GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 200,000 Max Cl/Cd: 79.89 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe400-il-200000-n5.txt Download as CSV file: xf-goe400-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3827 0.09677 0.09337 -0.0047 1.0000 0.0240
-7.750 -0.3767 0.09333 0.08996 -0.0066 1.0000 0.0237
-7.500 -0.3707 0.09000 0.08666 -0.0086 1.0000 0.0238
-7.250 -0.3620 0.08656 0.08326 -0.0119 1.0000 0.0251
-7.000 -0.3501 0.08232 0.07903 -0.0175 1.0000 0.0261
-6.750 -0.3368 0.07811 0.07484 -0.0222 1.0000 0.0262
-6.500 -0.3210 0.07354 0.07026 -0.0277 1.0000 0.0265
-6.250 -0.3046 0.06865 0.06539 -0.0334 1.0000 0.0277
-6.000 -0.2913 0.06827 0.06504 -0.0310 0.9980 0.0295
-5.750 -0.2591 0.06470 0.06141 -0.0373 0.9769 0.0320
-5.500 -0.2237 0.05947 0.05608 -0.0458 0.9546 0.0321
-5.250 -0.1874 0.05445 0.05091 -0.0537 0.9318 0.0330
-5.000 -0.1484 0.04885 0.04510 -0.0620 0.9066 0.0350
-4.750 -0.1151 0.04400 0.04001 -0.0674 0.8816 0.0353
-4.500 -0.0796 0.03886 0.03454 -0.0726 0.8582 0.0364
-4.250 -0.0504 0.03416 0.02953 -0.0761 0.8356 0.0376
-4.000 -0.0200 0.02951 0.02446 -0.0789 0.8161 0.0378
-3.750 0.0101 0.02461 0.01902 -0.0811 0.7987 0.0383
-3.500 0.0390 0.02067 0.01448 -0.0824 0.7827 0.0392
-3.250 0.0661 0.01919 0.01264 -0.0826 0.7673 0.0406
-3.000 0.0939 0.01721 0.01015 -0.0827 0.7536 0.0415
-2.750 0.1215 0.01583 0.00834 -0.0827 0.7405 0.0420
-2.500 0.1490 0.01490 0.00711 -0.0825 0.7283 0.0428
-2.250 0.1765 0.01421 0.00618 -0.0822 0.7169 0.0436
-2.000 0.2039 0.01367 0.00544 -0.0819 0.7061 0.0447
-1.750 0.2313 0.01324 0.00483 -0.0816 0.6954 0.0459
-1.500 0.2589 0.01289 0.00434 -0.0813 0.6850 0.0470
-1.250 0.2863 0.01262 0.00394 -0.0810 0.6753 0.0482
-1.000 0.3137 0.01233 0.00361 -0.0807 0.6654 0.0515
-0.750 0.3412 0.01214 0.00340 -0.0805 0.6558 0.0562
-0.500 0.3686 0.01199 0.00322 -0.0802 0.6469 0.0619
-0.250 0.3963 0.01200 0.00332 -0.0799 0.6373 0.0745
0.000 0.4240 0.01211 0.00332 -0.0796 0.6284 0.0924
0.250 0.4515 0.01218 0.00333 -0.0794 0.6193 0.1014
0.500 0.4791 0.01221 0.00329 -0.0791 0.6101 0.1086
0.750 0.5064 0.01222 0.00329 -0.0789 0.6015 0.1160
1.000 0.5337 0.01221 0.00329 -0.0787 0.5920 0.1254
1.250 0.5610 0.01223 0.00330 -0.0785 0.5829 0.1338
1.500 0.5882 0.01218 0.00324 -0.0782 0.5738 0.1378
1.750 0.6155 0.01212 0.00323 -0.0780 0.5641 0.1406
2.000 0.6427 0.01211 0.00321 -0.0777 0.5549 0.1430
2.250 0.6699 0.01212 0.00322 -0.0775 0.5444 0.1451
2.500 0.6970 0.01214 0.00325 -0.0772 0.5324 0.1474
2.750 0.7239 0.01218 0.00327 -0.0769 0.5186 0.1501
3.000 0.7507 0.01223 0.00332 -0.0766 0.5039 0.1538
3.250 0.7775 0.01229 0.00339 -0.0763 0.4890 0.1595
3.500 0.8042 0.01238 0.00350 -0.0760 0.4736 0.1687
3.750 0.8307 0.01245 0.00363 -0.0756 0.4585 0.1954
4.250 0.8839 0.01143 0.00397 -0.0751 0.4319 1.0000
4.500 0.9103 0.01166 0.00415 -0.0748 0.4186 1.0000
4.750 0.9366 0.01190 0.00435 -0.0744 0.4052 1.0000
5.000 0.9627 0.01215 0.00460 -0.0740 0.3902 1.0000
5.250 0.9886 0.01243 0.00485 -0.0737 0.3750 1.0000
5.500 1.0145 0.01272 0.00512 -0.0733 0.3600 1.0000
5.750 1.0402 0.01302 0.00543 -0.0729 0.3455 1.0000
6.000 1.0656 0.01336 0.00577 -0.0725 0.3275 1.0000
6.250 1.0909 0.01371 0.00613 -0.0721 0.3113 1.0000
6.500 1.1155 0.01412 0.00652 -0.0717 0.2908 1.0000
6.750 1.1390 0.01468 0.00699 -0.0711 0.2571 1.0000
7.000 1.1612 0.01541 0.00753 -0.0705 0.2146 1.0000
7.250 1.1821 0.01634 0.00822 -0.0698 0.1681 1.0000
7.500 1.2020 0.01741 0.00903 -0.0691 0.1225 1.0000
7.750 1.2221 0.01842 0.00987 -0.0683 0.0962 1.0000
8.000 1.2422 0.01939 0.01080 -0.0675 0.0801 1.0000
8.250 1.2634 0.02018 0.01159 -0.0668 0.0551 1.0000
8.500 1.2790 0.02166 0.01282 -0.0656 0.0294 1.0000
8.750 1.2970 0.02278 0.01401 -0.0644 0.0241 1.0000
9.000 1.3134 0.02401 0.01532 -0.0632 0.0207 1.0000
9.250 1.3295 0.02520 0.01664 -0.0619 0.0188 1.0000
9.500 1.3450 0.02637 0.01800 -0.0605 0.0176 1.0000
9.750 1.3584 0.02767 0.01944 -0.0590 0.0166 1.0000
10.000 1.3697 0.02907 0.02097 -0.0573 0.0156 1.0000
10.250 1.3773 0.03064 0.02266 -0.0554 0.0148 1.0000
10.500 1.3776 0.03263 0.02475 -0.0529 0.0140 1.0000
10.750 1.3780 0.03474 0.02698 -0.0509 0.0134 1.0000
11.000 1.3824 0.03665 0.02903 -0.0495 0.0130 1.0000
11.250 1.3850 0.03888 0.03141 -0.0483 0.0127 1.0000
11.500 1.3870 0.04132 0.03399 -0.0474 0.0124 1.0000
11.750 1.3886 0.04392 0.03674 -0.0467 0.0121 1.0000
12.000 1.3897 0.04667 0.03966 -0.0462 0.0118 1.0000
12.250 1.3903 0.04954 0.04267 -0.0458 0.0115 1.0000
12.500 1.3903 0.05254 0.04581 -0.0454 0.0113 1.0000
12.750 1.3899 0.05565 0.04906 -0.0453 0.0110 1.0000
13.000 1.3886 0.05890 0.05244 -0.0453 0.0107 1.0000
13.250 1.3865 0.06231 0.05598 -0.0455 0.0105 1.0000
13.500 1.3833 0.06591 0.05970 -0.0460 0.0103 1.0000
13.750 1.3790 0.06971 0.06362 -0.0465 0.0100 1.0000
14.000 1.3733 0.07376 0.06777 -0.0471 0.0098 1.0000
14.250 1.3658 0.07811 0.07225 -0.0476 0.0096 1.0000
14.500 1.3572 0.08287 0.07718 -0.0488 0.0095 1.0000
14.750 1.3485 0.08788 0.08239 -0.0506 0.0093 1.0000
15.000 1.3391 0.09321 0.08792 -0.0526 0.0093 1.0000
15.250 1.3286 0.09893 0.09384 -0.0549 0.0092 1.0000
15.500 1.3172 0.10506 0.10016 -0.0577 0.0092 1.0000
15.750 1.3051 0.11152 0.10681 -0.0608 0.0091 1.0000
16.000 1.2924 0.11840 0.11388 -0.0643 0.0091 1.0000
16.250 1.2791 0.12568 0.12133 -0.0683 0.0091 1.0000
16.500 1.2653 0.13336 0.12918 -0.0726 0.0091 1.0000
16.750 1.2510 0.14154 0.13753 -0.0775 0.0091 1.0000
17.000 1.2365 0.15015 0.14630 -0.0827 0.0091 1.0000
17.250 1.2218 0.15933 0.15563 -0.0885 0.0092 1.0000
17.500 1.2063 0.16932 0.16576 -0.0948 0.0093 1.0000
17.750 1.1903 0.18015 0.17671 -0.1016 0.0094 1.0000
18.000 1.1729 0.19249 0.18913 -0.1091 0.0095 1.0000
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