GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 200,000 Max Cl/Cd: 72.46 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe490-il-200000.txt Download as CSV file: xf-goe490-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 490 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3795 0.09863 0.09519 -0.0334 1.0000 0.0511
-8.500 -0.3901 0.09619 0.09284 -0.0344 1.0000 0.0513
-8.250 -0.4012 0.09383 0.09055 -0.0343 1.0000 0.0514
-8.000 -0.3859 0.08823 0.08494 -0.0305 1.0000 0.0531
-7.750 -0.3804 0.08618 0.08291 -0.0283 1.0000 0.0544
-7.500 -0.3842 0.08447 0.08126 -0.0262 1.0000 0.0563
-7.250 -0.3947 0.08255 0.07941 -0.0245 1.0000 0.0579
-7.000 -0.4040 0.08013 0.07705 -0.0241 1.0000 0.0598
-6.750 -0.4143 0.07746 0.07441 -0.0251 1.0000 0.0615
-6.500 -0.4234 0.07351 0.07034 -0.0326 1.0000 0.0634
-6.250 -0.4300 0.06873 0.06561 -0.0306 1.0000 0.0643
-6.000 -0.4292 0.06674 0.06368 -0.0272 1.0000 0.0652
-5.750 -0.4080 0.06427 0.06120 -0.0280 0.9971 0.0674
-5.500 -0.3639 0.05551 0.05197 -0.0428 0.9895 0.0769
-5.250 -0.3380 0.05301 0.04957 -0.0436 0.9854 0.0790
-4.750 -0.2745 0.03350 0.02883 -0.0550 0.9728 0.0599
-4.500 -0.2475 0.02735 0.02190 -0.0563 0.9660 0.0583
-4.250 -0.2138 0.02342 0.01724 -0.0578 0.9607 0.0584
-4.000 -0.1766 0.02132 0.01465 -0.0595 0.9555 0.0607
-3.750 -0.1409 0.01991 0.01284 -0.0607 0.9484 0.0628
-3.500 -0.1005 0.01815 0.01076 -0.0630 0.9450 0.0645
-3.250 -0.0696 0.01713 0.00970 -0.0636 0.9376 0.0676
-3.000 -0.0308 0.01639 0.00889 -0.0655 0.9330 0.0722
-2.750 0.0119 0.01554 0.00790 -0.0681 0.9303 0.0759
-2.500 0.0415 0.01475 0.00719 -0.0683 0.9218 0.0818
-2.250 0.0829 0.01407 0.00655 -0.0707 0.9181 0.0949
-2.000 0.1225 0.01352 0.00609 -0.0727 0.9131 0.1326
-1.750 0.1566 0.01306 0.00572 -0.0738 0.9053 0.1657
-1.500 0.1987 0.01263 0.00533 -0.0764 0.9010 0.1899
-1.250 0.2284 0.01238 0.00515 -0.0766 0.8904 0.2102
-1.000 0.2633 0.01217 0.00498 -0.0777 0.8814 0.2370
-0.750 0.2988 0.01193 0.00477 -0.0789 0.8723 0.2661
-0.500 0.3272 0.01162 0.00455 -0.0787 0.8598 0.2967
-0.250 0.3545 0.01117 0.00426 -0.0783 0.8470 0.3390
0.000 0.3755 0.01029 0.00405 -0.0768 0.8334 0.4969
0.250 0.5079 0.00917 0.00384 -0.0983 0.8243 1.0000
0.500 0.5321 0.00918 0.00370 -0.0970 0.8029 1.0000
0.750 0.5575 0.00921 0.00356 -0.0960 0.7824 1.0000
1.000 0.5803 0.00928 0.00351 -0.0946 0.7608 1.0000
1.250 0.6042 0.00938 0.00346 -0.0934 0.7404 1.0000
1.500 0.6270 0.00949 0.00346 -0.0921 0.7188 1.0000
1.750 0.6497 0.00964 0.00347 -0.0907 0.6968 1.0000
2.000 0.6718 0.00980 0.00350 -0.0892 0.6739 1.0000
2.250 0.6936 0.00998 0.00354 -0.0877 0.6499 1.0000
2.500 0.7146 0.01018 0.00362 -0.0861 0.6244 1.0000
2.750 0.7353 0.01039 0.00369 -0.0844 0.5983 1.0000
3.000 0.7560 0.01062 0.00378 -0.0827 0.5736 1.0000
3.250 0.7769 0.01085 0.00390 -0.0812 0.5504 1.0000
3.500 0.7982 0.01111 0.00406 -0.0797 0.5310 1.0000
3.750 0.8197 0.01136 0.00424 -0.0783 0.5123 1.0000
4.000 0.8412 0.01162 0.00443 -0.0769 0.4949 1.0000
4.250 0.8626 0.01191 0.00464 -0.0756 0.4784 1.0000
4.500 0.8840 0.01220 0.00489 -0.0742 0.4626 1.0000
4.750 0.9053 0.01251 0.00515 -0.0728 0.4470 1.0000
5.000 0.9264 0.01283 0.00543 -0.0714 0.4314 1.0000
5.250 0.9472 0.01316 0.00572 -0.0700 0.4157 1.0000
5.500 0.9675 0.01350 0.00603 -0.0685 0.3989 1.0000
5.750 0.9867 0.01378 0.00630 -0.0668 0.3773 1.0000
6.000 1.0050 0.01409 0.00655 -0.0649 0.3545 1.0000
6.250 1.0237 0.01438 0.00682 -0.0631 0.3305 1.0000
6.500 1.0417 0.01474 0.00713 -0.0613 0.3070 1.0000
6.750 1.0588 0.01516 0.00744 -0.0593 0.2813 1.0000
7.000 1.0767 0.01561 0.00783 -0.0575 0.2588 1.0000
7.250 1.0940 0.01611 0.00826 -0.0557 0.2399 1.0000
7.500 1.1115 0.01662 0.00873 -0.0539 0.2237 1.0000
7.750 1.1294 0.01709 0.00920 -0.0522 0.2047 1.0000
8.000 1.1465 0.01761 0.00968 -0.0504 0.1845 1.0000
8.250 1.1632 0.01817 0.01017 -0.0485 0.1607 1.0000
8.500 1.1768 0.01895 0.01078 -0.0463 0.1289 1.0000
8.750 1.1818 0.02038 0.01177 -0.0429 0.0616 1.0000
9.000 1.1848 0.02188 0.01311 -0.0389 0.0385 1.0000
9.250 1.1926 0.02293 0.01419 -0.0357 0.0322 1.0000
9.500 1.2021 0.02385 0.01520 -0.0328 0.0297 1.0000
9.750 1.2079 0.02501 0.01645 -0.0295 0.0273 1.0000
10.000 1.2125 0.02622 0.01781 -0.0262 0.0262 1.0000
10.250 1.2176 0.02742 0.01915 -0.0232 0.0256 1.0000
10.500 1.2203 0.02880 0.02067 -0.0202 0.0250 1.0000
10.750 1.2220 0.03033 0.02232 -0.0174 0.0246 1.0000
11.000 1.2220 0.03208 0.02421 -0.0147 0.0242 1.0000
11.250 1.2219 0.03397 0.02621 -0.0123 0.0239 1.0000
11.500 1.2224 0.03598 0.02831 -0.0103 0.0236 1.0000
11.750 1.2233 0.03808 0.03051 -0.0085 0.0233 1.0000
12.000 1.2256 0.04020 0.03271 -0.0069 0.0230 1.0000
12.250 1.2279 0.04241 0.03499 -0.0056 0.0224 1.0000
12.500 1.2299 0.04480 0.03741 -0.0043 0.0215 1.0000
12.750 1.2361 0.04721 0.03985 -0.0029 0.0209 1.0000
13.000 1.2451 0.04925 0.04199 -0.0018 0.0210 1.0000
13.250 1.2555 0.05163 0.04449 -0.0006 0.0209 1.0000
13.500 1.2640 0.05415 0.04719 0.0005 0.0209 1.0000
13.750 1.2694 0.05688 0.05010 0.0014 0.0209 1.0000
14.000 1.2708 0.05985 0.05328 0.0021 0.0210 1.0000
14.250 1.2681 0.06311 0.05677 0.0024 0.0212 1.0000
14.500 1.2618 0.06684 0.06076 0.0025 0.0215 1.0000
14.750 1.2516 0.07120 0.06543 0.0020 0.0220 1.0000
15.000 1.2369 0.07638 0.07091 0.0009 0.0225 1.0000
15.250 1.2176 0.08236 0.07718 -0.0011 0.0230 1.0000
15.500 1.1978 0.08875 0.08383 -0.0038 0.0233 1.0000
15.750 1.1775 0.09564 0.09096 -0.0071 0.0236 1.0000
16.000 1.1570 0.10298 0.09850 -0.0111 0.0239 1.0000
16.250 1.1356 0.11092 0.10664 -0.0158 0.0242 1.0000
16.500 1.1152 0.11912 0.11501 -0.0208 0.0245 1.0000
16.750 1.0903 0.12887 0.12494 -0.0271 0.0247 1.0000
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Polar data table (+)
Polar graphs
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