GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.14 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe285-il-1000000.txt Download as CSV file: xf-goe285-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2918 0.10382 0.10214 -0.0343 1.0000 0.0265
-10.750 -0.7605 0.03817 0.03575 -0.0662 1.0000 0.0243
-10.500 -0.7771 0.03397 0.03120 -0.0634 0.9998 0.0245
-10.250 -0.7579 0.03028 0.02712 -0.0658 0.9975 0.0247
-10.000 -0.7320 0.02809 0.02465 -0.0676 0.9954 0.0249
-9.750 -0.7062 0.02565 0.02187 -0.0694 0.9938 0.0251
-9.500 -0.6874 0.02210 0.01798 -0.0701 0.9904 0.0254
-9.250 -0.6589 0.02060 0.01636 -0.0712 0.9879 0.0257
-9.000 -0.6277 0.01954 0.01520 -0.0725 0.9860 0.0260
-8.750 -0.5950 0.01861 0.01419 -0.0741 0.9844 0.0263
-8.500 -0.5603 0.01787 0.01338 -0.0759 0.9831 0.0267
-8.250 -0.5315 0.01711 0.01255 -0.0763 0.9777 0.0270
-8.000 -0.5002 0.01626 0.01158 -0.0773 0.9732 0.0273
-7.750 -0.4713 0.01547 0.01069 -0.0776 0.9672 0.0276
-7.500 -0.4430 0.01476 0.00988 -0.0778 0.9594 0.0278
-7.250 -0.4156 0.01411 0.00915 -0.0776 0.9491 0.0281
-7.000 -0.3881 0.01354 0.00848 -0.0775 0.9371 0.0284
-6.750 -0.3612 0.01306 0.00790 -0.0771 0.9232 0.0286
-6.500 -0.3349 0.01265 0.00739 -0.0767 0.9075 0.0288
-6.250 -0.3085 0.01234 0.00696 -0.0762 0.8914 0.0290
-6.000 -0.2833 0.01171 0.00621 -0.0756 0.8756 0.0294
-5.750 -0.2584 0.01107 0.00548 -0.0749 0.8602 0.0300
-5.500 -0.2322 0.01071 0.00506 -0.0745 0.8459 0.0305
-5.250 -0.2055 0.01042 0.00470 -0.0741 0.8331 0.0309
-5.000 -0.1787 0.01015 0.00437 -0.0737 0.8209 0.0313
-4.750 -0.1518 0.00992 0.00407 -0.0734 0.8085 0.0318
-4.500 -0.1247 0.00969 0.00377 -0.0731 0.7955 0.0322
-4.250 -0.0973 0.00948 0.00351 -0.0728 0.7832 0.0328
-4.000 -0.0699 0.00930 0.00326 -0.0725 0.7708 0.0332
-3.750 -0.0426 0.00915 0.00304 -0.0722 0.7568 0.0336
-3.500 -0.0155 0.00891 0.00273 -0.0719 0.7413 0.0345
-3.250 0.0117 0.00872 0.00248 -0.0716 0.7249 0.0356
-2.750 0.0666 0.00852 0.00215 -0.0711 0.6900 0.0382
-2.500 0.0940 0.00843 0.00199 -0.0708 0.6727 0.0400
-2.250 0.1213 0.00834 0.00186 -0.0706 0.6562 0.0435
-2.000 0.1488 0.00821 0.00177 -0.0704 0.6420 0.0586
-1.750 0.1766 0.00814 0.00174 -0.0703 0.6300 0.0753
-1.500 0.2046 0.00812 0.00169 -0.0701 0.6187 0.0828
-1.250 0.2325 0.00812 0.00165 -0.0700 0.6069 0.0883
-1.000 0.2606 0.00808 0.00161 -0.0699 0.5951 0.0949
-0.750 0.2885 0.00807 0.00158 -0.0698 0.5824 0.1016
-0.500 0.3163 0.00805 0.00156 -0.0697 0.5679 0.1117
-0.250 0.3440 0.00804 0.00154 -0.0696 0.5512 0.1263
0.000 0.3715 0.00804 0.00153 -0.0694 0.5316 0.1452
0.250 0.3988 0.00806 0.00152 -0.0692 0.5087 0.1669
0.500 0.4255 0.00803 0.00154 -0.0690 0.4853 0.2091
0.750 0.4510 0.00775 0.00158 -0.0688 0.4649 0.3517
1.000 0.4744 0.00716 0.00165 -0.0682 0.4488 0.6077
1.250 0.4918 0.00648 0.00178 -0.0657 0.4361 0.8814
1.500 0.5215 0.00654 0.00191 -0.0657 0.4232 0.9673
1.750 0.5605 0.00669 0.00199 -0.0680 0.4112 0.9856
2.000 0.6006 0.00685 0.00207 -0.0706 0.3996 0.9937
2.250 0.6536 0.00703 0.00216 -0.0761 0.3860 0.9999
2.500 0.6789 0.00715 0.00221 -0.0755 0.3749 1.0000
2.750 0.7037 0.00726 0.00227 -0.0749 0.3637 1.0000
3.000 0.7282 0.00741 0.00235 -0.0741 0.3500 1.0000
3.250 0.7523 0.00760 0.00243 -0.0733 0.3308 1.0000
3.500 0.7756 0.00786 0.00255 -0.0724 0.3062 1.0000
3.750 0.7992 0.00809 0.00267 -0.0715 0.2870 1.0000
4.000 0.8232 0.00830 0.00280 -0.0707 0.2744 1.0000
4.250 0.8476 0.00849 0.00293 -0.0700 0.2651 1.0000
4.500 0.8719 0.00867 0.00307 -0.0693 0.2572 1.0000
4.750 0.8967 0.00885 0.00321 -0.0686 0.2506 1.0000
5.000 0.9212 0.00906 0.00337 -0.0680 0.2442 1.0000
5.250 0.9469 0.00918 0.00350 -0.0675 0.2412 1.0000
5.500 0.9724 0.00934 0.00364 -0.0670 0.2371 1.0000
5.750 0.9976 0.00953 0.00381 -0.0665 0.2328 1.0000
6.000 1.0227 0.00973 0.00399 -0.0660 0.2283 1.0000
6.250 1.0490 0.00986 0.00413 -0.0657 0.2254 1.0000
6.500 1.0746 0.01003 0.00430 -0.0653 0.2208 1.0000
6.750 1.0996 0.01026 0.00450 -0.0648 0.2152 1.0000
7.000 1.1255 0.01042 0.00466 -0.0645 0.2111 1.0000
7.250 1.1513 0.01058 0.00483 -0.0642 0.2061 1.0000
7.500 1.1759 0.01084 0.00506 -0.0637 0.1991 1.0000
7.750 1.2016 0.01101 0.00523 -0.0633 0.1912 1.0000
8.000 1.2246 0.01140 0.00548 -0.0626 0.1688 1.0000
8.250 1.2357 0.01275 0.00640 -0.0601 0.1010 1.0000
8.500 1.2541 0.01349 0.00700 -0.0587 0.0769 1.0000
8.750 1.2680 0.01458 0.00782 -0.0566 0.0415 1.0000
9.000 1.2886 0.01509 0.00831 -0.0556 0.0378 1.0000
9.250 1.3092 0.01558 0.00881 -0.0545 0.0353 1.0000
9.500 1.3305 0.01599 0.00926 -0.0535 0.0343 1.0000
9.750 1.3508 0.01645 0.00975 -0.0524 0.0333 1.0000
10.000 1.3698 0.01697 0.01029 -0.0512 0.0322 1.0000
10.250 1.3868 0.01759 0.01094 -0.0496 0.0311 1.0000
10.500 1.4011 0.01822 0.01162 -0.0475 0.0301 1.0000
10.750 1.4174 0.01871 0.01215 -0.0458 0.0297 1.0000
11.000 1.4327 0.01927 0.01276 -0.0440 0.0292 1.0000
11.250 1.4472 0.01989 0.01343 -0.0422 0.0286 1.0000
11.500 1.4608 0.02058 0.01417 -0.0404 0.0280 1.0000
11.750 1.4733 0.02135 0.01499 -0.0385 0.0274 1.0000
12.000 1.4836 0.02230 0.01598 -0.0365 0.0268 1.0000
12.250 1.4900 0.02353 0.01728 -0.0343 0.0262 1.0000
12.500 1.4912 0.02522 0.01906 -0.0319 0.0256 1.0000
12.750 1.5034 0.02621 0.02011 -0.0306 0.0254 1.0000
13.000 1.5147 0.02731 0.02127 -0.0295 0.0250 1.0000
13.250 1.5246 0.02858 0.02261 -0.0284 0.0246 1.0000
13.500 1.5328 0.03004 0.02414 -0.0273 0.0242 1.0000
13.750 1.5396 0.03170 0.02586 -0.0264 0.0237 1.0000
14.000 1.5452 0.03354 0.02777 -0.0255 0.0234 1.0000
14.250 1.5490 0.03563 0.02993 -0.0248 0.0230 1.0000
14.500 1.5510 0.03799 0.03237 -0.0243 0.0227 1.0000
14.750 1.5494 0.04086 0.03532 -0.0239 0.0224 1.0000
15.000 1.5425 0.04444 0.03899 -0.0238 0.0220 1.0000
15.250 1.5290 0.04893 0.04360 -0.0240 0.0217 1.0000
15.500 1.5229 0.05270 0.04747 -0.0243 0.0215 1.0000
15.750 1.5243 0.05563 0.05048 -0.0247 0.0213 1.0000
16.000 1.5236 0.05889 0.05384 -0.0252 0.0211 1.0000
16.250 1.5201 0.06261 0.05765 -0.0259 0.0208 1.0000
16.500 1.5149 0.06661 0.06175 -0.0267 0.0206 1.0000
16.750 1.5089 0.07079 0.06602 -0.0277 0.0204 1.0000
17.000 1.5012 0.07531 0.07064 -0.0289 0.0202 1.0000
17.250 1.4934 0.07986 0.07528 -0.0301 0.0199 1.0000
17.500 1.4854 0.08447 0.07997 -0.0314 0.0197 1.0000
17.750 1.4771 0.08918 0.08476 -0.0327 0.0195 1.0000
18.000 1.4688 0.09392 0.08959 -0.0342 0.0193 1.0000
18.250 1.4602 0.09871 0.09445 -0.0357 0.0192 1.0000
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