S8025 (8%) (s8025-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 500,000 Max Cl/Cd: 65.14 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8025-il-500000-n5.txt Download as CSV file: xf-s8025-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
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 -0.8789 0.05170 0.04919 -0.0096 1.0000 0.0035
-10.250 -0.9003 0.04587 0.04317 -0.0142 1.0000 0.0035
-10.000 -0.9186 0.04113 0.03814 -0.0142 1.0000 0.0034
-9.750 -0.9236 0.03684 0.03350 -0.0139 1.0000 0.0034
-9.500 -0.9221 0.03279 0.02903 -0.0133 1.0000 0.0034
-9.250 -0.9134 0.02951 0.02536 -0.0124 1.0000 0.0034
-9.000 -0.9002 0.02678 0.02226 -0.0116 1.0000 0.0034
-8.750 -0.8835 0.02456 0.01974 -0.0107 1.0000 0.0034
-8.500 -0.8649 0.02263 0.01753 -0.0099 1.0000 0.0035
-8.250 -0.8445 0.02103 0.01570 -0.0092 1.0000 0.0035
-8.000 -0.8231 0.01961 0.01407 -0.0084 1.0000 0.0036
-7.750 -0.8008 0.01836 0.01264 -0.0077 1.0000 0.0037
-7.500 -0.7777 0.01728 0.01139 -0.0071 1.0000 0.0037
-7.250 -0.7542 0.01630 0.01027 -0.0065 1.0000 0.0039
-7.000 -0.7300 0.01546 0.00931 -0.0059 1.0000 0.0040
-6.750 -0.7054 0.01473 0.00848 -0.0054 1.0000 0.0041
-6.500 -0.6814 0.01378 0.00743 -0.0048 1.0000 0.0044
-6.250 -0.6562 0.01314 0.00672 -0.0043 1.0000 0.0048
-6.000 -0.6307 0.01262 0.00611 -0.0039 1.0000 0.0052
-5.750 -0.6049 0.01213 0.00556 -0.0034 1.0000 0.0058
-5.500 -0.5788 0.01170 0.00506 -0.0030 1.0000 0.0063
-5.250 -0.5531 0.01121 0.00453 -0.0026 1.0000 0.0078
-5.000 -0.5272 0.01077 0.00408 -0.0021 1.0000 0.0110
-4.750 -0.5015 0.01027 0.00362 -0.0016 1.0000 0.0210
-4.500 -0.4758 0.00982 0.00328 -0.0012 1.0000 0.0390
-4.250 -0.4499 0.00947 0.00300 -0.0008 1.0000 0.0558
-4.000 -0.4243 0.00906 0.00274 -0.0004 1.0000 0.0847
-3.750 -0.3984 0.00873 0.00252 0.0000 1.0000 0.1097
-3.500 -0.3725 0.00842 0.00231 0.0004 1.0000 0.1345
-3.250 -0.3466 0.00816 0.00214 0.0008 1.0000 0.1584
-3.000 -0.3121 0.00793 0.00197 -0.0006 0.9810 0.1824
-2.750 -0.2691 0.00768 0.00180 -0.0039 0.9358 0.2163
-2.500 -0.2371 0.00756 0.00165 -0.0044 0.8708 0.2490
-2.250 -0.2127 0.00756 0.00153 -0.0034 0.8110 0.2756
-2.000 -0.1878 0.00751 0.00142 -0.0026 0.7626 0.3122
-1.750 -0.1623 0.00741 0.00131 -0.0020 0.7224 0.3576
-1.500 -0.1364 0.00734 0.00123 -0.0015 0.6830 0.3998
-1.250 -0.1101 0.00731 0.00116 -0.0011 0.6446 0.4354
-1.000 -0.0838 0.00725 0.00110 -0.0007 0.6089 0.4757
-0.750 -0.0574 0.00718 0.00106 -0.0003 0.5756 0.5224
-0.500 -0.0309 0.00713 0.00104 0.0001 0.5457 0.5655
-0.250 -0.0044 0.00707 0.00103 0.0005 0.5191 0.6072
0.000 0.0222 0.00704 0.00102 0.0009 0.4922 0.6461
0.250 0.0487 0.00702 0.00103 0.0013 0.4664 0.6817
0.500 0.0752 0.00701 0.00105 0.0018 0.4419 0.7165
0.750 0.1011 0.00700 0.00108 0.0023 0.4144 0.7569
1.000 0.1265 0.00697 0.00112 0.0031 0.3880 0.8022
1.250 0.1516 0.00695 0.00117 0.0040 0.3662 0.8487
1.500 0.1775 0.00694 0.00123 0.0047 0.3471 0.8957
1.750 0.2102 0.00703 0.00130 0.0040 0.3249 0.9386
2.000 0.2508 0.00715 0.00137 0.0013 0.3035 0.9707
2.250 0.2883 0.00730 0.00144 -0.0007 0.2840 0.9921
2.500 0.3208 0.00747 0.00152 -0.0017 0.2645 1.0000
2.750 0.3467 0.00763 0.00162 -0.0012 0.2459 1.0000
3.000 0.3726 0.00783 0.00172 -0.0008 0.2259 1.0000
3.250 0.3988 0.00801 0.00185 -0.0004 0.2096 1.0000
3.500 0.4251 0.00819 0.00198 0.0000 0.1952 1.0000
3.750 0.4514 0.00840 0.00212 0.0003 0.1795 1.0000
4.000 0.4778 0.00860 0.00228 0.0007 0.1660 1.0000
4.250 0.5043 0.00882 0.00247 0.0010 0.1540 1.0000
4.500 0.5307 0.00904 0.00266 0.0013 0.1419 1.0000
5.000 0.5835 0.00956 0.00309 0.0019 0.1137 1.0000
5.250 0.6098 0.00985 0.00334 0.0022 0.1008 1.0000
5.500 0.6361 0.01014 0.00360 0.0025 0.0890 1.0000
5.750 0.6625 0.01041 0.00388 0.0028 0.0797 1.0000
6.000 0.6887 0.01073 0.00418 0.0031 0.0704 1.0000
6.250 0.7148 0.01109 0.00452 0.0034 0.0613 1.0000
6.500 0.7409 0.01143 0.00487 0.0037 0.0541 1.0000
6.750 0.7669 0.01178 0.00524 0.0040 0.0483 1.0000
7.000 0.7928 0.01217 0.00564 0.0043 0.0422 1.0000
7.250 0.8186 0.01257 0.00608 0.0047 0.0375 1.0000
7.500 0.8441 0.01301 0.00654 0.0050 0.0327 1.0000
7.750 0.8694 0.01349 0.00707 0.0053 0.0289 1.0000
8.000 0.8949 0.01393 0.00756 0.0057 0.0262 1.0000
8.250 0.9197 0.01447 0.00811 0.0060 0.0230 1.0000
8.500 0.9446 0.01499 0.00869 0.0064 0.0207 1.0000
8.750 0.9695 0.01546 0.00925 0.0067 0.0191 1.0000
9.000 0.9940 0.01601 0.00988 0.0071 0.0174 1.0000
9.250 1.0177 0.01669 0.01062 0.0075 0.0157 1.0000
9.500 1.0417 0.01729 0.01132 0.0079 0.0145 1.0000
9.750 1.0656 0.01785 0.01197 0.0083 0.0130 1.0000
10.000 1.0888 0.01852 0.01269 0.0087 0.0113 1.0000
10.250 1.1115 0.01926 0.01351 0.0092 0.0097 1.0000
10.500 1.1339 0.02000 0.01435 0.0097 0.0083 1.0000
10.750 1.1548 0.02098 0.01542 0.0102 0.0071 1.0000
11.000 1.1755 0.02192 0.01650 0.0108 0.0064 1.0000
11.250 1.1950 0.02296 0.01767 0.0114 0.0057 1.0000
11.500 1.2134 0.02412 0.01894 0.0121 0.0052 1.0000
11.750 1.2285 0.02563 0.02060 0.0129 0.0047 1.0000
12.000 1.2443 0.02692 0.02206 0.0137 0.0045 1.0000
12.250 1.2581 0.02834 0.02363 0.0145 0.0042 1.0000
12.500 1.2700 0.02982 0.02527 0.0154 0.0039 1.0000
12.750 1.2784 0.03151 0.02712 0.0164 0.0037 1.0000
13.000 1.2797 0.03352 0.02931 0.0178 0.0036 1.0000
13.250 1.2737 0.03572 0.03165 0.0193 0.0035 1.0000
13.500 1.2581 0.03975 0.03587 0.0181 0.0034 1.0000
13.750 1.2452 0.04520 0.04150 0.0140 0.0034 1.0000
14.000 1.2217 0.05368 0.05021 0.0073 0.0035 1.0000
14.250 1.1975 0.06243 0.05913 0.0012 0.0035 1.0000
14.500 1.1594 0.07358 0.07043 -0.0058 0.0038 1.0000
14.750 1.1264 0.08383 0.08081 -0.0118 0.0037 1.0000
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Polar data table (+)
Polar graphs
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