GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 200,000 Max Cl/Cd: 58.82 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe390-il-200000-n5.txt Download as CSV file: xf-goe390-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3646 0.03787 0.03187 -0.1495 0.8090 0.0430
-11.500 -0.3657 0.03588 0.02971 -0.1496 0.8008 0.0432
-11.250 -0.3601 0.03441 0.02811 -0.1491 0.7936 0.0435
-11.000 -0.3500 0.03312 0.02671 -0.1487 0.7862 0.0438
-10.750 -0.3375 0.03193 0.02537 -0.1483 0.7798 0.0443
-10.500 -0.3233 0.03077 0.02403 -0.1478 0.7742 0.0448
-10.250 -0.3089 0.02959 0.02270 -0.1472 0.7675 0.0454
-10.000 -0.2934 0.02837 0.02127 -0.1465 0.7610 0.0462
-9.750 -0.2768 0.02712 0.01973 -0.1459 0.7554 0.0470
-9.500 -0.2574 0.02623 0.01872 -0.1452 0.7494 0.0476
-9.250 -0.2359 0.02565 0.01812 -0.1447 0.7432 0.0481
-9.000 -0.2137 0.02506 0.01744 -0.1442 0.7377 0.0487
-8.750 -0.1909 0.02443 0.01667 -0.1437 0.7329 0.0495
-8.500 -0.1691 0.02377 0.01591 -0.1431 0.7266 0.0504
-8.250 -0.1470 0.02304 0.01503 -0.1424 0.7195 0.0515
-8.000 -0.1234 0.02245 0.01430 -0.1419 0.7131 0.0524
-7.750 -0.1000 0.02205 0.01387 -0.1413 0.7054 0.0533
-7.500 -0.0759 0.02164 0.01338 -0.1408 0.6983 0.0546
-7.250 -0.0511 0.02117 0.01274 -0.1403 0.6929 0.0563
-7.000 -0.0266 0.02077 0.01229 -0.1399 0.6876 0.0578
-6.750 -0.0017 0.02047 0.01196 -0.1394 0.6818 0.0593
-6.500 0.0236 0.02010 0.01147 -0.1390 0.6765 0.0614
-6.250 0.0494 0.01975 0.01100 -0.1386 0.6721 0.0633
-6.000 0.0745 0.01945 0.01069 -0.1382 0.6670 0.0652
-5.750 0.0998 0.01914 0.01028 -0.1377 0.6615 0.0677
-5.500 0.1253 0.01883 0.00994 -0.1373 0.6563 0.0698
-5.250 0.1518 0.01858 0.00958 -0.1371 0.6517 0.0726
-5.000 0.1770 0.01831 0.00927 -0.1366 0.6467 0.0753
-4.750 0.2023 0.01804 0.00901 -0.1362 0.6416 0.0780
-4.500 0.2285 0.01783 0.00869 -0.1358 0.6366 0.0810
-4.250 0.2544 0.01754 0.00838 -0.1355 0.6320 0.0837
-4.000 0.2800 0.01734 0.00816 -0.1351 0.6269 0.0870
-3.750 0.3050 0.01711 0.00796 -0.1346 0.6212 0.0903
-3.500 0.3310 0.01694 0.00775 -0.1342 0.6160 0.0944
-3.250 0.3576 0.01678 0.00757 -0.1340 0.6114 0.0987
-3.000 0.3834 0.01667 0.00746 -0.1336 0.6065 0.1038
-2.750 0.4088 0.01657 0.00742 -0.1331 0.6009 0.1091
-2.500 0.4349 0.01649 0.00733 -0.1328 0.5953 0.1153
-2.250 0.4618 0.01644 0.00722 -0.1325 0.5903 0.1232
-2.000 0.4868 0.01640 0.00722 -0.1319 0.5842 0.1327
-1.750 0.5123 0.01637 0.00718 -0.1314 0.5780 0.1431
-1.500 0.5382 0.01633 0.00711 -0.1310 0.5725 0.1532
-1.250 0.5639 0.01630 0.00707 -0.1306 0.5672 0.1628
-1.000 0.5886 0.01629 0.00707 -0.1300 0.5607 0.1720
-0.750 0.6135 0.01625 0.00703 -0.1295 0.5544 0.1809
-0.500 0.6387 0.01626 0.00699 -0.1290 0.5485 0.1893
-0.250 0.6625 0.01625 0.00704 -0.1282 0.5413 0.1992
0.000 0.6866 0.01625 0.00704 -0.1276 0.5345 0.2099
0.250 0.7110 0.01628 0.00707 -0.1270 0.5285 0.2242
0.500 0.7345 0.01630 0.00716 -0.1262 0.5215 0.2414
1.000 0.7810 0.01635 0.00729 -0.1247 0.5083 0.2913
1.250 0.8033 0.01636 0.00741 -0.1239 0.5010 0.3307
1.500 0.8253 0.01633 0.00752 -0.1230 0.4946 0.3896
1.750 0.8470 0.01627 0.00773 -0.1220 0.4886 0.4773
2.000 0.8678 0.01626 0.00793 -0.1208 0.4823 0.5622
2.250 0.8868 0.01622 0.00809 -0.1192 0.4765 0.6423
2.500 0.9025 0.01602 0.00836 -0.1164 0.4712 0.8168
2.750 0.9399 0.01614 0.00859 -0.1184 0.4648 1.0000
3.000 0.9593 0.01642 0.00876 -0.1170 0.4597 1.0000
3.250 0.9796 0.01671 0.00893 -0.1158 0.4550 1.0000
3.500 0.9994 0.01701 0.00919 -0.1146 0.4500 1.0000
3.750 1.0192 0.01733 0.00945 -0.1134 0.4450 1.0000
4.000 1.0394 0.01767 0.00969 -0.1123 0.4404 1.0000
4.250 1.0602 0.01803 0.00994 -0.1113 0.4363 1.0000
4.500 1.0798 0.01839 0.01030 -0.1102 0.4318 1.0000
4.750 1.0994 0.01877 0.01064 -0.1092 0.4272 1.0000
5.000 1.1190 0.01917 0.01098 -0.1081 0.4229 1.0000
5.250 1.1392 0.01959 0.01129 -0.1072 0.4189 1.0000
5.500 1.1585 0.02002 0.01172 -0.1062 0.4149 1.0000
5.750 1.1769 0.02047 0.01218 -0.1050 0.4106 1.0000
6.000 1.1952 0.02095 0.01263 -0.1040 0.4064 1.0000
6.250 1.2142 0.02143 0.01305 -0.1030 0.4026 1.0000
6.500 1.2349 0.02190 0.01342 -0.1023 0.3991 1.0000
6.750 1.2515 0.02246 0.01403 -0.1011 0.3955 1.0000
7.000 1.2684 0.02303 0.01464 -0.1000 0.3916 1.0000
7.250 1.2851 0.02363 0.01523 -0.0989 0.3877 1.0000
7.500 1.3027 0.02421 0.01577 -0.0979 0.3840 1.0000
7.750 1.3219 0.02476 0.01625 -0.0971 0.3807 1.0000
8.000 1.3368 0.02548 0.01703 -0.0959 0.3772 1.0000
8.250 1.3511 0.02625 0.01785 -0.0947 0.3733 1.0000
8.500 1.3656 0.02702 0.01863 -0.0936 0.3693 1.0000
8.750 1.3810 0.02775 0.01934 -0.0926 0.3656 1.0000
9.000 1.3980 0.02843 0.01996 -0.0917 0.3624 1.0000
9.250 1.4105 0.02938 0.02099 -0.0906 0.3587 1.0000
9.500 1.4220 0.03039 0.02208 -0.0893 0.3546 1.0000
9.750 1.4341 0.03138 0.02308 -0.0882 0.3505 1.0000
10.000 1.4472 0.03231 0.02399 -0.0872 0.3468 1.0000
10.250 1.4609 0.03323 0.02490 -0.0862 0.3434 1.0000
10.500 1.4701 0.03450 0.02628 -0.0851 0.3393 1.0000
10.750 1.4793 0.03579 0.02762 -0.0839 0.3351 1.0000
11.000 1.4896 0.03699 0.02884 -0.0829 0.3311 1.0000
11.250 1.5015 0.03809 0.02989 -0.0820 0.3274 1.0000
11.500 1.5087 0.03964 0.03155 -0.0809 0.3231 1.0000
11.750 1.5152 0.04128 0.03326 -0.0799 0.3186 1.0000
12.000 1.5234 0.04278 0.03477 -0.0789 0.3145 1.0000
12.250 1.5333 0.04411 0.03609 -0.0781 0.3109 1.0000
12.500 1.5394 0.04590 0.03797 -0.0772 0.3068 1.0000
12.750 1.5436 0.04790 0.04005 -0.0763 0.3022 1.0000
13.000 1.5496 0.04970 0.04187 -0.0755 0.2978 1.0000
13.250 1.5579 0.05125 0.04339 -0.0748 0.2940 1.0000
13.500 1.5597 0.05362 0.04588 -0.0741 0.2894 1.0000
13.750 1.5625 0.05589 0.04821 -0.0734 0.2849 1.0000
14.000 1.5682 0.05783 0.05016 -0.0727 0.2810 1.0000
14.250 1.5756 0.05956 0.05186 -0.0722 0.2776 1.0000
14.500 1.5753 0.06228 0.05472 -0.0716 0.2734 1.0000
14.750 1.5763 0.06484 0.05735 -0.0711 0.2692 1.0000
15.000 1.5809 0.06697 0.05948 -0.0706 0.2654 1.0000
15.250 1.5884 0.06873 0.06122 -0.0702 0.2620 1.0000
15.500 1.5836 0.07209 0.06473 -0.0698 0.2578 1.0000
15.750 1.5830 0.07492 0.06763 -0.0694 0.2538 1.0000
16.000 1.5867 0.07721 0.06994 -0.0691 0.2505 1.0000
16.250 1.5962 0.07876 0.07146 -0.0689 0.2477 1.0000
16.500 1.5931 0.08198 0.07479 -0.0687 0.2444 1.0000
16.750 1.5884 0.08545 0.07839 -0.0686 0.2408 1.0000
17.000 1.5872 0.08843 0.08142 -0.0685 0.2373 1.0000
17.250 1.5940 0.09037 0.08336 -0.0685 0.2344 1.0000
17.500 1.6069 0.09145 0.08440 -0.0683 0.2319 1.0000
17.750 1.5928 0.09626 0.08939 -0.0686 0.2284 1.0000
18.000 1.5850 0.10024 0.09349 -0.0689 0.2251 1.0000
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