GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.54 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe490-il-1000000-n5.txt Download as CSV file: xf-goe490-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5083 0.10087 0.09919 -0.0288 1.0000 0.0061
-11.500 -0.5293 0.09316 0.09148 -0.0321 1.0000 0.0063
-11.250 -0.8337 0.02622 0.02326 -0.0747 0.9926 0.0047
-11.000 -0.8119 0.02350 0.02027 -0.0759 0.9900 0.0048
-10.750 -0.7875 0.02128 0.01780 -0.0771 0.9879 0.0049
-10.500 -0.7612 0.01944 0.01575 -0.0783 0.9863 0.0052
-10.250 -0.7380 0.01821 0.01436 -0.0782 0.9832 0.0055
-10.000 -0.7124 0.01719 0.01322 -0.0784 0.9804 0.0057
-9.750 -0.6847 0.01628 0.01217 -0.0789 0.9784 0.0060
-9.500 -0.6554 0.01551 0.01128 -0.0796 0.9768 0.0064
-9.250 -0.6294 0.01483 0.01048 -0.0795 0.9740 0.0067
-9.000 -0.6044 0.01422 0.00977 -0.0791 0.9699 0.0069
-8.750 -0.5768 0.01343 0.00886 -0.0794 0.9673 0.0076
-8.500 -0.5474 0.01278 0.00813 -0.0799 0.9653 0.0083
-8.250 -0.5230 0.01228 0.00756 -0.0793 0.9599 0.0088
-8.000 -0.4945 0.01181 0.00700 -0.0795 0.9557 0.0095
-7.500 -0.4310 0.01089 0.00598 -0.0814 0.9471 0.0122
-7.250 -0.3957 0.01052 0.00559 -0.0830 0.9413 0.0145
-7.000 -0.3588 0.01029 0.00537 -0.0850 0.9348 0.0170
-6.750 -0.3230 0.01009 0.00513 -0.0867 0.9261 0.0187
-6.500 -0.2890 0.00990 0.00487 -0.0880 0.9158 0.0194
-6.250 -0.2579 0.00961 0.00449 -0.0887 0.9043 0.0209
-6.000 -0.2286 0.00947 0.00431 -0.0890 0.8913 0.0223
-5.750 -0.2010 0.00934 0.00411 -0.0888 0.8781 0.0233
-5.500 -0.1743 0.00921 0.00390 -0.0884 0.8647 0.0244
-5.250 -0.1482 0.00909 0.00370 -0.0879 0.8504 0.0255
-5.000 -0.1226 0.00899 0.00351 -0.0873 0.8340 0.0263
-4.750 -0.0971 0.00892 0.00335 -0.0867 0.8163 0.0270
-4.500 -0.0715 0.00886 0.00321 -0.0860 0.8005 0.0274
-4.250 -0.0461 0.00874 0.00301 -0.0854 0.7863 0.0276
-4.000 -0.0214 0.00852 0.00267 -0.0846 0.7712 0.0287
-3.750 0.0033 0.00833 0.00237 -0.0838 0.7552 0.0297
-3.500 0.0285 0.00820 0.00216 -0.0831 0.7408 0.0306
-3.250 0.0540 0.00809 0.00198 -0.0824 0.7273 0.0314
-3.000 0.0795 0.00801 0.00182 -0.0818 0.7142 0.0321
-2.750 0.1051 0.00794 0.00169 -0.0812 0.7005 0.0328
-2.500 0.1306 0.00789 0.00156 -0.0806 0.6859 0.0335
-2.250 0.1563 0.00784 0.00146 -0.0800 0.6723 0.0343
-2.000 0.1823 0.00780 0.00136 -0.0795 0.6594 0.0352
-1.750 0.2080 0.00778 0.00128 -0.0789 0.6450 0.0362
-1.500 0.2335 0.00778 0.00121 -0.0783 0.6284 0.0377
-1.250 0.2586 0.00776 0.00115 -0.0776 0.6086 0.0451
-1.000 0.2821 0.00768 0.00109 -0.0766 0.5827 0.0805
-0.750 0.3061 0.00773 0.00108 -0.0758 0.5507 0.0998
-0.500 0.3297 0.00786 0.00110 -0.0748 0.5105 0.1134
-0.250 0.3539 0.00799 0.00111 -0.0740 0.4785 0.1226
0.000 0.3786 0.00810 0.00114 -0.0734 0.4529 0.1318
0.250 0.4041 0.00815 0.00116 -0.0728 0.4382 0.1399
0.500 0.4300 0.00820 0.00118 -0.0723 0.4264 0.1465
0.750 0.4558 0.00823 0.00120 -0.0719 0.4174 0.1571
1.000 0.4814 0.00826 0.00123 -0.0714 0.4065 0.1723
1.250 0.5068 0.00826 0.00129 -0.0708 0.3949 0.2036
1.500 0.5322 0.00827 0.00136 -0.0703 0.3856 0.2463
1.750 0.5578 0.00832 0.00143 -0.0698 0.3757 0.2681
2.000 0.5834 0.00839 0.00150 -0.0693 0.3622 0.2841
2.250 0.6090 0.00847 0.00156 -0.0688 0.3497 0.2953
2.750 0.6600 0.00862 0.00170 -0.0678 0.3270 0.3205
3.000 0.6844 0.00864 0.00178 -0.0672 0.3135 0.3600
3.750 0.8029 0.00816 0.00247 -0.0758 0.2407 0.9901
4.000 0.8366 0.00849 0.00268 -0.0773 0.2164 0.9957
4.250 0.8701 0.00885 0.00289 -0.0789 0.1896 0.9987
4.500 0.9000 0.00919 0.00310 -0.0795 0.1652 1.0000
4.750 0.9196 0.00956 0.00333 -0.0779 0.1406 1.0000
5.000 0.9396 0.00989 0.00356 -0.0764 0.1217 1.0000
5.250 0.9596 0.01024 0.00380 -0.0749 0.1052 1.0000
5.500 0.9792 0.01061 0.00407 -0.0733 0.0862 1.0000
5.750 0.9935 0.01135 0.00459 -0.0708 0.0406 1.0000
6.000 1.0106 0.01191 0.00504 -0.0688 0.0151 1.0000
6.250 1.0320 0.01216 0.00531 -0.0675 0.0125 1.0000
6.500 1.0530 0.01244 0.00560 -0.0662 0.0112 1.0000
6.750 1.0734 0.01276 0.00595 -0.0647 0.0097 1.0000
7.000 1.0940 0.01307 0.00629 -0.0634 0.0088 1.0000
7.250 1.1148 0.01336 0.00661 -0.0620 0.0081 1.0000
7.500 1.1351 0.01368 0.00695 -0.0607 0.0075 1.0000
7.750 1.1549 0.01403 0.00731 -0.0592 0.0070 1.0000
8.000 1.1733 0.01447 0.00779 -0.0575 0.0064 1.0000
8.250 1.1919 0.01489 0.00825 -0.0559 0.0061 1.0000
8.500 1.2107 0.01528 0.00869 -0.0543 0.0058 1.0000
8.750 1.2294 0.01566 0.00910 -0.0527 0.0055 1.0000
9.000 1.2477 0.01604 0.00951 -0.0511 0.0051 1.0000
9.250 1.2650 0.01648 0.00998 -0.0493 0.0048 1.0000
9.500 1.2809 0.01697 0.01050 -0.0473 0.0046 1.0000
9.750 1.2934 0.01753 0.01110 -0.0447 0.0043 1.0000
10.000 1.3041 0.01816 0.01180 -0.0417 0.0041 1.0000
10.250 1.3171 0.01870 0.01241 -0.0393 0.0040 1.0000
10.500 1.3298 0.01928 0.01305 -0.0369 0.0039 1.0000
10.750 1.3407 0.01997 0.01382 -0.0344 0.0038 1.0000
11.000 1.3519 0.02068 0.01459 -0.0320 0.0037 1.0000
11.250 1.3615 0.02150 0.01549 -0.0295 0.0036 1.0000
11.500 1.3700 0.02241 0.01648 -0.0270 0.0035 1.0000
11.750 1.3814 0.02317 0.01729 -0.0250 0.0034 1.0000
12.000 1.3889 0.02421 0.01841 -0.0228 0.0033 1.0000
12.250 1.3966 0.02528 0.01955 -0.0207 0.0032 1.0000
12.500 1.4037 0.02646 0.02081 -0.0188 0.0031 1.0000
12.750 1.4098 0.02778 0.02221 -0.0170 0.0031 1.0000
13.000 1.4208 0.02877 0.02325 -0.0158 0.0029 1.0000
13.250 1.4213 0.03069 0.02527 -0.0140 0.0029 1.0000
13.500 1.4214 0.03278 0.02745 -0.0125 0.0028 1.0000
13.750 1.4174 0.03540 0.03019 -0.0113 0.0027 1.0000
14.000 1.4158 0.03798 0.03288 -0.0106 0.0027 1.0000
14.250 1.4131 0.04086 0.03586 -0.0102 0.0026 1.0000
14.500 1.4160 0.04322 0.03832 -0.0100 0.0026 1.0000
14.750 1.4093 0.04683 0.04206 -0.0102 0.0026 1.0000
15.000 1.4022 0.05071 0.04606 -0.0107 0.0026 1.0000
15.250 1.3988 0.05424 0.04969 -0.0113 0.0025 1.0000
15.500 1.3897 0.05871 0.05428 -0.0124 0.0025 1.0000
15.750 1.3786 0.06363 0.05932 -0.0138 0.0025 1.0000
16.000 1.3639 0.06924 0.06507 -0.0156 0.0025 1.0000
16.250 1.3515 0.07465 0.07059 -0.0174 0.0025 1.0000
16.500 1.3409 0.07986 0.07592 -0.0192 0.0024 1.0000
16.750 1.3259 0.08578 0.08196 -0.0213 0.0024 1.0000
17.000 1.3178 0.09074 0.08702 -0.0231 0.0024 1.0000
17.250 1.3011 0.09708 0.09346 -0.0255 0.0024 1.0000
17.500 1.2904 0.10257 0.09905 -0.0276 0.0024 1.0000
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