GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.87 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe499-il-1000000-n5.txt Download as CSV file: xf-goe499-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2707 0.10641 0.10472 -0.0625 0.9806 0.0046
-10.500 -0.2602 0.10252 0.10083 -0.0656 0.9781 0.0048
-9.500 -0.3243 0.02033 0.01762 -0.1675 0.9091 0.0059
-9.250 -0.2979 0.01692 0.01377 -0.1714 0.9033 0.0063
-9.000 -0.2709 0.01528 0.01182 -0.1730 0.8985 0.0067
-8.750 -0.2438 0.01400 0.01035 -0.1742 0.8941 0.0079
-8.500 -0.2165 0.01291 0.00907 -0.1751 0.8894 0.0090
-8.250 -0.1890 0.01238 0.00846 -0.1755 0.8852 0.0110
-8.000 -0.1611 0.01323 0.00950 -0.1749 0.8817 0.0127
-7.750 -0.1335 0.01322 0.00948 -0.1749 0.8778 0.0144
-7.500 -0.1058 0.01382 0.01015 -0.1745 0.8738 0.0160
-7.250 -0.0781 0.01398 0.01027 -0.1745 0.8701 0.0175
-7.000 -0.0504 0.01389 0.01011 -0.1746 0.8663 0.0189
-6.750 -0.0228 0.01381 0.00995 -0.1747 0.8619 0.0201
-6.500 0.0046 0.01397 0.01007 -0.1746 0.8571 0.0210
-6.250 0.0321 0.01399 0.01004 -0.1746 0.8523 0.0215
-6.000 0.0596 0.01416 0.01017 -0.1745 0.8474 0.0219
-5.750 0.0871 0.01443 0.01040 -0.1743 0.8431 0.0222
-5.500 0.1155 0.01223 0.00783 -0.1760 0.8391 0.0236
-5.250 0.1434 0.01149 0.00697 -0.1765 0.8345 0.0245
-5.000 0.1713 0.01099 0.00636 -0.1767 0.8301 0.0250
-4.750 0.1993 0.01050 0.00576 -0.1770 0.8263 0.0252
-4.500 0.2275 0.01000 0.00514 -0.1773 0.8220 0.0254
-4.250 0.2556 0.00955 0.00459 -0.1774 0.8175 0.0255
-4.000 0.2836 0.00915 0.00408 -0.1776 0.8133 0.0255
-3.750 0.3118 0.00883 0.00370 -0.1778 0.8091 0.0258
-3.500 0.3399 0.00847 0.00326 -0.1779 0.8049 0.0257
-3.250 0.3680 0.00815 0.00285 -0.1780 0.8009 0.0255
-3.000 0.3963 0.00787 0.00251 -0.1781 0.7967 0.0253
-2.750 0.4244 0.00763 0.00221 -0.1782 0.7916 0.0251
-2.500 0.4523 0.00745 0.00196 -0.1782 0.7861 0.0250
-2.250 0.4804 0.00728 0.00175 -0.1783 0.7801 0.0249
-2.000 0.5084 0.00714 0.00155 -0.1783 0.7744 0.0249
-1.750 0.5364 0.00702 0.00139 -0.1783 0.7700 0.0249
-1.500 0.5646 0.00690 0.00125 -0.1784 0.7652 0.0249
-1.250 0.5925 0.00681 0.00112 -0.1784 0.7599 0.0251
-1.000 0.6203 0.00674 0.00101 -0.1783 0.7529 0.0255
-0.750 0.6474 0.00670 0.00091 -0.1782 0.7410 0.0265
-0.500 0.6745 0.00669 0.00086 -0.1779 0.7272 0.0286
-0.250 0.7012 0.00671 0.00083 -0.1777 0.7097 0.0313
0.000 0.7269 0.00681 0.00083 -0.1772 0.6844 0.0330
0.250 0.7521 0.00695 0.00086 -0.1766 0.6543 0.0360
0.500 0.7763 0.00718 0.00094 -0.1759 0.6139 0.0442
0.750 0.8002 0.00737 0.00107 -0.1752 0.5693 0.1006
1.000 0.8249 0.00757 0.00120 -0.1747 0.5365 0.1253
1.250 0.8502 0.00771 0.00135 -0.1743 0.5122 0.1676
1.500 0.8742 0.00800 0.00153 -0.1736 0.4749 0.1955
1.750 0.8981 0.00828 0.00174 -0.1730 0.4388 0.2345
2.000 0.9239 0.00839 0.00190 -0.1727 0.4206 0.2816
2.250 0.9492 0.00851 0.00207 -0.1723 0.3988 0.3437
2.500 0.9733 0.00870 0.00232 -0.1718 0.3615 0.4518
2.750 0.9879 0.00989 0.00292 -0.1697 0.2233 0.4976
3.000 1.0050 0.01095 0.00353 -0.1680 0.1077 0.5351
3.250 1.0247 0.01174 0.00405 -0.1666 0.0196 0.5781
3.500 1.0499 0.01187 0.00432 -0.1662 0.0157 0.6471
4.000 1.0968 0.01180 0.00489 -0.1645 0.0107 1.0000
4.250 1.1215 0.01208 0.00517 -0.1639 0.0097 1.0000
4.500 1.1459 0.01238 0.00549 -0.1633 0.0087 1.0000
4.750 1.1696 0.01275 0.00585 -0.1625 0.0076 1.0000
5.000 1.1928 0.01316 0.00630 -0.1617 0.0067 1.0000
5.250 1.2163 0.01352 0.00669 -0.1609 0.0063 1.0000
5.500 1.2393 0.01392 0.00711 -0.1601 0.0058 1.0000
5.750 1.2619 0.01433 0.00755 -0.1591 0.0054 1.0000
6.000 1.2842 0.01476 0.00799 -0.1582 0.0051 1.0000
6.250 1.3051 0.01532 0.00859 -0.1570 0.0047 1.0000
6.500 1.3234 0.01610 0.00944 -0.1553 0.0044 1.0000
6.750 1.3441 0.01660 0.00999 -0.1541 0.0042 1.0000
7.000 1.3640 0.01715 0.01059 -0.1527 0.0039 1.0000
7.250 1.3831 0.01774 0.01122 -0.1513 0.0037 1.0000
7.500 1.4006 0.01843 0.01197 -0.1495 0.0035 1.0000
7.750 1.4169 0.01912 0.01272 -0.1476 0.0033 1.0000
8.000 1.4322 0.01977 0.01341 -0.1454 0.0032 1.0000
8.250 1.4463 0.02048 0.01420 -0.1431 0.0031 1.0000
8.500 1.4600 0.02123 0.01500 -0.1408 0.0030 1.0000
8.750 1.4724 0.02209 0.01592 -0.1384 0.0029 1.0000
9.000 1.4811 0.02333 0.01725 -0.1354 0.0028 1.0000
9.250 1.4884 0.02486 0.01891 -0.1323 0.0027 1.0000
9.500 1.5002 0.02602 0.02017 -0.1300 0.0026 1.0000
9.750 1.5113 0.02733 0.02161 -0.1277 0.0026 1.0000
10.000 1.5219 0.02886 0.02327 -0.1254 0.0025 1.0000
10.250 1.5322 0.03069 0.02527 -0.1230 0.0024 1.0000
10.500 1.5424 0.03303 0.02783 -0.1208 0.0023 1.0000
11.000 1.5559 0.04427 0.04000 -0.1154 0.0020 1.0000
11.250 1.5535 0.04754 0.04351 -0.1121 0.0019 1.0000
11.500 1.5473 0.05096 0.04716 -0.1087 0.0018 1.0000
11.750 1.5348 0.05529 0.05175 -0.1052 0.0018 1.0000
12.000 1.5235 0.05913 0.05584 -0.1023 0.0018 1.0000
12.250 1.5072 0.06384 0.06078 -0.0997 0.0018 1.0000
12.500 1.4876 0.06910 0.06626 -0.0977 0.0017 1.0000
12.750 1.4604 0.07583 0.07321 -0.0963 0.0017 1.0000
13.000 1.4409 0.08151 0.07908 -0.0961 0.0017 1.0000
13.250 1.4181 0.08814 0.08590 -0.0969 0.0017 1.0000
13.500 1.3867 0.09701 0.09499 -0.0994 0.0018 1.0000
13.750 1.3651 0.10472 0.10285 -0.1026 0.0018 1.0000
14.000 1.3407 0.11396 0.11225 -0.1075 0.0018 1.0000
14.250 1.3066 0.12704 0.12553 -0.1154 0.0018 1.0000
14.500 1.2827 0.13897 0.13760 -0.1234 0.0018 1.0000
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Polar data table (+)
Polar graphs
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