GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.72 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe383-il-1000000.txt Download as CSV file: xf-goe383-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.1690 0.14770 0.14579 -0.0512 0.9055 0.0314
-16.500 -0.7485 0.06968 0.06678 -0.0884 1.0000 0.0304
-16.250 -0.7869 0.05994 0.05681 -0.0962 1.0000 0.0304
-16.000 -0.8076 0.05297 0.04963 -0.1025 0.9844 0.0304
-15.750 -0.8223 0.04787 0.04434 -0.1062 0.9718 0.0304
-15.500 -0.8352 0.04397 0.04027 -0.1077 0.9600 0.0305
-15.250 -0.8447 0.04083 0.03697 -0.1082 0.9493 0.0305
-15.000 -0.8504 0.03810 0.03408 -0.1084 0.9386 0.0306
-14.750 -0.8525 0.03575 0.03158 -0.1084 0.9283 0.0306
-14.500 -0.8528 0.03376 0.02945 -0.1078 0.9174 0.0307
-14.250 -0.8500 0.03203 0.02757 -0.1071 0.9048 0.0308
-14.000 -0.8454 0.03054 0.02595 -0.1060 0.8909 0.0309
-13.750 -0.8392 0.02927 0.02452 -0.1047 0.8751 0.0309
-13.500 -0.8311 0.02816 0.02325 -0.1032 0.8577 0.0310
-13.250 -0.8213 0.02721 0.02214 -0.1016 0.8394 0.0311
-13.000 -0.8101 0.02642 0.02118 -0.0999 0.8211 0.0312
-12.750 -0.7989 0.02577 0.02040 -0.0980 0.8036 0.0312
-12.500 -0.7871 0.02399 0.01845 -0.0967 0.7877 0.0315
-12.250 -0.7706 0.02292 0.01727 -0.0956 0.7718 0.0317
-12.000 -0.7522 0.02215 0.01639 -0.0947 0.7556 0.0319
-11.750 -0.7325 0.02149 0.01565 -0.0938 0.7397 0.0320
-11.500 -0.7118 0.02092 0.01500 -0.0930 0.7251 0.0322
-11.250 -0.6905 0.02041 0.01439 -0.0923 0.7114 0.0324
-11.000 -0.6683 0.01994 0.01385 -0.0916 0.6999 0.0326
-10.750 -0.6456 0.01950 0.01334 -0.0910 0.6900 0.0328
-10.500 -0.6223 0.01907 0.01284 -0.0904 0.6821 0.0331
-10.250 -0.5989 0.01864 0.01233 -0.0898 0.6743 0.0334
-10.000 -0.5752 0.01817 0.01180 -0.0893 0.6680 0.0336
-9.750 -0.5510 0.01770 0.01129 -0.0888 0.6624 0.0338
-9.500 -0.5268 0.01727 0.01079 -0.0883 0.6561 0.0340
-9.250 -0.5024 0.01689 0.01032 -0.0878 0.6490 0.0342
-9.000 -0.4772 0.01646 0.00987 -0.0874 0.6454 0.0345
-8.750 -0.4518 0.01609 0.00946 -0.0870 0.6415 0.0347
-8.500 -0.4262 0.01575 0.00907 -0.0867 0.6372 0.0349
-8.250 -0.4004 0.01546 0.00872 -0.0863 0.6323 0.0351
-8.000 -0.3756 0.01505 0.00825 -0.0858 0.6272 0.0353
-7.750 -0.3518 0.01442 0.00762 -0.0853 0.6248 0.0357
-7.500 -0.3263 0.01402 0.00721 -0.0849 0.6223 0.0361
-7.250 -0.2999 0.01371 0.00690 -0.0846 0.6196 0.0365
-7.000 -0.2732 0.01345 0.00662 -0.0844 0.6166 0.0368
-6.750 -0.2464 0.01321 0.00635 -0.0842 0.6134 0.0373
-6.500 -0.2196 0.01300 0.00610 -0.0840 0.6097 0.0377
-6.250 -0.1926 0.01281 0.00587 -0.0838 0.6059 0.0382
-6.000 -0.1649 0.01257 0.00563 -0.0837 0.6042 0.0386
-5.750 -0.1371 0.01237 0.00542 -0.0836 0.6021 0.0391
-5.500 -0.1096 0.01213 0.00517 -0.0835 0.5997 0.0396
-5.250 -0.0829 0.01181 0.00485 -0.0832 0.5972 0.0404
-5.000 -0.0552 0.01162 0.00466 -0.0831 0.5944 0.0411
-4.750 -0.0274 0.01147 0.00448 -0.0831 0.5912 0.0418
-4.500 0.0004 0.01135 0.00433 -0.0830 0.5874 0.0426
-4.250 0.0286 0.01123 0.00419 -0.0830 0.5843 0.0434
-4.000 0.0567 0.01102 0.00398 -0.0829 0.5822 0.0444
-3.750 0.0849 0.01082 0.00381 -0.0829 0.5798 0.0457
-3.500 0.1134 0.01068 0.00368 -0.0830 0.5770 0.0471
-3.250 0.1421 0.01057 0.00356 -0.0830 0.5739 0.0485
-3.000 0.1699 0.01041 0.00339 -0.0829 0.5707 0.0509
-2.750 0.1980 0.01034 0.00329 -0.0829 0.5667 0.0534
-2.500 0.2261 0.01019 0.00317 -0.0829 0.5634 0.0580
-2.250 0.2541 0.00996 0.00302 -0.0829 0.5605 0.0700
-2.000 0.2806 0.00957 0.00290 -0.0828 0.5570 0.1317
-1.500 0.3354 0.00919 0.00273 -0.0826 0.5487 0.1948
-1.250 0.3619 0.00897 0.00270 -0.0825 0.5440 0.2545
-1.000 0.3903 0.00880 0.00267 -0.0826 0.5406 0.2923
-0.750 0.4186 0.00867 0.00264 -0.0827 0.5359 0.3255
-0.500 0.4459 0.00852 0.00261 -0.0826 0.5304 0.3681
-0.250 0.4722 0.00833 0.00259 -0.0824 0.5244 0.4337
0.000 0.4994 0.00810 0.00258 -0.0824 0.5187 0.5047
0.250 0.5255 0.00791 0.00260 -0.0821 0.5114 0.5789
0.500 0.5518 0.00781 0.00265 -0.0818 0.5043 0.6389
0.750 0.5792 0.00778 0.00270 -0.0817 0.4960 0.6793
1.000 0.6055 0.00780 0.00277 -0.0813 0.4867 0.7144
1.250 0.6326 0.00782 0.00283 -0.0812 0.4773 0.7421
1.500 0.6590 0.00791 0.00291 -0.0808 0.4678 0.7615
1.750 0.6859 0.00797 0.00300 -0.0807 0.4594 0.7811
2.000 0.7119 0.00809 0.00310 -0.0803 0.4504 0.7985
2.750 0.7891 0.00837 0.00346 -0.0790 0.4275 0.8674
3.000 0.8134 0.00848 0.00361 -0.0782 0.4216 0.8941
3.250 0.8368 0.00865 0.00377 -0.0773 0.4157 0.9179
3.500 0.8625 0.00873 0.00390 -0.0768 0.4125 0.9395
3.750 0.8898 0.00886 0.00403 -0.0766 0.4087 0.9568
4.000 0.9198 0.00904 0.00419 -0.0772 0.4043 0.9700
4.250 0.9517 0.00927 0.00438 -0.0782 0.3994 0.9809
4.500 0.9881 0.00946 0.00455 -0.0802 0.3960 0.9875
4.750 1.0255 0.00961 0.00470 -0.0824 0.3929 0.9924
5.000 1.0657 0.00980 0.00486 -0.0853 0.3890 0.9951
5.250 1.1061 0.01003 0.00506 -0.0882 0.3848 0.9985
5.500 1.1313 0.01026 0.00525 -0.0881 0.3806 1.0000
5.750 1.1458 0.01036 0.00535 -0.0856 0.3782 1.0000
6.000 1.1633 0.01045 0.00545 -0.0837 0.3760 1.0000
6.250 1.1798 0.01056 0.00557 -0.0817 0.3732 1.0000
6.500 1.1957 0.01072 0.00572 -0.0795 0.3700 1.0000
6.750 1.2128 0.01094 0.00592 -0.0777 0.3664 1.0000
7.000 1.2294 0.01126 0.00620 -0.0760 0.3618 1.0000
7.250 1.2534 0.01139 0.00636 -0.0755 0.3591 1.0000
7.500 1.2759 0.01158 0.00657 -0.0748 0.3555 1.0000
7.750 1.2969 0.01185 0.00682 -0.0740 0.3513 1.0000
8.000 1.3156 0.01221 0.00716 -0.0728 0.3464 1.0000
8.250 1.3373 0.01249 0.00744 -0.0721 0.3429 1.0000
8.500 1.3602 0.01273 0.00770 -0.0717 0.3393 1.0000
8.750 1.3808 0.01306 0.00803 -0.0709 0.3348 1.0000
9.000 1.3988 0.01352 0.00847 -0.0698 0.3295 1.0000
9.250 1.4199 0.01387 0.00883 -0.0692 0.3246 1.0000
9.500 1.4393 0.01429 0.00925 -0.0684 0.3180 1.0000
9.750 1.4550 0.01491 0.00982 -0.0671 0.3107 1.0000
10.000 1.4736 0.01541 0.01032 -0.0663 0.3026 1.0000
10.250 1.4875 0.01617 0.01104 -0.0650 0.2935 1.0000
10.500 1.5019 0.01693 0.01177 -0.0638 0.2839 1.0000
10.750 1.5147 0.01781 0.01263 -0.0625 0.2749 1.0000
11.250 1.5379 0.01983 0.01460 -0.0600 0.2577 1.0000
11.500 1.5459 0.02113 0.01587 -0.0585 0.2497 1.0000
11.750 1.5580 0.02220 0.01694 -0.0575 0.2430 1.0000
12.250 1.5754 0.02489 0.01962 -0.0552 0.2300 1.0000
12.500 1.5817 0.02648 0.02120 -0.0540 0.2238 1.0000
12.750 1.5906 0.02791 0.02265 -0.0530 0.2189 1.0000
13.000 1.5995 0.02939 0.02414 -0.0522 0.2143 1.0000
13.250 1.6042 0.03122 0.02598 -0.0511 0.2095 1.0000
13.500 1.6124 0.03281 0.02760 -0.0504 0.2056 1.0000
13.750 1.6201 0.03447 0.02929 -0.0497 0.2014 1.0000
14.000 1.6234 0.03653 0.03136 -0.0488 0.1969 1.0000
14.250 1.6287 0.03842 0.03326 -0.0480 0.1930 1.0000
14.500 1.6357 0.04021 0.03510 -0.0474 0.1893 1.0000
14.750 1.6393 0.04231 0.03721 -0.0467 0.1850 1.0000
15.000 1.6398 0.04473 0.03965 -0.0460 0.1807 1.0000
15.250 1.6465 0.04658 0.04154 -0.0455 0.1767 1.0000
15.500 1.6466 0.04908 0.04405 -0.0448 0.1718 1.0000
15.750 1.6471 0.05157 0.04657 -0.0442 0.1671 1.0000
16.000 1.6481 0.05405 0.04906 -0.0437 0.1614 1.0000
16.250 1.6440 0.05704 0.05206 -0.0431 0.1556 1.0000
16.500 1.6404 0.06001 0.05503 -0.0426 0.1481 1.0000
16.750 1.6321 0.06357 0.05859 -0.0420 0.1393 1.0000
17.000 1.6162 0.06797 0.06296 -0.0414 0.1268 1.0000
17.250 1.5833 0.07433 0.06923 -0.0408 0.1055 1.0000
17.500 1.5448 0.08158 0.07639 -0.0404 0.0852 1.0000
17.750 1.5220 0.08718 0.08200 -0.0404 0.0773 1.0000
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