GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 500,000 Max Cl/Cd: 89.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe490-il-500000-n5.txt Download as CSV file: xf-goe490-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4117 0.10405 0.10174 -0.0271 1.0000 0.0083
-10.250 -0.4171 0.09916 0.09688 -0.0284 1.0000 0.0087
-9.750 -0.7026 0.02617 0.02272 -0.0696 0.9893 0.0081
-9.500 -0.6771 0.02354 0.01974 -0.0713 0.9868 0.0084
-9.250 -0.6528 0.02169 0.01763 -0.0719 0.9834 0.0089
-9.000 -0.6274 0.02010 0.01576 -0.0724 0.9798 0.0093
-8.750 -0.5992 0.01878 0.01419 -0.0733 0.9773 0.0098
-8.500 -0.5726 0.01757 0.01281 -0.0737 0.9743 0.0107
-8.250 -0.5464 0.01685 0.01199 -0.0737 0.9699 0.0116
-8.000 -0.5168 0.01619 0.01122 -0.0743 0.9672 0.0128
-7.500 -0.4606 0.01506 0.00990 -0.0748 0.9598 0.0153
-7.250 -0.4306 0.01482 0.00962 -0.0752 0.9560 0.0168
-7.000 -0.3994 0.01441 0.00911 -0.0760 0.9533 0.0185
-6.750 -0.3706 0.01408 0.00868 -0.0762 0.9485 0.0197
-6.500 -0.3413 0.01367 0.00824 -0.0766 0.9427 0.0213
-6.250 -0.3056 0.01344 0.00795 -0.0782 0.9389 0.0230
-6.000 -0.2733 0.01313 0.00756 -0.0792 0.9325 0.0248
-5.750 -0.2383 0.01281 0.00714 -0.0807 0.9265 0.0263
-5.500 -0.2027 0.01254 0.00677 -0.0823 0.9204 0.0273
-5.250 -0.1696 0.01199 0.00611 -0.0835 0.9121 0.0284
-5.000 -0.1374 0.01130 0.00531 -0.0845 0.9027 0.0303
-4.750 -0.1048 0.01092 0.00484 -0.0854 0.8925 0.0317
-4.500 -0.0752 0.01059 0.00442 -0.0857 0.8798 0.0328
-4.250 -0.0468 0.01032 0.00405 -0.0857 0.8659 0.0341
-4.000 -0.0194 0.01007 0.00369 -0.0855 0.8519 0.0352
-3.750 0.0072 0.00984 0.00337 -0.0851 0.8385 0.0360
-3.500 0.0336 0.00966 0.00309 -0.0846 0.8255 0.0367
-3.250 0.0599 0.00949 0.00283 -0.0841 0.8123 0.0373
-3.000 0.0859 0.00936 0.00261 -0.0835 0.7981 0.0378
-2.750 0.1115 0.00922 0.00237 -0.0829 0.7832 0.0388
-2.500 0.1371 0.00909 0.00215 -0.0822 0.7686 0.0407
-2.250 0.1626 0.00899 0.00199 -0.0816 0.7545 0.0435
-2.000 0.1879 0.00890 0.00185 -0.0809 0.7400 0.0486
-1.750 0.2127 0.00875 0.00173 -0.0801 0.7257 0.0679
-1.500 0.2375 0.00864 0.00167 -0.0794 0.7108 0.0980
-1.250 0.2628 0.00862 0.00162 -0.0788 0.6966 0.1123
-1.000 0.2881 0.00861 0.00158 -0.0781 0.6819 0.1248
-0.750 0.3133 0.00862 0.00154 -0.0774 0.6658 0.1341
-0.500 0.3379 0.00865 0.00151 -0.0766 0.6466 0.1437
-0.250 0.3619 0.00869 0.00148 -0.0757 0.6228 0.1542
0.000 0.3856 0.00877 0.00146 -0.0747 0.5968 0.1627
0.500 0.4329 0.00886 0.00151 -0.0729 0.5444 0.2107
0.750 0.4563 0.00895 0.00157 -0.0719 0.5159 0.2505
1.000 0.4799 0.00907 0.00163 -0.0710 0.4894 0.2764
1.250 0.5039 0.00918 0.00169 -0.0702 0.4676 0.2930
1.500 0.5283 0.00927 0.00174 -0.0695 0.4520 0.3092
1.750 0.5528 0.00934 0.00180 -0.0688 0.4373 0.3262
2.000 0.5768 0.00937 0.00188 -0.0680 0.4229 0.3582
3.000 0.7557 0.00876 0.00256 -0.0835 0.3681 1.0000
3.250 0.7786 0.00891 0.00267 -0.0824 0.3575 1.0000
3.500 0.8013 0.00907 0.00278 -0.0813 0.3451 1.0000
3.750 0.8238 0.00925 0.00291 -0.0802 0.3311 1.0000
4.000 0.8462 0.00944 0.00305 -0.0791 0.3156 1.0000
4.250 0.8677 0.00968 0.00320 -0.0778 0.2944 1.0000
4.500 0.8878 0.01002 0.00340 -0.0763 0.2664 1.0000
4.750 0.9059 0.01051 0.00367 -0.0745 0.2293 1.0000
5.000 0.9257 0.01088 0.00393 -0.0730 0.2048 1.0000
5.250 0.9457 0.01125 0.00419 -0.0715 0.1841 1.0000
5.500 0.9657 0.01163 0.00445 -0.0701 0.1618 1.0000
5.750 0.9845 0.01209 0.00477 -0.0684 0.1364 1.0000
6.000 1.0026 0.01260 0.00514 -0.0667 0.1125 1.0000
6.250 1.0206 0.01312 0.00552 -0.0649 0.0873 1.0000
6.500 1.0323 0.01410 0.00622 -0.0621 0.0357 1.0000
6.750 1.0483 0.01477 0.00680 -0.0600 0.0158 1.0000
7.000 1.0682 0.01514 0.00722 -0.0585 0.0131 1.0000
7.250 1.0880 0.01550 0.00766 -0.0570 0.0122 1.0000
7.500 1.1070 0.01592 0.00814 -0.0554 0.0112 1.0000
7.750 1.1251 0.01639 0.00869 -0.0537 0.0102 1.0000
8.000 1.1406 0.01705 0.00945 -0.0515 0.0091 1.0000
8.250 1.1581 0.01753 0.00998 -0.0497 0.0088 1.0000
8.500 1.1746 0.01806 0.01059 -0.0478 0.0083 1.0000
8.750 1.1899 0.01864 0.01126 -0.0457 0.0079 1.0000
9.000 1.2028 0.01924 0.01192 -0.0431 0.0074 1.0000
9.250 1.2139 0.01991 0.01266 -0.0403 0.0072 1.0000
9.500 1.2247 0.02062 0.01343 -0.0376 0.0069 1.0000
9.750 1.2340 0.02142 0.01429 -0.0348 0.0065 1.0000
10.000 1.2367 0.02263 0.01559 -0.0311 0.0062 1.0000
10.250 1.2481 0.02336 0.01640 -0.0289 0.0060 1.0000
10.500 1.2578 0.02421 0.01733 -0.0265 0.0057 1.0000
10.750 1.2633 0.02536 0.01858 -0.0238 0.0056 1.0000
11.000 1.2684 0.02659 0.01992 -0.0213 0.0054 1.0000
11.250 1.2722 0.02798 0.02141 -0.0189 0.0053 1.0000
11.500 1.2749 0.02953 0.02307 -0.0166 0.0052 1.0000
11.750 1.2799 0.03100 0.02463 -0.0149 0.0050 1.0000
12.000 1.2814 0.03285 0.02658 -0.0131 0.0049 1.0000
12.250 1.2825 0.03486 0.02868 -0.0117 0.0048 1.0000
12.500 1.2822 0.03714 0.03106 -0.0105 0.0047 1.0000
12.750 1.2835 0.03939 0.03340 -0.0096 0.0046 1.0000
13.000 1.2812 0.04215 0.03627 -0.0090 0.0046 1.0000
13.250 1.2797 0.04494 0.03917 -0.0086 0.0045 1.0000
13.500 1.2776 0.04794 0.04225 -0.0086 0.0044 1.0000
13.750 1.2737 0.05126 0.04568 -0.0087 0.0044 1.0000
14.000 1.2687 0.05482 0.04935 -0.0089 0.0043 1.0000
14.250 1.2612 0.05879 0.05341 -0.0094 0.0042 1.0000
14.500 1.2543 0.06280 0.05753 -0.0100 0.0042 1.0000
14.750 1.2494 0.06669 0.06157 -0.0108 0.0041 1.0000
15.000 1.2449 0.07069 0.06570 -0.0117 0.0041 1.0000
15.250 1.2409 0.07485 0.07000 -0.0131 0.0040 1.0000
15.500 1.2354 0.07915 0.07442 -0.0144 0.0040 1.0000
15.750 1.2293 0.08369 0.07909 -0.0159 0.0039 1.0000
16.000 1.2216 0.08839 0.08390 -0.0172 0.0040 1.0000
16.250 1.2150 0.09323 0.08888 -0.0191 0.0039 1.0000
16.500 1.2066 0.09851 0.09431 -0.0212 0.0038 1.0000
16.750 1.1977 0.10393 0.09986 -0.0234 0.0037 1.0000
17.000 1.1915 0.10916 0.10521 -0.0260 0.0036 1.0000
17.250 1.1831 0.11459 0.11077 -0.0283 0.0036 1.0000
17.500 1.1746 0.12043 0.11673 -0.0312 0.0035 1.0000
17.750 1.1649 0.12649 0.12292 -0.0342 0.0035 1.0000
18.000 1.1561 0.13258 0.12913 -0.0373 0.0035 1.0000
18.250 1.1451 0.13922 0.13591 -0.0408 0.0035 1.0000
18.500 1.1347 0.14598 0.14279 -0.0445 0.0034 1.0000
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