GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.76 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe499-il-1000000.txt Download as CSV file: xf-goe499-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 499 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2628 0.11336 0.11168 -0.0571 0.9921 0.0117
-10.250 -0.2509 0.10943 0.10775 -0.0603 0.9902 0.0117
-10.000 -0.2413 0.10499 0.10331 -0.0624 0.9886 0.0121
-9.750 -0.2264 0.10202 0.10033 -0.0651 0.9870 0.0124
-9.500 -0.2106 0.09910 0.09742 -0.0682 0.9855 0.0130
-9.250 -0.1956 0.09538 0.09369 -0.0719 0.9841 0.0131
-9.000 -0.1812 0.09208 0.09038 -0.0752 0.9811 0.0151
-8.750 -0.1684 0.08775 0.08605 -0.0806 0.9763 0.0158
-8.500 -0.1524 0.08344 0.08174 -0.0853 0.9733 0.0158
-8.250 -0.1335 0.07887 0.07716 -0.0908 0.9711 0.0158
-7.750 -0.0995 0.06845 0.06671 -0.1036 0.9600 0.0166
-7.500 -0.0717 0.06698 0.06522 -0.1070 0.9568 0.0175
-7.250 -0.0470 0.06458 0.06278 -0.1127 0.9465 0.0212
-7.000 -0.0280 0.06097 0.05912 -0.1178 0.9361 0.0214
-6.750 -0.0123 0.05693 0.05503 -0.1227 0.9257 0.0215
-6.500 0.0028 0.05256 0.05060 -0.1278 0.9150 0.0215
-6.250 0.0194 0.04737 0.04535 -0.1343 0.9046 0.0217
-6.000 0.0619 0.01833 0.01511 -0.1732 0.8908 0.0230
-5.750 0.0883 0.01842 0.01524 -0.1733 0.8866 0.0240
-5.500 0.1138 0.01919 0.01612 -0.1727 0.8823 0.0255
-5.250 0.1428 0.01741 0.01407 -0.1743 0.8778 0.0268
-5.000 0.1727 0.01499 0.01127 -0.1761 0.8738 0.0271
-4.750 0.2015 0.01374 0.00978 -0.1769 0.8697 0.0279
-4.500 0.2295 0.01333 0.00926 -0.1771 0.8653 0.0289
-4.250 0.2582 0.01268 0.00835 -0.1776 0.8614 0.0308
-4.000 0.2867 0.01182 0.00732 -0.1781 0.8578 0.0307
-3.750 0.3149 0.01125 0.00666 -0.1783 0.8537 0.0305
-3.500 0.3430 0.01073 0.00605 -0.1784 0.8495 0.0303
-3.250 0.3712 0.01026 0.00547 -0.1785 0.8456 0.0301
-3.000 0.3997 0.00925 0.00432 -0.1789 0.8417 0.0304
-2.750 0.4279 0.00866 0.00366 -0.1790 0.8374 0.0304
-2.500 0.4563 0.00785 0.00275 -0.1793 0.8331 0.0313
-2.250 0.4847 0.00744 0.00226 -0.1794 0.8290 0.0325
-2.000 0.5129 0.00720 0.00199 -0.1795 0.8250 0.0333
-1.750 0.5410 0.00702 0.00177 -0.1795 0.8210 0.0339
-1.500 0.5692 0.00689 0.00160 -0.1796 0.8170 0.0344
-1.250 0.5973 0.00676 0.00145 -0.1796 0.8130 0.0349
-1.000 0.6253 0.00665 0.00133 -0.1796 0.8085 0.0354
-0.750 0.6531 0.00658 0.00122 -0.1795 0.8032 0.0366
-0.500 0.6809 0.00650 0.00113 -0.1794 0.7972 0.0379
-0.250 0.7086 0.00644 0.00104 -0.1793 0.7914 0.0398
0.000 0.7365 0.00628 0.00099 -0.1793 0.7856 0.0877
0.250 0.7642 0.00608 0.00101 -0.1794 0.7782 0.1749
0.500 0.7916 0.00602 0.00105 -0.1793 0.7704 0.2198
0.750 0.8187 0.00599 0.00107 -0.1791 0.7614 0.2492
1.000 0.8460 0.00596 0.00111 -0.1790 0.7522 0.2798
1.250 0.8730 0.00593 0.00115 -0.1788 0.7423 0.3184
1.500 0.8993 0.00580 0.00126 -0.1785 0.7241 0.4382
1.750 0.9229 0.00585 0.00139 -0.1777 0.6832 0.5541
2.000 0.9434 0.00616 0.00158 -0.1762 0.6176 0.6344
2.250 0.9605 0.00611 0.00186 -0.1740 0.5500 1.0000
2.500 0.9825 0.00660 0.00211 -0.1729 0.5019 1.0000
2.750 1.0047 0.00710 0.00235 -0.1719 0.4535 1.0000
3.000 1.0278 0.00752 0.00257 -0.1710 0.4150 1.0000
3.250 1.0482 0.00817 0.00286 -0.1697 0.3428 1.0000
3.500 1.0514 0.01060 0.00403 -0.1657 0.0898 1.0000
3.750 1.0710 0.01148 0.00459 -0.1642 0.0190 1.0000
4.000 1.0957 0.01177 0.00490 -0.1636 0.0172 1.0000
4.250 1.1199 0.01212 0.00528 -0.1628 0.0155 1.0000
4.500 1.1433 0.01256 0.00573 -0.1619 0.0141 1.0000
4.750 1.1638 0.01331 0.00659 -0.1605 0.0128 1.0000
5.000 1.1869 0.01372 0.00703 -0.1596 0.0122 1.0000
5.250 1.2101 0.01412 0.00744 -0.1587 0.0114 1.0000
5.500 1.2316 0.01467 0.00803 -0.1575 0.0107 1.0000
5.750 1.2523 0.01526 0.00866 -0.1562 0.0102 1.0000
6.000 1.2722 0.01591 0.00936 -0.1548 0.0097 1.0000
6.250 1.2906 0.01666 0.01014 -0.1531 0.0093 1.0000
6.500 1.3044 0.01785 0.01138 -0.1507 0.0089 1.0000
6.750 1.3129 0.01994 0.01356 -0.1473 0.0084 1.0000
7.000 1.3334 0.02050 0.01417 -0.1460 0.0081 1.0000
7.250 1.3523 0.02153 0.01526 -0.1444 0.0079 1.0000
7.500 1.3719 0.02246 0.01627 -0.1430 0.0076 1.0000
7.750 1.3920 0.02359 0.01747 -0.1417 0.0073 1.0000
8.000 1.4148 0.02525 0.01922 -0.1408 0.0072 1.0000
8.250 1.4396 0.02718 0.02127 -0.1403 0.0071 1.0000
8.500 1.4647 0.02940 0.02364 -0.1398 0.0070 1.0000
8.750 1.4874 0.03185 0.02629 -0.1389 0.0069 1.0000
9.000 1.5079 0.03590 0.03068 -0.1373 0.0071 1.0000
9.500 1.5151 0.05046 0.04605 -0.1310 0.0084 1.0000
9.750 1.5161 0.05338 0.04924 -0.1274 0.0083 1.0000
10.000 1.5148 0.05587 0.05197 -0.1235 0.0083 1.0000
10.250 1.5251 0.05532 0.05163 -0.1200 0.0076 1.0000
10.500 1.5169 0.05809 0.05462 -0.1152 0.0073 1.0000
10.750 1.5036 0.06088 0.05759 -0.1102 0.0071 1.0000
11.000 1.4888 0.06401 0.06091 -0.1059 0.0070 1.0000
11.250 1.4726 0.06750 0.06457 -0.1022 0.0069 1.0000
11.500 1.4551 0.07134 0.06859 -0.0993 0.0068 1.0000
11.750 1.4368 0.07557 0.07299 -0.0971 0.0068 1.0000
12.000 1.4163 0.08041 0.07799 -0.0957 0.0067 1.0000
12.250 1.3943 0.08589 0.08363 -0.0952 0.0067 1.0000
12.500 1.3729 0.09172 0.08963 -0.0957 0.0067 1.0000
12.750 1.3498 0.09835 0.09641 -0.0973 0.0067 1.0000
13.000 1.3249 0.10605 0.10426 -0.1004 0.0068 1.0000
13.250 1.3012 0.11439 0.11274 -0.1048 0.0068 1.0000
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Polar data table (+)
Polar graphs
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