GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 500,000 Max Cl/Cd: 106.47 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe407-il-500000.txt Download as CSV file: xf-goe407-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3257 0.10225 0.10001 -0.0259 1.0000 0.0233
-8.750 -0.3264 0.09983 0.09761 -0.0256 1.0000 0.0238
-8.500 -0.3285 0.09742 0.09524 -0.0252 1.0000 0.0244
-8.250 -0.3249 0.09351 0.09134 -0.0312 0.9980 0.0256
-8.000 -0.3131 0.08844 0.08626 -0.0419 0.9928 0.0258
-7.750 -0.2939 0.08235 0.08015 -0.0510 0.9869 0.0259
-7.500 -0.2766 0.07888 0.07668 -0.0510 0.9852 0.0262
-7.250 -0.2516 0.07540 0.07319 -0.0548 0.9833 0.0266
-7.000 -0.2337 0.07199 0.06977 -0.0583 0.9768 0.0270
-6.750 -0.2077 0.06800 0.06575 -0.0643 0.9730 0.0277
-6.500 -0.1843 0.06401 0.06172 -0.0697 0.9673 0.0285
-6.250 -0.1484 0.05771 0.05524 -0.0810 0.9596 0.0307
-6.000 -0.1267 0.05169 0.04905 -0.0859 0.9508 0.0311
-5.750 -0.1055 0.04861 0.04595 -0.0875 0.9452 0.0315
-5.500 -0.0867 0.04633 0.04365 -0.0880 0.9345 0.0319
-5.250 -0.0637 0.04388 0.04113 -0.0893 0.9222 0.0324
-5.000 -0.0345 0.04107 0.03821 -0.0919 0.9081 0.0334
-4.750 0.0113 0.03659 0.03326 -0.0968 0.8911 0.0369
-4.500 0.0424 0.03188 0.02832 -0.1006 0.8710 0.0377
-4.250 0.0750 0.03019 0.02644 -0.1030 0.8459 0.0384
-3.750 0.1185 0.02755 0.02334 -0.1018 0.8008 0.0410
-3.500 0.1335 0.02458 0.01983 -0.0987 0.7843 0.0450
-3.250 0.1521 0.02352 0.01868 -0.0974 0.7693 0.0458
-2.750 0.1919 0.02175 0.01668 -0.0946 0.7447 0.0489
-2.500 0.2105 0.02015 0.01465 -0.0921 0.7348 0.0541
-2.250 0.2316 0.01925 0.01370 -0.0910 0.7249 0.0552
-2.000 0.2535 0.01855 0.01294 -0.0899 0.7156 0.0571
-1.750 0.2811 0.01979 0.01385 -0.0886 0.7071 0.0628
-1.500 0.2973 0.01688 0.01088 -0.0870 0.6988 0.0658
-1.250 0.3204 0.01626 0.01017 -0.0860 0.6909 0.0682
-1.000 0.3469 0.01251 0.00565 -0.0834 0.6840 0.0415
-0.750 0.3725 0.01184 0.00483 -0.0826 0.6765 0.0408
-0.500 0.3980 0.01133 0.00426 -0.0819 0.6692 0.0407
-0.250 0.4231 0.01097 0.00381 -0.0811 0.6620 0.0408
0.000 0.4479 0.01072 0.00354 -0.0803 0.6549 0.0417
0.250 0.4723 0.01049 0.00327 -0.0794 0.6476 0.0425
0.500 0.4967 0.01028 0.00302 -0.0785 0.6413 0.0428
0.750 0.5207 0.01009 0.00283 -0.0775 0.6342 0.0435
1.250 0.5683 0.00980 0.00250 -0.0755 0.6196 0.0460
1.500 0.5925 0.00976 0.00243 -0.0746 0.6120 0.0485
1.750 0.6167 0.00970 0.00239 -0.0736 0.6039 0.0524
2.000 0.6405 0.00966 0.00237 -0.0726 0.5958 0.0669
2.250 0.6606 0.00918 0.00245 -0.0711 0.5870 0.2840
2.500 0.8569 0.00827 0.00300 -0.1095 0.5587 1.0000
2.750 0.8793 0.00837 0.00303 -0.1083 0.5423 1.0000
3.000 0.9012 0.00849 0.00308 -0.1070 0.5217 1.0000
3.250 0.9220 0.00866 0.00313 -0.1054 0.4978 1.0000
3.750 0.9615 0.00919 0.00337 -0.1020 0.4438 1.0000
4.000 0.9815 0.00947 0.00354 -0.1005 0.4239 1.0000
4.250 1.0019 0.00975 0.00372 -0.0989 0.4071 1.0000
4.500 1.0227 0.01001 0.00390 -0.0975 0.3919 1.0000
4.750 1.0437 0.01025 0.00409 -0.0961 0.3785 1.0000
5.000 1.0649 0.01048 0.00429 -0.0948 0.3674 1.0000
5.250 1.0854 0.01074 0.00450 -0.0933 0.3572 1.0000
5.500 1.1067 0.01096 0.00469 -0.0920 0.3470 1.0000
5.750 1.1274 0.01119 0.00491 -0.0906 0.3372 1.0000
6.000 1.1473 0.01146 0.00514 -0.0891 0.3276 1.0000
6.250 1.1686 0.01166 0.00536 -0.0878 0.3194 1.0000
6.500 1.1878 0.01196 0.00561 -0.0861 0.3107 1.0000
6.750 1.2088 0.01215 0.00584 -0.0848 0.3024 1.0000
7.000 1.2278 0.01243 0.00610 -0.0831 0.2942 1.0000
7.250 1.2471 0.01268 0.00634 -0.0815 0.2828 1.0000
7.500 1.2662 0.01294 0.00659 -0.0799 0.2718 1.0000
7.750 1.2840 0.01324 0.00688 -0.0780 0.2601 1.0000
8.000 1.3009 0.01357 0.00718 -0.0760 0.2487 1.0000
8.250 1.3175 0.01390 0.00749 -0.0739 0.2353 1.0000
8.500 1.3323 0.01430 0.00783 -0.0715 0.2162 1.0000
8.750 1.3427 0.01480 0.00823 -0.0683 0.1922 1.0000
9.000 1.3460 0.01553 0.00875 -0.0638 0.1540 1.0000
9.250 1.3492 0.01631 0.00937 -0.0594 0.1316 1.0000
9.500 1.3564 0.01696 0.00998 -0.0558 0.1213 1.0000
9.750 1.3656 0.01756 0.01057 -0.0527 0.1142 1.0000
10.000 1.3748 0.01818 0.01121 -0.0496 0.1077 1.0000
10.250 1.3870 0.01868 0.01176 -0.0471 0.1033 1.0000
10.500 1.3955 0.01939 0.01246 -0.0441 0.0972 1.0000
10.750 1.4084 0.01990 0.01303 -0.0419 0.0923 1.0000
11.000 1.4198 0.02051 0.01367 -0.0395 0.0866 1.0000
11.250 1.4304 0.02119 0.01437 -0.0372 0.0803 1.0000
11.500 1.4395 0.02198 0.01514 -0.0347 0.0703 1.0000
11.750 1.4422 0.02320 0.01622 -0.0316 0.0512 1.0000
12.000 1.4367 0.02501 0.01788 -0.0278 0.0322 1.0000
12.250 1.4368 0.02658 0.01945 -0.0250 0.0265 1.0000
12.500 1.4378 0.02821 0.02111 -0.0225 0.0238 1.0000
12.750 1.4407 0.02979 0.02279 -0.0204 0.0223 1.0000
13.000 1.4414 0.03165 0.02472 -0.0184 0.0211 1.0000
13.250 1.4395 0.03383 0.02698 -0.0166 0.0200 1.0000
13.500 1.4384 0.03607 0.02932 -0.0150 0.0195 1.0000
13.750 1.4398 0.03816 0.03152 -0.0138 0.0189 1.0000
14.000 1.4385 0.04060 0.03407 -0.0127 0.0184 1.0000
14.250 1.4364 0.04324 0.03680 -0.0118 0.0179 1.0000
14.500 1.4340 0.04597 0.03964 -0.0111 0.0175 1.0000
14.750 1.4273 0.04931 0.04307 -0.0106 0.0169 1.0000
15.000 1.4208 0.05271 0.04658 -0.0103 0.0167 1.0000
15.250 1.4091 0.05685 0.05082 -0.0101 0.0164 1.0000
15.500 1.3958 0.06134 0.05542 -0.0103 0.0161 1.0000
15.750 1.3881 0.06528 0.05946 -0.0106 0.0159 1.0000
16.000 1.3830 0.06898 0.06327 -0.0110 0.0157 1.0000
16.250 1.3760 0.07305 0.06745 -0.0115 0.0156 1.0000
16.500 1.3693 0.07719 0.07169 -0.0122 0.0154 1.0000
16.750 1.3633 0.08128 0.07589 -0.0131 0.0151 1.0000
17.000 1.3569 0.08548 0.08019 -0.0140 0.0149 1.0000
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