GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 500,000 Max Cl/Cd: 106 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe584-il-500000-n5.txt Download as CSV file: xf-goe584-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 584 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3912 0.14800 0.14543 -0.0316 1.0000 0.0133
-15.000 -0.3846 0.14526 0.14269 -0.0327 1.0000 0.0135
-13.500 -0.9028 0.03169 0.02829 -0.0995 0.9864 0.0184
-13.250 -0.8865 0.02859 0.02491 -0.1020 0.9761 0.0190
-13.000 -0.8634 0.02630 0.02243 -0.1043 0.9668 0.0199
-12.750 -0.8366 0.02451 0.02048 -0.1064 0.9568 0.0210
-12.500 -0.8074 0.02299 0.01875 -0.1084 0.9457 0.0223
-12.250 -0.7771 0.02183 0.01747 -0.1102 0.9326 0.0236
-12.000 -0.7484 0.02097 0.01648 -0.1112 0.9174 0.0252
-11.750 -0.7237 0.02013 0.01545 -0.1113 0.9007 0.0267
-11.500 -0.6984 0.01976 0.01501 -0.1111 0.8857 0.0280
-11.250 -0.6740 0.01943 0.01458 -0.1107 0.8721 0.0294
-11.000 -0.6514 0.01891 0.01389 -0.1099 0.8592 0.0310
-10.750 -0.6280 0.01852 0.01338 -0.1093 0.8483 0.0323
-10.500 -0.6021 0.01853 0.01333 -0.1089 0.8387 0.0333
-10.250 -0.5767 0.01844 0.01318 -0.1084 0.8292 0.0345
-10.000 -0.5525 0.01814 0.01274 -0.1078 0.8209 0.0358
-9.750 -0.5285 0.01771 0.01215 -0.1072 0.8127 0.0370
-9.500 -0.5044 0.01736 0.01165 -0.1065 0.8052 0.0380
-9.250 -0.4787 0.01727 0.01155 -0.1061 0.7974 0.0388
-9.000 -0.4528 0.01724 0.01146 -0.1057 0.7902 0.0396
-8.750 -0.4269 0.01715 0.01131 -0.1053 0.7835 0.0405
-8.500 -0.4014 0.01697 0.01104 -0.1048 0.7763 0.0415
-8.250 -0.3762 0.01671 0.01066 -0.1043 0.7696 0.0426
-8.000 -0.3508 0.01638 0.01021 -0.1039 0.7626 0.0436
-7.750 -0.3251 0.01618 0.00987 -0.1034 0.7561 0.0443
-7.500 -0.3006 0.01563 0.00922 -0.1029 0.7495 0.0452
-7.250 -0.2754 0.01528 0.00882 -0.1024 0.7425 0.0461
-7.000 -0.2495 0.01507 0.00856 -0.1020 0.7360 0.0468
-6.750 -0.2234 0.01484 0.00828 -0.1016 0.7295 0.0477
-6.500 -0.1976 0.01455 0.00791 -0.1012 0.7229 0.0484
-6.250 -0.1715 0.01424 0.00752 -0.1008 0.7164 0.0492
-6.000 -0.1454 0.01396 0.00715 -0.1004 0.7093 0.0501
-5.750 -0.1194 0.01365 0.00675 -0.1000 0.7032 0.0508
-5.500 -0.0931 0.01333 0.00635 -0.0996 0.6968 0.0514
-5.250 -0.0668 0.01306 0.00599 -0.0992 0.6902 0.0519
-5.000 -0.0404 0.01282 0.00568 -0.0988 0.6840 0.0525
-4.750 -0.0137 0.01262 0.00542 -0.0985 0.6773 0.0529
-4.500 0.0125 0.01236 0.00507 -0.0980 0.6715 0.0533
-4.250 0.0382 0.01190 0.00458 -0.0976 0.6657 0.0542
-4.000 0.0642 0.01159 0.00423 -0.0972 0.6594 0.0550
-3.750 0.0904 0.01138 0.00396 -0.0967 0.6536 0.0558
-3.500 0.1171 0.01118 0.00375 -0.0964 0.6478 0.0565
-3.250 0.1437 0.01102 0.00355 -0.0961 0.6421 0.0573
-3.000 0.1703 0.01089 0.00337 -0.0957 0.6366 0.0581
-2.750 0.1972 0.01075 0.00321 -0.0954 0.6309 0.0591
-2.500 0.2240 0.01063 0.00307 -0.0951 0.6252 0.0601
-2.250 0.2506 0.01053 0.00292 -0.0947 0.6200 0.0610
-2.000 0.2777 0.01042 0.00279 -0.0945 0.6144 0.0618
-1.750 0.3045 0.01033 0.00267 -0.0941 0.6088 0.0626
-1.500 0.3312 0.01028 0.00257 -0.0938 0.6034 0.0632
-1.250 0.3582 0.01018 0.00247 -0.0935 0.5974 0.0642
-1.000 0.3847 0.01009 0.00235 -0.0931 0.5910 0.0663
-0.750 0.4113 0.01004 0.00228 -0.0928 0.5848 0.0685
-0.500 0.4383 0.00998 0.00223 -0.0925 0.5785 0.0710
-0.250 0.4649 0.00996 0.00219 -0.0921 0.5726 0.0744
0.000 0.4917 0.00992 0.00216 -0.0919 0.5674 0.0803
0.250 0.5184 0.00986 0.00214 -0.0916 0.5616 0.0922
0.500 0.5442 0.00975 0.00215 -0.0911 0.5559 0.1350
0.750 0.5704 0.00965 0.00218 -0.0908 0.5505 0.1782
1.000 0.5967 0.00959 0.00221 -0.0905 0.5446 0.2111
1.250 0.6224 0.00954 0.00225 -0.0900 0.5387 0.2532
1.500 0.6476 0.00935 0.00232 -0.0896 0.5335 0.3439
1.750 0.6710 0.00904 0.00238 -0.0889 0.5271 0.4785
2.000 0.6825 0.00815 0.00254 -0.0853 0.5218 0.8356
2.500 0.8073 0.00828 0.00278 -0.1002 0.5058 1.0000
2.750 0.8315 0.00838 0.00285 -0.0994 0.4993 1.0000
3.000 0.8552 0.00849 0.00293 -0.0985 0.4921 1.0000
3.250 0.8789 0.00862 0.00302 -0.0976 0.4854 1.0000
3.500 0.9028 0.00873 0.00311 -0.0968 0.4775 1.0000
3.750 0.9261 0.00888 0.00322 -0.0959 0.4702 1.0000
4.000 0.9498 0.00901 0.00333 -0.0950 0.4615 1.0000
4.250 0.9725 0.00918 0.00345 -0.0940 0.4508 1.0000
4.500 0.9943 0.00938 0.00359 -0.0928 0.4378 1.0000
4.750 1.0156 0.00961 0.00374 -0.0915 0.4220 1.0000
5.000 1.0366 0.00985 0.00392 -0.0902 0.4059 1.0000
5.250 1.0570 0.01013 0.00412 -0.0889 0.3889 1.0000
5.500 1.0775 0.01040 0.00433 -0.0875 0.3743 1.0000
5.750 1.0986 0.01066 0.00454 -0.0863 0.3623 1.0000
6.000 1.1192 0.01093 0.00477 -0.0850 0.3499 1.0000
6.250 1.1392 0.01123 0.00502 -0.0836 0.3379 1.0000
6.500 1.1583 0.01156 0.00530 -0.0821 0.3257 1.0000
6.750 1.1779 0.01186 0.00557 -0.0806 0.3143 1.0000
7.000 1.1972 0.01216 0.00585 -0.0792 0.3045 1.0000
7.250 1.2151 0.01251 0.00617 -0.0775 0.2946 1.0000
7.500 1.2336 0.01281 0.00647 -0.0759 0.2847 1.0000
7.750 1.2490 0.01316 0.00680 -0.0737 0.2756 1.0000
8.000 1.2634 0.01354 0.00714 -0.0714 0.2652 1.0000
8.250 1.2774 0.01395 0.00753 -0.0691 0.2534 1.0000
8.500 1.2882 0.01451 0.00802 -0.0664 0.2366 1.0000
8.750 1.2982 0.01515 0.00857 -0.0637 0.2196 1.0000
9.000 1.3084 0.01581 0.00916 -0.0611 0.2038 1.0000
9.250 1.3196 0.01647 0.00978 -0.0588 0.1903 1.0000
9.500 1.3299 0.01721 0.01048 -0.0566 0.1763 1.0000
9.750 1.3397 0.01802 0.01125 -0.0544 0.1630 1.0000
10.000 1.3494 0.01889 0.01208 -0.0523 0.1517 1.0000
10.250 1.3569 0.01993 0.01306 -0.0501 0.1389 1.0000
10.500 1.3663 0.02092 0.01404 -0.0483 0.1292 1.0000
10.750 1.3759 0.02195 0.01507 -0.0466 0.1221 1.0000
11.000 1.3857 0.02302 0.01613 -0.0451 0.1150 1.0000
11.250 1.3941 0.02422 0.01733 -0.0435 0.1090 1.0000
11.500 1.4041 0.02535 0.01849 -0.0422 0.1029 1.0000
11.750 1.4116 0.02669 0.01984 -0.0408 0.0971 1.0000
12.000 1.4205 0.02798 0.02115 -0.0395 0.0912 1.0000
12.250 1.4259 0.02957 0.02273 -0.0382 0.0842 1.0000
12.500 1.4296 0.03134 0.02447 -0.0369 0.0739 1.0000
13.000 1.4168 0.03681 0.02973 -0.0337 0.0366 1.0000
13.250 1.4137 0.03942 0.03234 -0.0325 0.0299 1.0000
13.500 1.4161 0.04162 0.03459 -0.0317 0.0269 1.0000
13.750 1.4178 0.04393 0.03696 -0.0310 0.0246 1.0000
14.000 1.4201 0.04625 0.03934 -0.0304 0.0230 1.0000
14.250 1.4235 0.04850 0.04166 -0.0299 0.0214 1.0000
14.500 1.4257 0.05095 0.04418 -0.0295 0.0204 1.0000
14.750 1.4263 0.05360 0.04690 -0.0292 0.0194 1.0000
15.000 1.4277 0.05624 0.04961 -0.0289 0.0186 1.0000
15.250 1.4298 0.05885 0.05231 -0.0288 0.0179 1.0000
15.500 1.4303 0.06167 0.05521 -0.0288 0.0171 1.0000
15.750 1.4297 0.06469 0.05831 -0.0288 0.0165 1.0000
16.000 1.4272 0.06801 0.06170 -0.0290 0.0159 1.0000
16.250 1.4247 0.07140 0.06517 -0.0293 0.0155 1.0000
16.500 1.4235 0.07467 0.06854 -0.0296 0.0151 1.0000
16.750 1.4212 0.07813 0.07209 -0.0301 0.0146 1.0000
17.000 1.4187 0.08169 0.07574 -0.0307 0.0142 1.0000
17.250 1.4152 0.08544 0.07959 -0.0314 0.0138 1.0000
17.500 1.4104 0.08945 0.08368 -0.0323 0.0134 1.0000
17.750 1.4038 0.09377 0.08808 -0.0333 0.0131 1.0000
18.000 1.3969 0.09822 0.09264 -0.0345 0.0129 1.0000
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