GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.92 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe385-il-1000000.txt Download as CSV file: xf-goe385-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2879 0.09802 0.09654 -0.0244 1.0000 0.0131
-9.750 -0.2824 0.09511 0.09365 -0.0250 1.0000 0.0133
-9.250 -0.3922 0.09817 0.09663 -0.0181 1.0000 0.0130
-9.000 -0.3847 0.09546 0.09393 -0.0191 1.0000 0.0132
-8.750 -0.3779 0.09257 0.09105 -0.0205 1.0000 0.0134
-8.500 -0.3714 0.08960 0.08810 -0.0222 1.0000 0.0136
-8.250 -0.3659 0.08643 0.08495 -0.0242 1.0000 0.0140
-8.000 -0.3619 0.08314 0.08168 -0.0264 1.0000 0.0144
-7.750 -0.3518 0.07885 0.07740 -0.0317 0.9876 0.0151
-7.500 -0.3326 0.07011 0.06860 -0.0467 0.9683 0.0161
-7.250 -0.3205 0.06470 0.06312 -0.0519 0.9504 0.0161
-5.500 -0.1963 0.03453 0.03152 -0.0661 0.8150 0.0203
-5.250 -0.1795 0.02603 0.02240 -0.0668 0.8057 0.0206
-5.000 -0.1557 0.02653 0.02295 -0.0674 0.7938 0.0214
-4.750 -0.1306 0.02606 0.02242 -0.0676 0.7812 0.0221
-4.500 -0.1001 0.02581 0.02191 -0.0670 0.7663 0.0255
-4.250 -0.0743 0.02343 0.01916 -0.0668 0.7490 0.0257
-4.000 -0.0523 0.01814 0.01333 -0.0669 0.7283 0.0267
-3.750 -0.0259 0.01762 0.01271 -0.0671 0.6992 0.0274
-3.500 0.0009 0.01707 0.01199 -0.0671 0.6749 0.0285
-3.250 0.0288 0.01661 0.01134 -0.0671 0.6587 0.0308
-3.000 0.0585 0.01777 0.01235 -0.0668 0.6463 0.0326
-2.500 0.1131 0.01313 0.00720 -0.0668 0.6295 0.0310
-2.250 0.1415 0.01221 0.00614 -0.0668 0.6218 0.0311
-2.000 0.1698 0.01160 0.00540 -0.0667 0.6150 0.0313
-1.750 0.1982 0.01099 0.00472 -0.0668 0.6083 0.0314
-1.500 0.2264 0.01052 0.00417 -0.0668 0.6020 0.0315
-1.250 0.2549 0.01007 0.00369 -0.0668 0.5964 0.0316
-1.000 0.2832 0.00972 0.00330 -0.0669 0.5906 0.0318
-0.750 0.3118 0.00961 0.00315 -0.0670 0.5847 0.0324
-0.500 0.3402 0.00931 0.00284 -0.0670 0.5783 0.0329
-0.250 0.3683 0.00885 0.00231 -0.0671 0.5710 0.0336
0.000 0.3969 0.00857 0.00202 -0.0673 0.5635 0.0345
0.500 0.4543 0.00833 0.00172 -0.0676 0.5494 0.0361
0.750 0.4829 0.00827 0.00163 -0.0677 0.5418 0.0372
1.000 0.5117 0.00820 0.00156 -0.0679 0.5337 0.0389
1.250 0.5403 0.00818 0.00150 -0.0680 0.5242 0.0408
1.500 0.5689 0.00817 0.00145 -0.0682 0.5129 0.0430
1.750 0.5974 0.00815 0.00142 -0.0683 0.5000 0.0534
2.000 0.6211 0.00600 0.00157 -0.0681 0.4865 1.0000
2.250 0.6490 0.00614 0.00161 -0.0681 0.4689 1.0000
2.500 0.6768 0.00631 0.00166 -0.0682 0.4482 1.0000
2.750 0.7043 0.00651 0.00174 -0.0682 0.4250 1.0000
3.000 0.7319 0.00671 0.00183 -0.0683 0.4043 1.0000
3.500 0.7864 0.00719 0.00208 -0.0683 0.3595 1.0000
3.750 0.8139 0.00739 0.00220 -0.0684 0.3445 1.0000
4.000 0.8414 0.00759 0.00234 -0.0684 0.3324 1.0000
4.250 0.8688 0.00779 0.00248 -0.0685 0.3211 1.0000
4.500 0.8964 0.00795 0.00261 -0.0686 0.3116 1.0000
4.750 0.9239 0.00814 0.00276 -0.0686 0.3025 1.0000
5.250 0.9785 0.00852 0.00307 -0.0687 0.2828 1.0000
5.500 1.0056 0.00872 0.00323 -0.0688 0.2732 1.0000
5.750 1.0325 0.00895 0.00342 -0.0688 0.2626 1.0000
6.000 1.0594 0.00916 0.00360 -0.0688 0.2512 1.0000
6.250 1.0862 0.00937 0.00378 -0.0688 0.2409 1.0000
6.500 1.1125 0.00964 0.00400 -0.0687 0.2268 1.0000
6.750 1.1387 0.00992 0.00423 -0.0686 0.2132 1.0000
7.000 1.1642 0.01027 0.00450 -0.0685 0.1952 1.0000
7.250 1.1867 0.01095 0.00494 -0.0680 0.1528 1.0000
7.500 1.2077 0.01177 0.00554 -0.0672 0.1170 1.0000
7.750 1.2310 0.01231 0.00600 -0.0668 0.1007 1.0000
8.000 1.2510 0.01320 0.00664 -0.0659 0.0605 1.0000
8.250 1.2722 0.01392 0.00728 -0.0651 0.0415 1.0000
8.500 1.2900 0.01497 0.00814 -0.0639 0.0167 1.0000
8.750 1.3125 0.01547 0.00870 -0.0632 0.0149 1.0000
9.000 1.3335 0.01610 0.00936 -0.0624 0.0133 1.0000
9.250 1.3541 0.01674 0.01007 -0.0615 0.0123 1.0000
9.500 1.3752 0.01728 0.01067 -0.0607 0.0118 1.0000
9.750 1.3951 0.01790 0.01135 -0.0597 0.0112 1.0000
10.000 1.4136 0.01858 0.01209 -0.0585 0.0106 1.0000
10.250 1.4300 0.01938 0.01295 -0.0571 0.0101 1.0000
10.500 1.4391 0.02066 0.01434 -0.0546 0.0094 1.0000
10.750 1.4510 0.02147 0.01524 -0.0525 0.0092 1.0000
11.000 1.4627 0.02223 0.01605 -0.0504 0.0089 1.0000
11.250 1.4722 0.02317 0.01707 -0.0482 0.0087 1.0000
11.500 1.4809 0.02424 0.01822 -0.0461 0.0084 1.0000
11.750 1.4882 0.02549 0.01955 -0.0442 0.0081 1.0000
12.000 1.4947 0.02689 0.02103 -0.0424 0.0079 1.0000
12.250 1.5000 0.02850 0.02272 -0.0409 0.0077 1.0000
12.500 1.5042 0.03036 0.02467 -0.0397 0.0075 1.0000
12.750 1.5062 0.03255 0.02695 -0.0387 0.0073 1.0000
13.000 1.5047 0.03524 0.02973 -0.0378 0.0072 1.0000
13.250 1.4982 0.03860 0.03321 -0.0372 0.0070 1.0000
13.500 1.4874 0.04266 0.03739 -0.0369 0.0069 1.0000
13.750 1.4731 0.04730 0.04217 -0.0369 0.0068 1.0000
14.000 1.4671 0.05106 0.04603 -0.0371 0.0067 1.0000
14.250 1.4662 0.05427 0.04934 -0.0374 0.0067 1.0000
14.500 1.4640 0.05767 0.05284 -0.0378 0.0066 1.0000
14.750 1.4609 0.06128 0.05655 -0.0383 0.0065 1.0000
15.000 1.4570 0.06504 0.06041 -0.0389 0.0064 1.0000
15.250 1.4524 0.06902 0.06448 -0.0397 0.0064 1.0000
15.500 1.4479 0.07309 0.06866 -0.0407 0.0063 1.0000
15.750 1.4419 0.07741 0.07308 -0.0417 0.0061 1.0000
16.000 1.4359 0.08182 0.07758 -0.0429 0.0061 1.0000
16.250 1.4300 0.08632 0.08218 -0.0441 0.0060 1.0000
16.500 1.4236 0.09095 0.08691 -0.0455 0.0059 1.0000
16.750 1.4165 0.09569 0.09173 -0.0469 0.0058 1.0000
17.000 1.4097 0.10046 0.09660 -0.0485 0.0057 1.0000
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Polar data table (+)
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