GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.57 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe382-il-1000000.txt Download as CSV file: xf-goe382-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5711 0.04614 0.04304 -0.1151 0.8675 0.0267
-13.500 -0.5976 0.04044 0.03704 -0.1194 0.8537 0.0266
-13.250 -0.6094 0.03713 0.03352 -0.1205 0.8400 0.0266
-13.000 -0.6144 0.03475 0.03094 -0.1203 0.8259 0.0267
-12.750 -0.6146 0.03289 0.02889 -0.1192 0.8111 0.0268
-12.500 -0.6122 0.03139 0.02722 -0.1175 0.7961 0.0268
-12.250 -0.6048 0.03011 0.02580 -0.1160 0.7815 0.0270
-12.000 -0.5923 0.02895 0.02450 -0.1150 0.7665 0.0271
-11.750 -0.5773 0.02793 0.02334 -0.1141 0.7510 0.0272
-11.500 -0.5617 0.02691 0.02217 -0.1132 0.7354 0.0274
-11.250 -0.5450 0.02594 0.02104 -0.1123 0.7204 0.0275
-11.000 -0.5272 0.02497 0.01993 -0.1115 0.7074 0.0277
-10.750 -0.5081 0.02413 0.01895 -0.1108 0.6956 0.0279
-10.500 -0.4880 0.02337 0.01805 -0.1101 0.6845 0.0282
-10.250 -0.4674 0.02257 0.01712 -0.1094 0.6755 0.0284
-10.000 -0.4465 0.02173 0.01613 -0.1088 0.6667 0.0286
-9.750 -0.4248 0.02092 0.01518 -0.1081 0.6592 0.0287
-9.500 -0.4022 0.02016 0.01430 -0.1076 0.6525 0.0289
-9.250 -0.3791 0.01949 0.01350 -0.1071 0.6459 0.0290
-9.000 -0.3551 0.01886 0.01276 -0.1066 0.6409 0.0291
-8.750 -0.3306 0.01825 0.01207 -0.1062 0.6362 0.0293
-8.500 -0.3057 0.01773 0.01146 -0.1059 0.6315 0.0294
-8.250 -0.2807 0.01726 0.01089 -0.1055 0.6266 0.0296
-8.000 -0.2550 0.01684 0.01039 -0.1052 0.6226 0.0297
-7.750 -0.2288 0.01644 0.00994 -0.1050 0.6191 0.0298
-7.500 -0.2024 0.01611 0.00955 -0.1048 0.6153 0.0299
-7.250 -0.1787 0.01511 0.00850 -0.1043 0.6114 0.0302
-7.000 -0.1542 0.01452 0.00787 -0.1038 0.6069 0.0305
-6.750 -0.1286 0.01407 0.00740 -0.1035 0.6037 0.0308
-6.500 -0.1022 0.01368 0.00702 -0.1033 0.6009 0.0312
-6.250 -0.0756 0.01337 0.00670 -0.1031 0.5975 0.0316
-6.000 -0.0491 0.01310 0.00639 -0.1029 0.5938 0.0320
-5.750 -0.0227 0.01284 0.00609 -0.1027 0.5899 0.0323
-5.500 0.0037 0.01261 0.00582 -0.1024 0.5860 0.0326
-5.250 0.0309 0.01233 0.00553 -0.1023 0.5835 0.0329
-5.000 0.0581 0.01208 0.00527 -0.1022 0.5803 0.0332
-4.750 0.0853 0.01186 0.00503 -0.1020 0.5767 0.0335
-4.500 0.1124 0.01169 0.00481 -0.1019 0.5730 0.0338
-4.250 0.1394 0.01156 0.00463 -0.1017 0.5689 0.0340
-4.000 0.1661 0.01127 0.00433 -0.1015 0.5658 0.0345
-3.750 0.1933 0.01100 0.00407 -0.1014 0.5625 0.0351
-3.500 0.2208 0.01081 0.00387 -0.1013 0.5586 0.0357
-3.250 0.2482 0.01068 0.00371 -0.1012 0.5547 0.0364
-3.000 0.2753 0.01059 0.00358 -0.1011 0.5503 0.0371
-2.750 0.3034 0.01048 0.00346 -0.1011 0.5469 0.0380
-2.500 0.3316 0.01035 0.00333 -0.1012 0.5429 0.0390
-2.250 0.3592 0.01023 0.00321 -0.1011 0.5383 0.0406
-2.000 0.3864 0.01017 0.00312 -0.1010 0.5335 0.0424
-1.750 0.4140 0.01008 0.00305 -0.1010 0.5293 0.0466
-1.500 0.4421 0.00997 0.00304 -0.1011 0.5249 0.0654
-1.250 0.4700 0.00995 0.00302 -0.1011 0.5196 0.0743
-1.000 0.4967 0.00993 0.00297 -0.1009 0.5138 0.0806
-0.750 0.5248 0.00987 0.00292 -0.1010 0.5090 0.0863
-0.500 0.5522 0.00980 0.00287 -0.1010 0.5034 0.0969
-0.250 0.5780 0.00970 0.00290 -0.1008 0.4973 0.1474
0.000 0.6056 0.00968 0.00290 -0.1009 0.4919 0.1607
0.250 0.6329 0.00968 0.00291 -0.1008 0.4855 0.1711
0.500 0.6587 0.00971 0.00294 -0.1006 0.4784 0.1879
0.750 0.6850 0.00951 0.00297 -0.1005 0.4729 0.2623
1.000 0.7106 0.00942 0.00302 -0.1003 0.4665 0.3258
1.250 0.7350 0.00927 0.00308 -0.1000 0.4603 0.4150
1.500 0.7592 0.00892 0.00319 -0.0996 0.4552 0.5763
1.750 0.7846 0.00891 0.00328 -0.0993 0.4491 0.6260
2.000 0.8090 0.00892 0.00340 -0.0988 0.4430 0.6770
2.250 0.8344 0.00886 0.00351 -0.0985 0.4381 0.7361
2.500 0.8583 0.00884 0.00365 -0.0978 0.4327 0.7948
2.750 0.8806 0.00891 0.00382 -0.0968 0.4271 0.8493
3.000 0.9036 0.00891 0.00397 -0.0957 0.4234 0.9057
3.250 0.9284 0.00901 0.00413 -0.0950 0.4191 0.9492
3.500 0.9621 0.00922 0.00431 -0.0965 0.4140 0.9751
3.750 0.9985 0.00947 0.00450 -0.0987 0.4087 0.9878
4.000 1.0383 0.00963 0.00465 -0.1015 0.4048 0.9949
4.250 1.0793 0.00985 0.00483 -0.1046 0.4003 0.9995
4.500 1.0954 0.01002 0.00496 -0.1026 0.3963 1.0000
4.750 1.1044 0.01020 0.00511 -0.0991 0.3923 1.0000
5.000 1.1240 0.01031 0.00522 -0.0977 0.3899 1.0000
5.250 1.1444 0.01046 0.00537 -0.0965 0.3867 1.0000
5.500 1.1648 0.01066 0.00555 -0.0954 0.3832 1.0000
5.750 1.1845 0.01092 0.00578 -0.0943 0.3793 1.0000
6.000 1.2038 0.01123 0.00605 -0.0932 0.3752 1.0000
6.250 1.2279 0.01139 0.00623 -0.0928 0.3728 1.0000
6.500 1.2507 0.01161 0.00645 -0.0923 0.3699 1.0000
6.750 1.2726 0.01187 0.00670 -0.0917 0.3667 1.0000
7.000 1.2932 0.01219 0.00701 -0.0909 0.3634 1.0000
7.250 1.3117 0.01261 0.00739 -0.0899 0.3595 1.0000
7.500 1.3347 0.01286 0.00766 -0.0895 0.3571 1.0000
7.750 1.3578 0.01311 0.00793 -0.0892 0.3545 1.0000
8.000 1.3792 0.01343 0.00826 -0.0886 0.3514 1.0000
8.250 1.3993 0.01381 0.00864 -0.0880 0.3484 1.0000
8.500 1.4177 0.01429 0.00910 -0.0871 0.3451 1.0000
8.750 1.4360 0.01478 0.00959 -0.0862 0.3416 1.0000
9.000 1.4588 0.01507 0.00991 -0.0860 0.3389 1.0000
9.250 1.4792 0.01548 0.01033 -0.0854 0.3351 1.0000
9.500 1.4970 0.01602 0.01086 -0.0846 0.3313 1.0000
9.750 1.5122 0.01671 0.01153 -0.0835 0.3272 1.0000
10.000 1.5315 0.01720 0.01206 -0.0830 0.3244 1.0000
10.250 1.5522 0.01764 0.01252 -0.0826 0.3213 1.0000
10.500 1.5697 0.01824 0.01314 -0.0819 0.3176 1.0000
10.750 1.5839 0.01905 0.01393 -0.0809 0.3132 1.0000
11.000 1.5984 0.01986 0.01475 -0.0800 0.3087 1.0000
11.250 1.6172 0.02044 0.01537 -0.0796 0.3048 1.0000
11.500 1.6324 0.02124 0.01619 -0.0788 0.3011 1.0000
11.750 1.6448 0.02223 0.01717 -0.0778 0.2974 1.0000
12.000 1.6563 0.02330 0.01826 -0.0768 0.2936 1.0000
12.250 1.6737 0.02402 0.01902 -0.0764 0.2903 1.0000
12.500 1.6872 0.02502 0.02005 -0.0757 0.2864 1.0000
12.750 1.6975 0.02626 0.02129 -0.0747 0.2823 1.0000
13.000 1.7059 0.02767 0.02272 -0.0737 0.2782 1.0000
13.250 1.7207 0.02864 0.02373 -0.0732 0.2747 1.0000
13.500 1.7311 0.02996 0.02508 -0.0725 0.2702 1.0000
13.750 1.7353 0.03180 0.02693 -0.0714 0.2651 1.0000
14.000 1.7457 0.03316 0.02832 -0.0708 0.2613 1.0000
14.250 1.7550 0.03464 0.02984 -0.0701 0.2568 1.0000
14.500 1.7579 0.03668 0.03189 -0.0692 0.2516 1.0000
14.750 1.7628 0.03858 0.03381 -0.0684 0.2467 1.0000
15.000 1.7681 0.04046 0.03573 -0.0676 0.2409 1.0000
15.250 1.7638 0.04324 0.03850 -0.0665 0.2343 1.0000
15.500 1.7673 0.04531 0.04061 -0.0658 0.2277 1.0000
15.750 1.7601 0.04843 0.04371 -0.0647 0.2200 1.0000
16.000 1.7589 0.05102 0.04633 -0.0639 0.2122 1.0000
16.250 1.7489 0.05448 0.04979 -0.0629 0.2041 1.0000
16.500 1.7389 0.05800 0.05331 -0.0619 0.1946 1.0000
16.750 1.7281 0.06167 0.05697 -0.0610 0.1849 1.0000
17.000 1.7118 0.06595 0.06125 -0.0601 0.1754 1.0000
17.250 1.6927 0.07066 0.06594 -0.0593 0.1656 1.0000
17.500 1.6765 0.07516 0.07045 -0.0587 0.1562 1.0000
17.750 1.6594 0.07983 0.07513 -0.0583 0.1478 1.0000
18.000 1.6403 0.08481 0.08012 -0.0579 0.1399 1.0000
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