GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 200,000 Max Cl/Cd: 74.61 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe593-il-200000.txt Download as CSV file: xf-goe593-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3495 0.10626 0.10268 -0.0395 1.0000 0.0601
-9.750 -0.3759 0.10323 0.09976 -0.0426 1.0000 0.0612
-9.500 -0.3975 0.10040 0.09703 -0.0435 1.0000 0.0614
-9.250 -0.3927 0.09647 0.09312 -0.0403 1.0000 0.0622
-9.000 -0.3878 0.09465 0.09133 -0.0371 1.0000 0.0630
-8.750 -0.3875 0.09318 0.08989 -0.0343 1.0000 0.0641
-8.500 -0.3935 0.09171 0.08848 -0.0319 1.0000 0.0656
-8.250 -0.3314 0.07530 0.07233 -0.0470 0.9885 0.0733
-8.000 -0.3012 0.07273 0.06973 -0.0459 0.9862 0.0751
-7.750 -0.2872 0.06870 0.06569 -0.0489 0.9823 0.0777
-7.500 -0.4098 0.07226 0.06906 -0.0536 0.9827 0.0741
-7.250 -0.3891 0.06968 0.06648 -0.0547 0.9771 0.0759
-7.000 -0.3647 0.06464 0.06132 -0.0618 0.9722 0.0806
-6.750 -0.3584 0.05599 0.05228 -0.0703 0.9611 0.0862
-6.500 -0.3676 0.03984 0.03496 -0.0732 0.9497 0.0626
-6.250 -0.3393 0.03533 0.03014 -0.0751 0.9465 0.0587
-6.000 -0.3256 0.03086 0.02512 -0.0738 0.9378 0.0569
-5.750 -0.2956 0.02783 0.02157 -0.0749 0.9339 0.0582
-5.500 -0.2603 0.02544 0.01867 -0.0765 0.9315 0.0597
-5.250 -0.2395 0.02403 0.01691 -0.0751 0.9227 0.0607
-5.000 -0.2046 0.02217 0.01478 -0.0766 0.9195 0.0629
-4.750 -0.1649 0.02099 0.01354 -0.0790 0.9174 0.0656
-4.500 -0.1388 0.02016 0.01259 -0.0785 0.9100 0.0676
-4.250 -0.1024 0.01931 0.01159 -0.0799 0.9060 0.0710
-4.000 -0.0623 0.01812 0.01036 -0.0822 0.9037 0.0748
-3.750 -0.0190 0.01728 0.00954 -0.0850 0.9019 0.0798
-3.500 0.0076 0.01681 0.00900 -0.0846 0.8941 0.0849
-3.250 0.0440 0.01609 0.00835 -0.0861 0.8896 0.0941
-3.000 0.0846 0.01532 0.00762 -0.0884 0.8866 0.1110
-2.750 0.1102 0.01476 0.00720 -0.0878 0.8783 0.1388
-2.500 0.1453 0.01413 0.00667 -0.0890 0.8725 0.1749
-2.250 0.1796 0.01357 0.00625 -0.0901 0.8663 0.2098
-2.000 0.2063 0.01309 0.00596 -0.0897 0.8568 0.2582
-1.750 0.2311 0.01233 0.00567 -0.0890 0.8480 0.3695
-1.500 0.2454 0.01111 0.00561 -0.0858 0.8392 0.6725
-1.250 0.3401 0.01066 0.00568 -0.0975 0.8371 0.9347
-1.000 0.3972 0.01075 0.00564 -0.1030 0.8280 0.9650
-0.750 0.4630 0.01069 0.00539 -0.1103 0.8213 0.9839
-0.500 0.5226 0.01059 0.00517 -0.1169 0.8104 0.9980
-0.250 0.5511 0.01052 0.00499 -0.1170 0.7989 1.0000
0.000 0.5745 0.01047 0.00482 -0.1161 0.7880 1.0000
0.250 0.5948 0.01046 0.00472 -0.1145 0.7756 1.0000
0.500 0.6148 0.01047 0.00465 -0.1128 0.7633 1.0000
0.750 0.6364 0.01050 0.00459 -0.1114 0.7516 1.0000
1.000 0.6594 0.01053 0.00451 -0.1103 0.7401 1.0000
1.250 0.6805 0.01058 0.00448 -0.1087 0.7274 1.0000
1.500 0.7004 0.01066 0.00450 -0.1070 0.7145 1.0000
1.750 0.7213 0.01075 0.00453 -0.1054 0.7017 1.0000
2.000 0.7424 0.01084 0.00454 -0.1039 0.6885 1.0000
2.250 0.7634 0.01094 0.00457 -0.1023 0.6746 1.0000
2.500 0.7841 0.01106 0.00461 -0.1007 0.6601 1.0000
2.750 0.8042 0.01118 0.00466 -0.0989 0.6448 1.0000
3.000 0.8238 0.01132 0.00473 -0.0971 0.6289 1.0000
3.250 0.8428 0.01146 0.00482 -0.0951 0.6117 1.0000
3.500 0.8612 0.01162 0.00493 -0.0931 0.5931 1.0000
3.750 0.8791 0.01180 0.00503 -0.0909 0.5728 1.0000
4.000 0.8968 0.01202 0.00513 -0.0887 0.5518 1.0000
4.250 0.9135 0.01225 0.00529 -0.0864 0.5293 1.0000
4.500 0.9302 0.01253 0.00546 -0.0840 0.5069 1.0000
4.750 0.9469 0.01285 0.00566 -0.0817 0.4857 1.0000
5.000 0.9637 0.01320 0.00590 -0.0795 0.4655 1.0000
5.250 0.9809 0.01358 0.00618 -0.0774 0.4472 1.0000
5.500 0.9986 0.01398 0.00649 -0.0754 0.4308 1.0000
5.750 1.0171 0.01438 0.00682 -0.0737 0.4164 1.0000
6.000 1.0364 0.01481 0.00717 -0.0721 0.4037 1.0000
6.250 1.0561 0.01525 0.00754 -0.0706 0.3921 1.0000
6.500 1.0745 0.01564 0.00790 -0.0689 0.3798 1.0000
6.750 1.0926 0.01601 0.00827 -0.0671 0.3680 1.0000
7.000 1.1121 0.01644 0.00867 -0.0656 0.3581 1.0000
7.250 1.1311 0.01684 0.00905 -0.0641 0.3485 1.0000
7.500 1.1495 0.01722 0.00947 -0.0624 0.3391 1.0000
7.750 1.1689 0.01768 0.00985 -0.0610 0.3303 1.0000
8.000 1.1844 0.01798 0.01026 -0.0588 0.3208 1.0000
8.250 1.2015 0.01839 0.01067 -0.0570 0.3120 1.0000
8.500 1.2168 0.01874 0.01108 -0.0548 0.3040 1.0000
8.750 1.2338 0.01918 0.01153 -0.0530 0.2967 1.0000
9.000 1.2472 0.01951 0.01196 -0.0505 0.2888 1.0000
9.250 1.2617 0.01995 0.01242 -0.0483 0.2811 1.0000
9.500 1.2741 0.02031 0.01288 -0.0457 0.2729 1.0000
9.750 1.2869 0.02075 0.01337 -0.0433 0.2647 1.0000
10.000 1.2974 0.02119 0.01387 -0.0406 0.2554 1.0000
10.250 1.3071 0.02164 0.01444 -0.0379 0.2447 1.0000
10.500 1.3155 0.02218 0.01505 -0.0351 0.2328 1.0000
10.750 1.3217 0.02282 0.01574 -0.0321 0.2171 1.0000
11.000 1.3250 0.02369 0.01660 -0.0290 0.1958 1.0000
11.250 1.3252 0.02492 0.01774 -0.0259 0.1631 1.0000
11.500 1.3196 0.02675 0.01934 -0.0225 0.1306 1.0000
11.750 1.3137 0.02880 0.02124 -0.0194 0.1128 1.0000
12.000 1.3111 0.03077 0.02315 -0.0168 0.1025 1.0000
12.250 1.3111 0.03265 0.02507 -0.0147 0.0948 1.0000
12.500 1.3062 0.03498 0.02737 -0.0126 0.0893 1.0000
12.750 1.3091 0.03683 0.02933 -0.0111 0.0842 1.0000
13.000 1.3069 0.03916 0.03168 -0.0096 0.0798 1.0000
13.250 1.3041 0.04162 0.03419 -0.0081 0.0760 1.0000
13.500 1.3057 0.04381 0.03649 -0.0071 0.0720 1.0000
13.750 1.3033 0.04643 0.03913 -0.0062 0.0684 1.0000
14.000 1.3010 0.04909 0.04181 -0.0052 0.0653 1.0000
14.250 1.3017 0.05160 0.04447 -0.0046 0.0618 1.0000
14.500 1.3005 0.05435 0.04727 -0.0042 0.0588 1.0000
14.750 1.2992 0.05707 0.04995 -0.0033 0.0556 1.0000
15.000 1.2984 0.05999 0.05305 -0.0033 0.0528 1.0000
15.250 1.2984 0.06281 0.05595 -0.0032 0.0503 1.0000
15.500 1.3008 0.06518 0.05821 -0.0023 0.0472 1.0000
15.750 1.2990 0.06841 0.06165 -0.0026 0.0456 1.0000
16.000 1.2982 0.07156 0.06495 -0.0029 0.0437 1.0000
16.250 1.2982 0.07458 0.06804 -0.0032 0.0418 1.0000
16.500 1.3011 0.07715 0.07058 -0.0032 0.0401 1.0000
16.750 1.3004 0.08036 0.07392 -0.0033 0.0385 1.0000
17.000 1.2967 0.08414 0.07789 -0.0042 0.0373 1.0000
17.250 1.2937 0.08788 0.08177 -0.0052 0.0361 1.0000
17.500 1.2924 0.09136 0.08536 -0.0061 0.0350 1.0000
17.750 1.2928 0.09456 0.08863 -0.0069 0.0341 1.0000
18.000 1.3013 0.09635 0.09035 -0.0061 0.0327 1.0000
18.250 1.2914 0.10141 0.09565 -0.0082 0.0323 1.0000
18.500 1.2813 0.10664 0.10111 -0.0103 0.0318 1.0000
18.750 1.2708 0.11205 0.10674 -0.0128 0.0313 1.0000
19.000 1.2590 0.11781 0.11270 -0.0156 0.0309 1.0000
19.250 1.2460 0.12392 0.11901 -0.0188 0.0304 1.0000
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Polar data table (+)
Polar graphs
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