GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.12 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe490-il-1000000.txt Download as CSV file: xf-goe490-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3031 0.12922 0.12762 -0.0252 1.0000 0.0131
-12.250 -0.3070 0.12482 0.12322 -0.0269 1.0000 0.0140
-10.500 -0.8134 0.02716 0.02455 -0.0623 0.9976 0.0100
-10.250 -0.7887 0.02392 0.02095 -0.0645 0.9955 0.0103
-10.000 -0.7594 0.02229 0.01910 -0.0662 0.9942 0.0106
-9.750 -0.7370 0.01999 0.01647 -0.0667 0.9913 0.0109
-9.500 -0.7111 0.01823 0.01449 -0.0676 0.9888 0.0117
-9.250 -0.6795 0.01768 0.01388 -0.0687 0.9872 0.0122
-9.000 -0.6474 0.01712 0.01324 -0.0699 0.9859 0.0128
-8.750 -0.6152 0.01648 0.01250 -0.0712 0.9848 0.0134
-8.500 -0.5821 0.01593 0.01183 -0.0725 0.9839 0.0140
-8.250 -0.5591 0.01481 0.01053 -0.0719 0.9796 0.0147
-8.000 -0.5278 0.01459 0.01032 -0.0727 0.9772 0.0156
-7.750 -0.4950 0.01439 0.01011 -0.0738 0.9754 0.0164
-7.500 -0.4609 0.01413 0.00980 -0.0751 0.9739 0.0173
-7.250 -0.4254 0.01391 0.00952 -0.0767 0.9726 0.0182
-7.000 -0.3923 0.01284 0.00830 -0.0781 0.9713 0.0194
-6.750 -0.3678 0.01256 0.00802 -0.0774 0.9649 0.0203
-6.500 -0.3348 0.01239 0.00784 -0.0784 0.9622 0.0213
-6.250 -0.3005 0.01216 0.00757 -0.0798 0.9600 0.0226
-6.000 -0.2646 0.01192 0.00728 -0.0814 0.9582 0.0236
-5.750 -0.2367 0.01184 0.00715 -0.0812 0.9511 0.0240
-5.500 -0.2057 0.01044 0.00561 -0.0822 0.9461 0.0261
-5.250 -0.1728 0.01012 0.00527 -0.0833 0.9395 0.0273
-5.000 -0.1382 0.00979 0.00489 -0.0847 0.9321 0.0286
-4.750 -0.1055 0.00949 0.00452 -0.0856 0.9225 0.0298
-4.500 -0.0728 0.00929 0.00426 -0.0866 0.9124 0.0308
-4.250 -0.0426 0.00911 0.00399 -0.0869 0.9015 0.0312
-4.000 -0.0173 0.00847 0.00323 -0.0863 0.8895 0.0327
-3.750 0.0088 0.00813 0.00281 -0.0858 0.8776 0.0341
-3.500 0.0350 0.00791 0.00253 -0.0852 0.8650 0.0355
-3.250 0.0610 0.00774 0.00228 -0.0847 0.8521 0.0366
-3.000 0.0868 0.00760 0.00207 -0.0840 0.8386 0.0380
-2.750 0.1125 0.00749 0.00190 -0.0834 0.8252 0.0394
-2.500 0.1381 0.00742 0.00174 -0.0827 0.8108 0.0404
-2.250 0.1632 0.00728 0.00153 -0.0819 0.7956 0.0437
-2.000 0.1882 0.00716 0.00139 -0.0811 0.7802 0.0498
-1.750 0.2122 0.00694 0.00128 -0.0802 0.7650 0.0928
-1.500 0.2372 0.00689 0.00125 -0.0794 0.7488 0.1154
-1.250 0.2620 0.00690 0.00121 -0.0787 0.7297 0.1270
-0.750 0.3115 0.00696 0.00115 -0.0770 0.6890 0.1456
-0.500 0.3364 0.00697 0.00111 -0.0763 0.6704 0.1555
-0.250 0.3611 0.00699 0.00109 -0.0755 0.6513 0.1680
0.000 0.3857 0.00699 0.00108 -0.0747 0.6323 0.1877
0.250 0.4101 0.00696 0.00111 -0.0739 0.6118 0.2296
0.500 0.4346 0.00702 0.00115 -0.0731 0.5898 0.2602
0.750 0.4595 0.00708 0.00118 -0.0724 0.5668 0.2843
1.000 0.4836 0.00717 0.00122 -0.0716 0.5393 0.3035
1.250 0.5077 0.00728 0.00125 -0.0707 0.5107 0.3188
1.500 0.5315 0.00738 0.00130 -0.0699 0.4845 0.3401
1.750 0.5429 0.00654 0.00139 -0.0667 0.4651 0.7190
2.000 0.6190 0.00637 0.00173 -0.0774 0.4391 0.9839
2.250 0.6668 0.00658 0.00184 -0.0818 0.4230 0.9924
2.500 0.7109 0.00674 0.00193 -0.0855 0.4096 0.9969
2.750 0.7546 0.00688 0.00199 -0.0891 0.3969 1.0000
3.000 0.7783 0.00698 0.00206 -0.0882 0.3875 1.0000
3.250 0.8015 0.00710 0.00214 -0.0871 0.3755 1.0000
3.500 0.8245 0.00724 0.00223 -0.0861 0.3631 1.0000
3.750 0.8468 0.00742 0.00232 -0.0849 0.3436 1.0000
4.000 0.8682 0.00765 0.00243 -0.0836 0.3177 1.0000
4.250 0.8895 0.00789 0.00257 -0.0822 0.2950 1.0000
4.500 0.9095 0.00821 0.00274 -0.0807 0.2651 1.0000
4.750 0.9298 0.00852 0.00293 -0.0792 0.2408 1.0000
5.000 0.9505 0.00880 0.00313 -0.0778 0.2221 1.0000
5.250 0.9713 0.00908 0.00333 -0.0764 0.2044 1.0000
5.500 0.9915 0.00940 0.00355 -0.0749 0.1841 1.0000
5.750 1.0104 0.00981 0.00381 -0.0731 0.1564 1.0000
6.000 1.0288 0.01026 0.00410 -0.0714 0.1305 1.0000
6.250 1.0464 0.01076 0.00445 -0.0695 0.1045 1.0000
6.500 1.0562 0.01182 0.00514 -0.0662 0.0412 1.0000
6.750 1.0711 0.01254 0.00572 -0.0637 0.0162 1.0000
7.000 1.0918 0.01285 0.00607 -0.0623 0.0147 1.0000
7.250 1.1117 0.01321 0.00648 -0.0608 0.0136 1.0000
7.500 1.1309 0.01362 0.00694 -0.0591 0.0127 1.0000
7.750 1.1484 0.01416 0.00753 -0.0572 0.0117 1.0000
8.000 1.1649 0.01476 0.00822 -0.0551 0.0111 1.0000
8.250 1.1836 0.01518 0.00868 -0.0534 0.0108 1.0000
8.500 1.2016 0.01563 0.00918 -0.0517 0.0104 1.0000
8.750 1.2185 0.01614 0.00974 -0.0498 0.0099 1.0000
9.000 1.2350 0.01665 0.01029 -0.0478 0.0094 1.0000
9.250 1.2492 0.01728 0.01096 -0.0455 0.0088 1.0000
9.500 1.2609 0.01792 0.01166 -0.0427 0.0087 1.0000
9.750 1.2635 0.01892 0.01275 -0.0384 0.0083 1.0000
10.000 1.2593 0.02033 0.01428 -0.0332 0.0080 1.0000
10.250 1.2710 0.02099 0.01499 -0.0308 0.0079 1.0000
10.500 1.2799 0.02183 0.01591 -0.0280 0.0078 1.0000
10.750 1.2893 0.02268 0.01682 -0.0256 0.0076 1.0000
11.000 1.2967 0.02369 0.01790 -0.0230 0.0075 1.0000
11.250 1.3040 0.02476 0.01905 -0.0206 0.0073 1.0000
11.500 1.3097 0.02600 0.02037 -0.0183 0.0072 1.0000
11.750 1.3135 0.02746 0.02190 -0.0160 0.0070 1.0000
12.000 1.3185 0.02892 0.02344 -0.0141 0.0069 1.0000
12.250 1.3231 0.03049 0.02509 -0.0124 0.0067 1.0000
12.500 1.3287 0.03205 0.02673 -0.0110 0.0064 1.0000
12.750 1.3323 0.03389 0.02864 -0.0098 0.0062 1.0000
13.000 1.3352 0.03589 0.03072 -0.0087 0.0062 1.0000
13.250 1.3353 0.03825 0.03316 -0.0078 0.0061 1.0000
13.500 1.3371 0.04055 0.03552 -0.0073 0.0060 1.0000
13.750 1.3339 0.04343 0.03847 -0.0067 0.0058 1.0000
14.000 1.3257 0.04691 0.04203 -0.0056 0.0057 1.0000
14.250 1.3166 0.05053 0.04576 -0.0040 0.0055 1.0000
14.500 1.3162 0.05346 0.04881 -0.0045 0.0055 1.0000
14.750 1.3143 0.05648 0.05192 -0.0041 0.0055 1.0000
15.000 1.3120 0.05984 0.05540 -0.0049 0.0055 1.0000
15.250 1.3083 0.06338 0.05905 -0.0055 0.0054 1.0000
15.500 1.3046 0.06725 0.06305 -0.0068 0.0054 1.0000
15.750 1.2982 0.07140 0.06733 -0.0078 0.0053 1.0000
16.000 1.2919 0.07563 0.07168 -0.0089 0.0053 1.0000
16.250 1.2829 0.08039 0.07658 -0.0102 0.0053 1.0000
16.500 1.2755 0.08494 0.08123 -0.0116 0.0053 1.0000
16.750 1.2671 0.09013 0.08656 -0.0141 0.0052 1.0000
17.000 1.2573 0.09515 0.09168 -0.0157 0.0053 1.0000
17.250 1.2459 0.10079 0.09746 -0.0180 0.0053 1.0000
17.500 1.2347 0.10670 0.10349 -0.0208 0.0052 1.0000
17.750 1.2270 0.11218 0.10908 -0.0238 0.0051 1.0000
18.000 1.2100 0.11902 0.11606 -0.0266 0.0052 1.0000
18.250 1.1975 0.12557 0.12273 -0.0301 0.0052 1.0000
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Polar data table (+)
Polar graphs
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