GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 100,000 Max Cl/Cd: 62.02 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417-il-100000.txt Download as CSV file: xf-goe417-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2893 0.10072 0.09616 -0.0211 1.0000 0.0410
-7.250 -0.2983 0.09977 0.09530 -0.0189 1.0000 0.0416
-7.000 -0.3066 0.09879 0.09441 -0.0171 1.0000 0.0420
-6.750 -0.3121 0.09809 0.09379 -0.0171 1.0000 0.0427
-6.500 -0.3144 0.09742 0.09317 -0.0185 1.0000 0.0431
-6.250 -0.3108 0.09709 0.09288 -0.0224 1.0000 0.0435
-6.000 -0.3005 0.09617 0.09195 -0.0270 1.0000 0.0437
-5.750 -0.3085 0.08979 0.08569 -0.0201 1.0000 0.0446
-5.500 -0.3097 0.08618 0.08211 -0.0161 1.0000 0.0459
-5.250 -0.3069 0.08361 0.07958 -0.0152 1.0000 0.0475
-5.000 -0.3010 0.08119 0.07718 -0.0156 1.0000 0.0492
-4.750 -0.2922 0.07873 0.07473 -0.0171 1.0000 0.0510
-4.500 -0.2782 0.07632 0.07231 -0.0199 1.0000 0.0534
-4.250 -0.2252 0.07636 0.07206 -0.0347 1.0000 0.0562
-4.000 -0.2258 0.07119 0.06701 -0.0324 1.0000 0.0570
-3.750 -0.2260 0.06768 0.06359 -0.0293 1.0000 0.0584
-3.500 -0.2102 0.06473 0.06064 -0.0303 0.9986 0.0612
-3.250 -0.1283 0.06158 0.05709 -0.0475 0.9909 0.0707
-3.000 -0.1099 0.05691 0.05253 -0.0479 0.9846 0.0753
-2.750 -0.0449 0.05363 0.04894 -0.0594 0.9758 0.0857
-2.500 -0.0034 0.04997 0.04524 -0.0643 0.9669 0.0953
-2.250 0.0514 0.04641 0.04148 -0.0719 0.9571 0.1083
-2.000 0.1059 0.04366 0.03844 -0.0791 0.9460 0.1296
-1.750 0.1485 0.04068 0.03539 -0.0834 0.9379 0.1466
-1.500 0.1949 0.03858 0.03306 -0.0882 0.9292 0.1739
0.000 0.4692 0.02642 0.01935 -0.1078 0.8773 0.1883
0.250 0.5257 0.02378 0.01596 -0.1104 0.8713 0.1182
0.500 0.5650 0.02239 0.01427 -0.1112 0.8603 0.1075
0.750 0.6078 0.02100 0.01258 -0.1125 0.8511 0.1014
1.000 0.6484 0.01977 0.01132 -0.1138 0.8407 0.1051
1.250 0.6832 0.01880 0.01031 -0.1139 0.8268 0.1068
1.500 0.7170 0.01789 0.00936 -0.1137 0.8119 0.1084
1.750 0.7488 0.01721 0.00860 -0.1132 0.7940 0.1121
2.000 0.7782 0.01664 0.00801 -0.1124 0.7728 0.1205
2.250 0.8094 0.01609 0.00746 -0.1118 0.7514 0.1481
2.500 0.8429 0.01442 0.00707 -0.1120 0.7252 1.0000
2.750 0.8696 0.01443 0.00678 -0.1108 0.6964 1.0000
3.000 0.8958 0.01457 0.00664 -0.1097 0.6666 1.0000
3.250 0.9211 0.01486 0.00663 -0.1086 0.6366 1.0000
3.500 0.9452 0.01524 0.00673 -0.1073 0.6065 1.0000
3.750 0.9683 0.01566 0.00692 -0.1060 0.5777 1.0000
4.000 0.9910 0.01608 0.00720 -0.1048 0.5512 1.0000
4.250 1.0144 0.01652 0.00748 -0.1037 0.5288 1.0000
4.500 1.0379 0.01697 0.00781 -0.1028 0.5089 1.0000
4.750 1.0618 0.01743 0.00817 -0.1019 0.4914 1.0000
5.000 1.0858 0.01792 0.00855 -0.1011 0.4753 1.0000
5.250 1.1097 0.01843 0.00902 -0.1003 0.4598 1.0000
5.500 1.1335 0.01896 0.00950 -0.0995 0.4451 1.0000
5.750 1.1571 0.01952 0.01004 -0.0988 0.4307 1.0000
6.000 1.1806 0.02010 0.01061 -0.0980 0.4164 1.0000
6.250 1.2038 0.02071 0.01127 -0.0971 0.4022 1.0000
6.500 1.2269 0.02136 0.01194 -0.0963 0.3879 1.0000
6.750 1.2497 0.02206 0.01266 -0.0954 0.3734 1.0000
7.000 1.2723 0.02280 0.01343 -0.0945 0.3589 1.0000
7.250 1.2945 0.02358 0.01431 -0.0936 0.3448 1.0000
7.500 1.3165 0.02441 0.01522 -0.0927 0.3313 1.0000
7.750 1.3377 0.02518 0.01608 -0.0916 0.3178 1.0000
8.000 1.3568 0.02567 0.01664 -0.0902 0.3028 1.0000
8.250 1.3740 0.02594 0.01699 -0.0884 0.2869 1.0000
8.500 1.3899 0.02617 0.01733 -0.0865 0.2718 1.0000
8.750 1.4038 0.02632 0.01759 -0.0843 0.2559 1.0000
9.000 1.4169 0.02652 0.01796 -0.0820 0.2402 1.0000
9.250 1.4273 0.02666 0.01838 -0.0792 0.2190 1.0000
9.500 1.4330 0.02702 0.01878 -0.0759 0.1805 1.0000
9.750 1.4299 0.02899 0.02028 -0.0717 0.1052 1.0000
10.000 1.4231 0.03151 0.02232 -0.0674 0.0672 1.0000
10.250 1.4159 0.03394 0.02468 -0.0632 0.0596 1.0000
10.500 1.4126 0.03609 0.02699 -0.0598 0.0548 1.0000
10.750 1.4064 0.03852 0.02958 -0.0565 0.0515 1.0000
11.000 1.3975 0.04131 0.03247 -0.0536 0.0495 1.0000
11.250 1.3884 0.04437 0.03562 -0.0510 0.0480 1.0000
11.500 1.3891 0.04682 0.03822 -0.0491 0.0467 1.0000
11.750 1.3914 0.04933 0.04088 -0.0474 0.0454 1.0000
12.000 1.3968 0.05182 0.04349 -0.0459 0.0441 1.0000
12.250 1.4036 0.05436 0.04615 -0.0445 0.0423 1.0000
12.500 1.4111 0.05702 0.04891 -0.0432 0.0403 1.0000
13.000 1.4667 0.06463 0.05665 -0.0415 0.0373 1.0000
13.250 1.4680 0.06839 0.06071 -0.0404 0.0372 1.0000
13.500 1.4653 0.07254 0.06517 -0.0394 0.0372 1.0000
13.750 1.4602 0.07718 0.07008 -0.0387 0.0373 1.0000
14.000 1.4488 0.08114 0.07435 -0.0383 0.0375 1.0000
14.250 1.4347 0.08536 0.07883 -0.0385 0.0376 1.0000
14.500 1.4186 0.08993 0.08367 -0.0393 0.0378 1.0000
14.750 1.4004 0.09501 0.08902 -0.0411 0.0380 1.0000
15.000 1.3799 0.10075 0.09503 -0.0438 0.0383 1.0000
15.250 1.3572 0.10735 0.10190 -0.0476 0.0387 1.0000
15.500 1.3321 0.11512 0.10994 -0.0527 0.0391 1.0000
15.750 1.3053 0.12423 0.11931 -0.0591 0.0396 1.0000
16.000 1.2703 0.13622 0.13155 -0.0682 0.0404 1.0000
16.250 1.2182 0.15490 0.15046 -0.0827 0.0420 1.0000
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Polar data table (+)
Polar graphs
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