GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 200,000 Max Cl/Cd: 74.59 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe488-il-200000.txt Download as CSV file: xf-goe488-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3232 0.08401 0.08063 -0.0284 1.0000 0.0477
-8.250 -0.3229 0.08109 0.07774 -0.0280 1.0000 0.0491
-8.000 -0.4353 0.08955 0.08614 -0.0312 1.0000 0.0449
-7.750 -0.4172 0.08639 0.08296 -0.0260 1.0000 0.0469
-7.500 -0.4204 0.08431 0.08093 -0.0244 1.0000 0.0481
-7.250 -0.4243 0.08193 0.07859 -0.0238 1.0000 0.0490
-7.000 -0.4287 0.07955 0.07625 -0.0233 1.0000 0.0501
-6.750 -0.4331 0.07708 0.07382 -0.0230 1.0000 0.0515
-6.500 -0.4365 0.07440 0.07115 -0.0236 1.0000 0.0535
-6.250 -0.4307 0.07152 0.06809 -0.0305 1.0000 0.0563
-6.000 -0.4237 0.06845 0.06485 -0.0318 1.0000 0.0566
-5.750 -0.4280 0.06259 0.05909 -0.0301 1.0000 0.0577
-5.500 -0.4238 0.06033 0.05686 -0.0275 1.0000 0.0588
-5.250 -0.4168 0.05839 0.05493 -0.0256 1.0000 0.0606
-5.000 -0.4063 0.05601 0.05249 -0.0253 1.0000 0.0636
-4.750 -0.3799 0.05091 0.04681 -0.0307 1.0000 0.0707
-4.500 -0.3713 0.04779 0.04379 -0.0292 1.0000 0.0720
-4.250 -0.3477 0.04547 0.04148 -0.0303 0.9976 0.0743
-4.000 -0.3063 0.04148 0.03694 -0.0356 0.9942 0.0854
-3.750 -0.2811 0.03913 0.03469 -0.0368 0.9904 0.0880
-3.500 -0.2415 0.03629 0.03137 -0.0406 0.9859 0.0999
-3.250 -0.2082 0.03399 0.02914 -0.0430 0.9819 0.1032
-3.000 -0.1730 0.03176 0.02659 -0.0454 0.9758 0.1156
-2.750 -0.1355 0.03014 0.02480 -0.0481 0.9718 0.1298
-2.500 -0.0884 0.02313 0.01624 -0.0487 0.9702 0.0704
-2.250 -0.0606 0.02069 0.01359 -0.0488 0.9648 0.0678
-2.000 -0.0230 0.01917 0.01179 -0.0505 0.9602 0.0667
-1.750 0.0195 0.01820 0.01058 -0.0531 0.9569 0.0680
-1.500 0.0502 0.01747 0.00971 -0.0534 0.9503 0.0689
-1.250 0.0893 0.01659 0.00875 -0.0554 0.9455 0.0694
-1.000 0.1335 0.01565 0.00778 -0.0584 0.9422 0.0709
-0.750 0.1631 0.01487 0.00707 -0.0585 0.9341 0.0739
-0.500 0.2067 0.01422 0.00649 -0.0614 0.9295 0.0796
-0.250 0.2432 0.01364 0.00599 -0.0628 0.9227 0.0909
0.000 0.2810 0.01280 0.00554 -0.0645 0.9170 0.1605
0.250 0.3715 0.01039 0.00539 -0.0774 0.9216 1.0000
0.500 0.4113 0.01017 0.00507 -0.0794 0.9154 1.0000
0.750 0.4433 0.01000 0.00484 -0.0798 0.9061 1.0000
1.000 0.4821 0.00972 0.00451 -0.0814 0.8986 1.0000
1.250 0.5088 0.00958 0.00434 -0.0806 0.8863 1.0000
1.500 0.5361 0.00944 0.00417 -0.0799 0.8734 1.0000
1.750 0.5633 0.00929 0.00399 -0.0791 0.8587 1.0000
2.000 0.5907 0.00913 0.00379 -0.0783 0.8408 1.0000
2.250 0.6140 0.00901 0.00362 -0.0766 0.8141 1.0000
2.500 0.6372 0.00893 0.00344 -0.0748 0.7790 1.0000
2.750 0.6592 0.00894 0.00333 -0.0729 0.7316 1.0000
3.000 0.6803 0.00912 0.00318 -0.0707 0.6583 1.0000
3.250 0.6973 0.00965 0.00323 -0.0681 0.5783 1.0000
3.500 0.7135 0.01024 0.00342 -0.0655 0.5036 1.0000
3.750 0.7314 0.01079 0.00367 -0.0635 0.4551 1.0000
4.000 0.7514 0.01127 0.00396 -0.0619 0.4245 1.0000
4.250 0.7725 0.01173 0.00427 -0.0606 0.4031 1.0000
4.500 0.7948 0.01212 0.00458 -0.0595 0.3851 1.0000
4.750 0.8174 0.01250 0.00492 -0.0585 0.3696 1.0000
5.000 0.8399 0.01286 0.00526 -0.0574 0.3527 1.0000
5.250 0.8622 0.01322 0.00559 -0.0564 0.3351 1.0000
5.500 0.8841 0.01357 0.00590 -0.0553 0.3165 1.0000
5.750 0.9063 0.01387 0.00620 -0.0542 0.2965 1.0000
6.000 0.9288 0.01413 0.00651 -0.0532 0.2765 1.0000
6.250 0.9509 0.01443 0.00680 -0.0521 0.2555 1.0000
6.500 0.9730 0.01472 0.00707 -0.0511 0.2248 1.0000
6.750 0.9932 0.01523 0.00741 -0.0498 0.1843 1.0000
7.000 1.0119 0.01598 0.00798 -0.0484 0.1442 1.0000
7.250 1.0261 0.01738 0.00888 -0.0464 0.0679 1.0000
7.500 1.0380 0.01910 0.01043 -0.0438 0.0432 1.0000
7.750 1.0570 0.01991 0.01133 -0.0422 0.0362 1.0000
8.000 1.0723 0.02106 0.01254 -0.0401 0.0327 1.0000
8.250 1.0887 0.02206 0.01365 -0.0382 0.0307 1.0000
8.500 1.1040 0.02316 0.01486 -0.0361 0.0292 1.0000
8.750 1.1184 0.02438 0.01614 -0.0340 0.0280 1.0000
9.000 1.1320 0.02581 0.01762 -0.0319 0.0270 1.0000
9.250 1.1449 0.02816 0.02000 -0.0299 0.0258 1.0000
9.500 1.1625 0.02945 0.02144 -0.0284 0.0250 1.0000
9.750 1.1798 0.03118 0.02334 -0.0269 0.0243 1.0000
10.000 1.1968 0.03332 0.02571 -0.0254 0.0239 1.0000
10.250 1.2124 0.03576 0.02841 -0.0238 0.0238 1.0000
10.500 1.2245 0.03850 0.03145 -0.0219 0.0238 1.0000
10.750 1.2318 0.04158 0.03487 -0.0195 0.0240 1.0000
11.000 1.2340 0.04484 0.03845 -0.0167 0.0243 1.0000
11.250 1.2302 0.04809 0.04200 -0.0134 0.0247 1.0000
11.500 1.2218 0.05156 0.04574 -0.0100 0.0250 1.0000
11.750 1.2105 0.05560 0.05003 -0.0070 0.0254 1.0000
12.000 1.2084 0.05936 0.05397 -0.0052 0.0260 1.0000
12.250 1.1980 0.06120 0.05605 -0.0025 0.0265 1.0000
12.500 1.1669 0.06532 0.06059 -0.0006 0.0274 1.0000
12.750 1.1293 0.07150 0.06714 -0.0014 0.0281 1.0000
13.000 1.0992 0.07825 0.07414 -0.0043 0.0284 1.0000
13.250 1.0720 0.08582 0.08190 -0.0091 0.0286 1.0000
13.500 1.0454 0.09465 0.09090 -0.0155 0.0286 1.0000
13.750 1.0135 0.10633 0.10272 -0.0243 0.0287 1.0000
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Polar data table (+)
Polar graphs
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