GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe549-il-1000000.txt Download as CSV file: xf-goe549-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1004 0.09500 0.09323 -0.0753 0.9225 0.0197
-11.250 -0.5468 0.03525 0.03294 -0.1090 0.9560 0.0146
-11.000 -0.5633 0.02599 0.02279 -0.1172 0.9123 0.0148
-10.750 -0.5580 0.02394 0.02044 -0.1156 0.8933 0.0149
-10.500 -0.5459 0.02262 0.01891 -0.1142 0.8798 0.0151
-10.000 -0.5103 0.02106 0.01709 -0.1121 0.8580 0.0153
-9.750 -0.4903 0.02046 0.01637 -0.1111 0.8481 0.0155
-9.500 -0.4693 0.01994 0.01574 -0.1103 0.8377 0.0157
-9.250 -0.4492 0.01919 0.01485 -0.1094 0.8269 0.0160
-9.000 -0.4294 0.01830 0.01380 -0.1084 0.8161 0.0162
-8.750 -0.4082 0.01762 0.01296 -0.1074 0.8040 0.0167
-8.500 -0.3870 0.01684 0.01200 -0.1065 0.7900 0.0172
-8.250 -0.3645 0.01630 0.01130 -0.1056 0.7735 0.0177
-8.000 -0.3402 0.01613 0.01097 -0.1049 0.7525 0.0181
-7.750 -0.3208 0.01516 0.00983 -0.1037 0.7259 0.0189
-7.500 -0.2969 0.01514 0.00970 -0.1030 0.6964 0.0193
-7.250 -0.2725 0.01507 0.00950 -0.1024 0.6754 0.0198
-7.000 -0.2477 0.01495 0.00928 -0.1019 0.6611 0.0205
-6.750 -0.2225 0.01475 0.00897 -0.1014 0.6510 0.0214
-6.500 -0.1961 0.01474 0.00886 -0.1010 0.6434 0.0222
-6.250 -0.1722 0.01407 0.00804 -0.1004 0.6365 0.0231
-6.000 -0.1477 0.01350 0.00744 -0.1000 0.6309 0.0239
-5.750 -0.1215 0.01327 0.00719 -0.0997 0.6258 0.0246
-5.500 -0.0956 0.01304 0.00689 -0.0994 0.6208 0.0254
-5.250 -0.0694 0.01280 0.00659 -0.0990 0.6163 0.0262
-5.000 -0.0427 0.01252 0.00627 -0.0988 0.6124 0.0269
-4.750 -0.0162 0.01227 0.00597 -0.0985 0.6083 0.0275
-4.500 0.0107 0.01220 0.00582 -0.0982 0.6040 0.0280
-4.250 0.0373 0.01196 0.00553 -0.0979 0.6002 0.0285
-4.000 0.0607 0.01098 0.00452 -0.0972 0.5968 0.0298
-3.750 0.0869 0.01068 0.00422 -0.0969 0.5928 0.0309
-3.500 0.1134 0.01050 0.00401 -0.0966 0.5885 0.0320
-3.250 0.1397 0.01029 0.00374 -0.0963 0.5843 0.0325
-3.000 0.1667 0.01004 0.00348 -0.0961 0.5809 0.0330
-2.750 0.1935 0.00981 0.00323 -0.0958 0.5772 0.0333
-2.500 0.2201 0.00963 0.00300 -0.0955 0.5735 0.0336
-2.250 0.2467 0.00950 0.00281 -0.0952 0.5695 0.0339
-2.000 0.2742 0.00931 0.00262 -0.0950 0.5665 0.0343
-1.750 0.3017 0.00917 0.00246 -0.0948 0.5629 0.0348
-1.500 0.3290 0.00907 0.00233 -0.0947 0.5592 0.0353
-1.250 0.3559 0.00898 0.00219 -0.0944 0.5552 0.0358
-1.000 0.3833 0.00886 0.00204 -0.0942 0.5518 0.0371
-0.750 0.4110 0.00875 0.00193 -0.0941 0.5481 0.0391
-0.500 0.4385 0.00868 0.00185 -0.0940 0.5440 0.0411
-0.250 0.4657 0.00866 0.00180 -0.0938 0.5399 0.0442
0.000 0.4918 0.00838 0.00175 -0.0935 0.5362 0.1216
0.250 0.5158 0.00779 0.00172 -0.0930 0.5322 0.3114
0.500 0.5405 0.00746 0.00173 -0.0926 0.5276 0.4339
0.750 0.5651 0.00726 0.00179 -0.0920 0.5231 0.5398
1.000 0.5915 0.00714 0.00184 -0.0917 0.5191 0.6010
1.250 0.6175 0.00705 0.00187 -0.0913 0.5143 0.6501
1.500 0.6428 0.00698 0.00191 -0.0907 0.5091 0.6965
1.750 0.6663 0.00681 0.00196 -0.0897 0.5043 0.7715
2.000 0.7408 0.00650 0.00209 -0.0998 0.4972 0.9850
2.250 0.7842 0.00661 0.00213 -0.1033 0.4894 1.0000
2.500 0.8084 0.00671 0.00216 -0.1025 0.4787 1.0000
2.750 0.8332 0.00680 0.00221 -0.1019 0.4701 1.0000
3.000 0.8572 0.00692 0.00227 -0.1012 0.4619 1.0000
3.250 0.8825 0.00701 0.00234 -0.1006 0.4550 1.0000
3.500 0.9064 0.00715 0.00242 -0.0999 0.4464 1.0000
3.750 0.9312 0.00726 0.00250 -0.0993 0.4369 1.0000
4.000 0.9550 0.00742 0.00259 -0.0985 0.4251 1.0000
4.250 0.9784 0.00760 0.00271 -0.0977 0.4131 1.0000
4.500 1.0016 0.00779 0.00283 -0.0968 0.4004 1.0000
4.750 1.0249 0.00798 0.00296 -0.0960 0.3881 1.0000
5.000 1.0485 0.00816 0.00310 -0.0952 0.3770 1.0000
5.250 1.0721 0.00835 0.00325 -0.0945 0.3694 1.0000
5.500 1.0958 0.00852 0.00339 -0.0938 0.3605 1.0000
5.750 1.1189 0.00873 0.00356 -0.0929 0.3508 1.0000
6.000 1.1413 0.00897 0.00375 -0.0920 0.3404 1.0000
6.250 1.1650 0.00914 0.00391 -0.0913 0.3328 1.0000
6.500 1.1874 0.00938 0.00411 -0.0904 0.3245 1.0000
6.750 1.2109 0.00956 0.00428 -0.0897 0.3178 1.0000
7.000 1.2327 0.00982 0.00451 -0.0887 0.3092 1.0000
7.250 1.2551 0.01004 0.00471 -0.0878 0.3004 1.0000
7.500 1.2769 0.01028 0.00493 -0.0869 0.2939 1.0000
7.750 1.2992 0.01049 0.00514 -0.0860 0.2869 1.0000
8.000 1.3198 0.01077 0.00540 -0.0848 0.2797 1.0000
8.250 1.3406 0.01102 0.00564 -0.0837 0.2703 1.0000
8.500 1.3604 0.01131 0.00591 -0.0824 0.2624 1.0000
8.750 1.3773 0.01168 0.00623 -0.0806 0.2504 1.0000
9.000 1.3911 0.01208 0.00658 -0.0783 0.2364 1.0000
9.250 1.4064 0.01243 0.00690 -0.0762 0.2261 1.0000
9.500 1.4165 0.01299 0.00738 -0.0733 0.2088 1.0000
9.750 1.4283 0.01352 0.00785 -0.0708 0.1949 1.0000
10.000 1.4341 0.01432 0.00854 -0.0675 0.1719 1.0000
10.250 1.4298 0.01565 0.00966 -0.0630 0.1376 1.0000
10.500 1.4139 0.01772 0.01146 -0.0576 0.0923 1.0000
10.750 1.4210 0.01878 0.01249 -0.0554 0.0828 1.0000
11.000 1.4300 0.01979 0.01350 -0.0536 0.0752 1.0000
11.250 1.4368 0.02100 0.01470 -0.0517 0.0668 1.0000
11.500 1.4453 0.02218 0.01588 -0.0501 0.0583 1.0000
11.750 1.4388 0.02451 0.01806 -0.0476 0.0369 1.0000
12.000 1.4404 0.02639 0.01992 -0.0460 0.0282 1.0000
12.250 1.4444 0.02818 0.02174 -0.0448 0.0241 1.0000
12.500 1.4496 0.02995 0.02354 -0.0437 0.0221 1.0000
12.750 1.4548 0.03179 0.02543 -0.0429 0.0208 1.0000
13.000 1.4607 0.03364 0.02734 -0.0422 0.0196 1.0000
13.250 1.4665 0.03556 0.02933 -0.0416 0.0190 1.0000
13.500 1.4705 0.03767 0.03150 -0.0410 0.0182 1.0000
13.750 1.4740 0.03990 0.03380 -0.0405 0.0178 1.0000
14.000 1.4746 0.04249 0.03644 -0.0401 0.0169 1.0000
14.250 1.4743 0.04518 0.03920 -0.0396 0.0163 1.0000
14.500 1.4745 0.04784 0.04195 -0.0393 0.0158 1.0000
14.750 1.4772 0.05029 0.04447 -0.0390 0.0155 1.0000
15.000 1.4786 0.05289 0.04713 -0.0388 0.0152 1.0000
15.250 1.4786 0.05565 0.04997 -0.0386 0.0149 1.0000
15.500 1.4780 0.05855 0.05294 -0.0385 0.0144 1.0000
15.750 1.4764 0.06159 0.05604 -0.0385 0.0140 1.0000
16.000 1.4737 0.06481 0.05935 -0.0385 0.0138 1.0000
16.250 1.4701 0.06816 0.06277 -0.0386 0.0134 1.0000
16.500 1.4649 0.07178 0.06646 -0.0387 0.0130 1.0000
16.750 1.4558 0.07600 0.07076 -0.0391 0.0126 1.0000
17.000 1.4513 0.07964 0.07449 -0.0394 0.0125 1.0000
17.250 1.4505 0.08283 0.07775 -0.0398 0.0123 1.0000
17.500 1.4504 0.08593 0.08092 -0.0402 0.0120 1.0000
17.750 1.4483 0.08936 0.08442 -0.0407 0.0117 1.0000
18.000 1.4435 0.09321 0.08835 -0.0413 0.0116 1.0000
18.250 1.4416 0.09665 0.09186 -0.0420 0.0112 1.0000
18.500 1.4396 0.10013 0.09540 -0.0427 0.0108 1.0000
18.750 1.4351 0.10403 0.09937 -0.0436 0.0105 1.0000
19.000 1.4309 0.10793 0.10333 -0.0445 0.0103 1.0000
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