GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 200,000 Max Cl/Cd: 71.77 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417a-il-200000.txt Download as CSV file: xf-goe417a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2932 0.09229 0.08908 -0.0125 1.0000 0.0232
-7.250 -0.2971 0.09041 0.08723 -0.0110 1.0000 0.0235
-7.000 -0.3029 0.08868 0.08554 -0.0093 1.0000 0.0237
-6.750 -0.3103 0.08711 0.08402 -0.0072 1.0000 0.0238
-6.500 -0.3143 0.08529 0.08222 -0.0060 1.0000 0.0240
-6.250 -0.3156 0.08325 0.08022 -0.0053 1.0000 0.0243
-6.000 -0.3158 0.08120 0.07820 -0.0048 1.0000 0.0245
-5.750 -0.3132 0.07898 0.07600 -0.0051 0.9997 0.0248
-5.500 -0.2800 0.07499 0.07195 -0.0130 0.9946 0.0255
-5.250 -0.2413 0.07249 0.06936 -0.0235 0.9882 0.0257
-5.000 -0.3202 0.08166 0.07839 -0.0108 1.0000 0.0253
-4.500 -0.2269 0.07577 0.07229 -0.0309 0.9910 0.0259
-4.250 -0.2090 0.07107 0.06759 -0.0322 0.9868 0.0262
-4.000 -0.1782 0.06727 0.06377 -0.0368 0.9833 0.0266
-3.750 -0.1492 0.06418 0.06062 -0.0407 0.9770 0.0270
-3.500 -0.1120 0.06105 0.05744 -0.0464 0.9725 0.0277
-3.250 -0.0734 0.05811 0.05443 -0.0519 0.9684 0.0286
-3.000 -0.0382 0.05553 0.05177 -0.0563 0.9616 0.0295
-2.750 0.0364 0.05529 0.05119 -0.0676 0.9577 0.0306
-2.500 0.0626 0.05150 0.04740 -0.0698 0.9529 0.0308
-2.250 0.0822 0.04794 0.04386 -0.0707 0.9464 0.0312
-2.000 0.1168 0.04506 0.04095 -0.0742 0.9429 0.0318
-1.750 0.1496 0.04283 0.03865 -0.0768 0.9371 0.0328
-1.500 0.1840 0.04078 0.03652 -0.0794 0.9307 0.0338
-1.250 0.2285 0.03891 0.03451 -0.0834 0.9276 0.0356
-1.000 0.2793 0.03920 0.03445 -0.0864 0.9206 0.0368
-0.750 0.3001 0.03517 0.03053 -0.0875 0.9150 0.0377
-0.500 0.3379 0.03282 0.02815 -0.0905 0.9118 0.0394
-0.250 0.3676 0.03125 0.02649 -0.0910 0.9027 0.0411
0.000 0.4183 0.03048 0.02548 -0.0941 0.8982 0.0441
0.250 0.4643 0.02832 0.02315 -0.0973 0.8956 0.0452
0.500 0.4845 0.02616 0.02103 -0.0965 0.8847 0.0465
0.750 0.5260 0.02433 0.01914 -0.0992 0.8814 0.0495
1.000 0.5636 0.02486 0.01936 -0.0988 0.8706 0.0545
1.250 0.5996 0.02164 0.01618 -0.1012 0.8655 0.0567
1.500 0.6254 0.02034 0.01486 -0.1006 0.8523 0.0609
1.750 0.6569 0.01948 0.01383 -0.1003 0.8392 0.0683
2.000 0.6926 0.01964 0.01376 -0.1007 0.8239 0.0784
2.250 0.7234 0.01720 0.01139 -0.1018 0.8077 0.0832
2.500 0.7610 0.01627 0.01030 -0.1032 0.7885 0.0945
2.750 0.7939 0.01551 0.00940 -0.1039 0.7644 0.1099
3.000 0.8259 0.01482 0.00854 -0.1046 0.7384 0.1376
3.250 0.8537 0.01425 0.00780 -0.1046 0.7116 0.1766
3.500 0.8787 0.01389 0.00736 -0.1037 0.6867 0.1988
3.750 0.9042 0.01375 0.00706 -0.1026 0.6618 0.2057
4.000 0.9277 0.01366 0.00683 -0.1010 0.6326 0.2033
4.250 0.9518 0.01372 0.00666 -0.0991 0.6014 0.1536
4.500 0.9737 0.01404 0.00668 -0.0966 0.5698 0.0991
4.750 0.9942 0.01429 0.00668 -0.0944 0.5392 0.0789
5.000 1.0144 0.01423 0.00654 -0.0926 0.5018 0.0744
5.250 1.0320 0.01438 0.00655 -0.0903 0.4563 0.0712
5.500 1.0467 0.01471 0.00662 -0.0875 0.3846 0.0705
5.750 1.0595 0.01560 0.00699 -0.0848 0.2910 0.0749
6.000 1.0767 0.01641 0.00745 -0.0831 0.2419 0.0779
6.250 1.0967 0.01701 0.00786 -0.0819 0.2092 0.0814
6.500 1.1140 0.01770 0.00828 -0.0799 0.1599 0.0888
6.750 1.1218 0.01920 0.00903 -0.0764 0.0677 0.1027
7.000 1.2257 0.02103 0.01193 -0.0946 0.0503 1.0000
7.250 1.2368 0.02215 0.01308 -0.0915 0.0468 1.0000
7.500 1.2439 0.02380 0.01471 -0.0877 0.0445 1.0000
7.750 1.2589 0.02479 0.01576 -0.0852 0.0432 1.0000
8.000 1.2743 0.02594 0.01695 -0.0829 0.0417 1.0000
8.250 1.2909 0.02717 0.01821 -0.0808 0.0399 1.0000
8.500 1.3079 0.02844 0.01951 -0.0791 0.0378 1.0000
8.750 1.3292 0.03029 0.02134 -0.0781 0.0364 1.0000
9.000 1.3589 0.03336 0.02445 -0.0788 0.0353 1.0000
9.250 1.3872 0.03709 0.02837 -0.0791 0.0349 1.0000
9.500 1.4013 0.03869 0.03021 -0.0766 0.0345 1.0000
9.750 1.4122 0.03990 0.03173 -0.0736 0.0338 1.0000
10.000 1.4230 0.04169 0.03381 -0.0707 0.0331 1.0000
10.250 1.4330 0.04447 0.03689 -0.0679 0.0332 1.0000
10.500 1.4395 0.04766 0.04040 -0.0648 0.0334 1.0000
10.750 1.4573 0.05357 0.04649 -0.0642 0.0352 1.0000
11.000 1.3841 0.04562 0.03916 -0.0498 0.0360 1.0000
11.250 1.3377 0.04923 0.04357 -0.0387 0.0403 1.0000
14.000 1.0618 0.15539 0.15185 -0.0701 0.0747 1.0000
14.250 1.0638 0.15905 0.15550 -0.0710 0.0716 1.0000
14.500 1.0756 0.15992 0.15640 -0.0688 0.0696 1.0000
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Polar data table (+)
Polar graphs
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