GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 500,000 Max Cl/Cd: 86.97 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe285-il-500000-n5.txt Download as CSV file: xf-goe285-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4522 0.12006 0.11742 -0.0228 1.0000 0.0209
-12.000 -0.4458 0.11737 0.11473 -0.0238 1.0000 0.0211
-11.000 -0.7788 0.03767 0.03428 -0.0688 1.0000 0.0238
-10.750 -0.7866 0.03400 0.03025 -0.0669 0.9996 0.0240
-10.500 -0.7671 0.03065 0.02649 -0.0691 0.9959 0.0243
-10.250 -0.7435 0.02836 0.02387 -0.0706 0.9928 0.0244
-10.000 -0.7198 0.02650 0.02175 -0.0715 0.9889 0.0246
-9.750 -0.6950 0.02451 0.01956 -0.0725 0.9856 0.0248
-9.500 -0.6667 0.02313 0.01805 -0.0737 0.9830 0.0251
-9.250 -0.6408 0.02205 0.01686 -0.0741 0.9778 0.0253
-9.000 -0.6114 0.02105 0.01574 -0.0750 0.9740 0.0255
-8.750 -0.5835 0.02017 0.01476 -0.0755 0.9687 0.0258
-8.500 -0.5553 0.01938 0.01387 -0.0760 0.9625 0.0261
-8.250 -0.5260 0.01861 0.01300 -0.0766 0.9570 0.0265
-8.000 -0.4981 0.01784 0.01211 -0.0768 0.9493 0.0268
-7.750 -0.4688 0.01709 0.01124 -0.0773 0.9414 0.0270
-7.500 -0.4392 0.01638 0.01041 -0.0778 0.9306 0.0273
-7.250 -0.4106 0.01575 0.00965 -0.0780 0.9165 0.0276
-7.000 -0.3828 0.01518 0.00897 -0.0779 0.9013 0.0279
-6.750 -0.3559 0.01469 0.00835 -0.0776 0.8864 0.0281
-6.500 -0.3294 0.01425 0.00778 -0.0773 0.8720 0.0283
-6.250 -0.3030 0.01386 0.00728 -0.0769 0.8586 0.0285
-6.000 -0.2767 0.01350 0.00681 -0.0764 0.8447 0.0288
-5.750 -0.2512 0.01298 0.00621 -0.0759 0.8309 0.0292
-5.500 -0.2250 0.01259 0.00575 -0.0755 0.8185 0.0296
-5.250 -0.1986 0.01228 0.00538 -0.0751 0.8063 0.0300
-4.750 -0.1451 0.01176 0.00473 -0.0744 0.7814 0.0312
-4.500 -0.1183 0.01152 0.00442 -0.0741 0.7666 0.0317
-4.250 -0.0915 0.01131 0.00413 -0.0737 0.7505 0.0321
-4.000 -0.0647 0.01113 0.00386 -0.0733 0.7337 0.0326
-3.750 -0.0377 0.01096 0.00361 -0.0730 0.7179 0.0331
-3.500 -0.0107 0.01079 0.00336 -0.0726 0.7011 0.0337
-3.250 0.0160 0.01063 0.00312 -0.0723 0.6830 0.0347
-3.000 0.0430 0.01051 0.00293 -0.0719 0.6671 0.0358
-2.750 0.0702 0.01041 0.00275 -0.0717 0.6539 0.0371
-2.500 0.0974 0.01033 0.00260 -0.0714 0.6399 0.0387
-2.250 0.1244 0.01022 0.00246 -0.0711 0.6251 0.0425
-2.000 0.1515 0.01011 0.00237 -0.0708 0.6104 0.0529
-1.750 0.1787 0.01006 0.00232 -0.0706 0.5946 0.0672
-1.500 0.2060 0.01005 0.00226 -0.0703 0.5783 0.0752
-1.250 0.2334 0.01002 0.00220 -0.0701 0.5629 0.0816
-1.000 0.2609 0.01002 0.00214 -0.0699 0.5477 0.0872
-0.750 0.2881 0.01001 0.00210 -0.0697 0.5300 0.0940
-0.500 0.3152 0.01003 0.00207 -0.0695 0.5092 0.1012
0.000 0.3687 0.01012 0.00207 -0.0689 0.4679 0.1268
0.250 0.3956 0.01017 0.00208 -0.0687 0.4514 0.1412
1.000 0.4755 0.00997 0.00219 -0.0681 0.4149 0.2933
1.250 0.5006 0.00962 0.00226 -0.0677 0.4047 0.4555
1.500 0.5246 0.00918 0.00234 -0.0671 0.3957 0.6368
1.750 0.5436 0.00857 0.00253 -0.0646 0.3866 0.9210
2.000 0.5993 0.00874 0.00266 -0.0704 0.3734 0.9916
2.250 0.6418 0.00890 0.00275 -0.0737 0.3612 1.0000
2.500 0.6662 0.00906 0.00282 -0.0729 0.3502 1.0000
2.750 0.6908 0.00921 0.00290 -0.0722 0.3379 1.0000
3.000 0.7152 0.00937 0.00299 -0.0714 0.3248 1.0000
3.250 0.7394 0.00956 0.00310 -0.0707 0.3114 1.0000
3.500 0.7634 0.00977 0.00321 -0.0699 0.2980 1.0000
3.750 0.7872 0.01001 0.00336 -0.0691 0.2835 1.0000
4.000 0.8110 0.01026 0.00351 -0.0683 0.2708 1.0000
4.250 0.8355 0.01047 0.00367 -0.0676 0.2613 1.0000
4.500 0.8600 0.01070 0.00384 -0.0670 0.2540 1.0000
4.750 0.8848 0.01090 0.00401 -0.0664 0.2473 1.0000
5.000 0.9093 0.01114 0.00420 -0.0657 0.2411 1.0000
5.250 0.9345 0.01133 0.00438 -0.0652 0.2365 1.0000
5.500 0.9597 0.01152 0.00456 -0.0647 0.2324 1.0000
5.750 0.9846 0.01173 0.00477 -0.0642 0.2286 1.0000
6.000 1.0092 0.01197 0.00499 -0.0636 0.2248 1.0000
6.250 1.0345 0.01216 0.00519 -0.0632 0.2209 1.0000
6.500 1.0596 0.01237 0.00540 -0.0627 0.2165 1.0000
6.750 1.0841 0.01261 0.00564 -0.0622 0.2120 1.0000
7.000 1.1085 0.01287 0.00589 -0.0616 0.2075 1.0000
7.250 1.1336 0.01306 0.00611 -0.0612 0.2028 1.0000
7.500 1.1578 0.01333 0.00637 -0.0606 0.1962 1.0000
7.750 1.1819 0.01359 0.00663 -0.0600 0.1875 1.0000
8.000 1.2053 0.01390 0.00690 -0.0594 0.1745 1.0000
8.250 1.2191 0.01497 0.00758 -0.0574 0.1158 1.0000
8.500 1.2378 0.01563 0.00817 -0.0561 0.1005 1.0000
8.750 1.2569 0.01624 0.00873 -0.0548 0.0880 1.0000
9.000 1.2732 0.01702 0.00941 -0.0532 0.0665 1.0000
9.250 1.2856 0.01806 0.01026 -0.0511 0.0426 1.0000
9.500 1.3030 0.01866 0.01087 -0.0496 0.0388 1.0000
9.750 1.3198 0.01921 0.01145 -0.0480 0.0370 1.0000
10.000 1.3349 0.01980 0.01207 -0.0461 0.0355 1.0000
10.250 1.3490 0.02047 0.01278 -0.0441 0.0342 1.0000
10.500 1.3637 0.02111 0.01347 -0.0424 0.0332 1.0000
10.750 1.3783 0.02177 0.01419 -0.0407 0.0325 1.0000
11.000 1.3919 0.02252 0.01500 -0.0390 0.0319 1.0000
11.250 1.4045 0.02334 0.01589 -0.0372 0.0312 1.0000
11.500 1.4156 0.02430 0.01690 -0.0355 0.0305 1.0000
11.750 1.4253 0.02539 0.01805 -0.0338 0.0298 1.0000
12.000 1.4329 0.02669 0.01941 -0.0320 0.0291 1.0000
12.250 1.4387 0.02819 0.02100 -0.0303 0.0286 1.0000
12.500 1.4484 0.02947 0.02235 -0.0292 0.0282 1.0000
12.750 1.4569 0.03090 0.02387 -0.0281 0.0278 1.0000
13.000 1.4639 0.03252 0.02558 -0.0271 0.0273 1.0000
13.250 1.4698 0.03433 0.02748 -0.0262 0.0268 1.0000
13.500 1.4742 0.03634 0.02958 -0.0254 0.0264 1.0000
13.750 1.4773 0.03858 0.03191 -0.0248 0.0260 1.0000
14.000 1.4792 0.04105 0.03447 -0.0245 0.0256 1.0000
14.250 1.4788 0.04386 0.03737 -0.0243 0.0252 1.0000
14.500 1.4760 0.04705 0.04066 -0.0243 0.0248 1.0000
14.750 1.4705 0.05069 0.04439 -0.0245 0.0245 1.0000
15.000 1.4618 0.05481 0.04862 -0.0250 0.0242 1.0000
15.250 1.4564 0.05866 0.05257 -0.0255 0.0240 1.0000
15.500 1.4529 0.06235 0.05638 -0.0262 0.0237 1.0000
15.750 1.4478 0.06635 0.06050 -0.0270 0.0235 1.0000
16.000 1.4419 0.07055 0.06481 -0.0280 0.0232 1.0000
16.250 1.4355 0.07490 0.06927 -0.0291 0.0230 1.0000
16.500 1.4284 0.07941 0.07388 -0.0303 0.0227 1.0000
16.750 1.4207 0.08401 0.07859 -0.0316 0.0224 1.0000
17.000 1.4133 0.08863 0.08330 -0.0329 0.0221 1.0000
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