993 0.0250
2.250 0.7547 0.01015 0.00287 -0.0819 0.4795 0.0177
2.500 0.7799 0.01002 0.00261 -0.0812 0.4541 0.0158
2.750 0.8051 0.01007 0.00251 -0.0806 0.4257 0.0146
3.000 0.8302 0.01015 0.00247 -0.0801 0.3992 0.0142
3.250 0.8550 0.01027 0.00246 -0.0796 0.3716 0.0143
3.500 0.8799 0.01041 0.00247 -0.0791 0.3474 0.0152
3.750 0.9049 0.01061 0.00255 -0.0786 0.3259 0.0180
4.000 0.9298 0.01087 0.00269 -0.0782 0.3039 0.0193
4.250 0.9547 0.01113 0.00284 -0.0777 0.2823 0.0198
4.500 0.9795 0.01141 0.00301 -0.0772 0.2602 0.0212
4.750 1.0035 0.01177 0.00324 -0.0767 0.2296 0.0281
5.000 1.0325 0.01089 0.00381 -0.0779 0.1894 1.0000
5.250 1.0558 0.01135 0.00412 -0.0773 0.1673 1.0000
5.500 1.0797 0.01172 0.00440 -0.0767 0.1537 1.0000
5.750 1.1040 0.01203 0.00467 -0.0762 0.1452 1.0000
6.000 1.1273 0.01244 0.00498 -0.0756 0.1276 1.0000
6.250 1.1483 0.01310 0.00542 -0.0748 0.0946 1.0000
6.500 1.1701 0.01365 0.00582 -0.0740 0.0752 1.0000
6.750 1.1884 0.01457 0.00643 -0.0728 0.0393 1.0000
7.000 1.2044 0.01574 0.00729 -0.0711 0.0086 1.0000
7.250 1.2277 0.01607 0.00762 -0.0705 0.0057 1.0000
7.500 1.2508 0.01641 0.00803 -0.0699 0.0048 1.0000
7.750 1.2734 0.01679 0.00845 -0.0692 0.0040 1.0000
8.000 1.2954 0.01722 0.00895 -0.0684 0.0038 1.0000
8.250 1.3169 0.01769 0.00949 -0.0675 0.0036 1.0000
8.500 1.3377 0.01819 0.01010 -0.0665 0.0034 1.0000
8.750 1.3578 0.01876 0.01077 -0.0654 0.0032 1.0000
9.000 1.3772 0.01935 0.01145 -0.0643 0.0031 1.0000
9.250 1.3955 0.02002 0.01223 -0.0630 0.0030 1.0000
9.500 1.4129 0.02072 0.01305 -0.0616 0.0030 1.0000
9.750 1.4293 0.02147 0.01393 -0.0600 0.0029 1.0000
10.000 1.4444 0.02227 0.01486 -0.0584 0.0029 1.0000
10.250 1.4569 0.02315 0.01588 -0.0563 0.0028 1.0000
10.500 1.4659 0.02411 0.01697 -0.0537 0.0027 1.0000
10.750 1.4706 0.02537 0.01838 -0.0508 0.0024 1.0000
11.000 1.4773 0.02651 0.01967 -0.0483 0.0024 1.0000
11.250 1.4785 0.02812 0.02144 -0.0456 0.0022 1.0000
11.500 1.4775 0.03004 0.02350 -0.0432 0.0021 1.0000
11.750 1.4780 0.03198 0.02558 -0.0413 0.0021 1.0000
12.000 1.4729 0.03462 0.02837 -0.0397 0.0021 1.0000
12.250 1.4702 0.03725 0.03114 -0.0387 0.0020 1.0000
12.500 1.4632 0.04054 0.03458 -0.0381 0.0020 1.0000
12.750 1.4546 0.04424 0.03843 -0.0379 0.0020 1.0000
13.000 1.4458 0.04817 0.04249 -0.0380 0.0019 1.0000
13.250 1.4230 0.05405 0.04854 -0.0388 0.0018 1.0000
13.500 1.4124 0.05863 0.05325 -0.0396 0.0018 1.0000
13.750 1.4083 0.06251 0.05725 -0.0405 0.0019 1.0000
14.000 1.3924 0.06815 0.06303 -0.0420 0.0018 1.0000
14.250 1.3788 0.07380 0.06881 -0.0437 0.0018 1.0000
14.500 1.3665 0.07942 0.07454 -0.0456 0.0018 1.0000
14.750 1.3616 0.08438 0.07967 -0.0477 0.0018 1.0000
15.000 1.3514 0.09021 0.08563 -0.0501 0.0018 1.0000
15.250 1.3447 0.09585 0.09143 -0.0528 0.0017 1.0000
15.500 1.3351 0.10204 0.09775 -0.0557 0.0017 1.0000
15.750 1.3261 0.10839 0.10423 -0.0588 0.0017 1.0000
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Polar data table (+)
Polar graphs
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