S8025 (8%) (s8025-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 200,000 Max Cl/Cd: 48.9 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8025-il-200000-n5.txt Download as CSV file: xf-s8025-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8193 0.05257 0.04886 -0.0114 1.0000 0.0071
-9.250 -0.8396 0.04638 0.04228 -0.0130 1.0000 0.0070
-9.000 -0.8446 0.04148 0.03696 -0.0133 1.0000 0.0070
-8.750 -0.8413 0.03725 0.03226 -0.0130 1.0000 0.0070
-8.500 -0.8316 0.03379 0.02837 -0.0124 1.0000 0.0071
-8.250 -0.8173 0.03095 0.02513 -0.0117 1.0000 0.0072
-8.000 -0.8003 0.02849 0.02232 -0.0110 1.0000 0.0074
-7.750 -0.7812 0.02636 0.01985 -0.0102 1.0000 0.0076
-7.500 -0.7607 0.02449 0.01769 -0.0095 1.0000 0.0079
-7.250 -0.7391 0.02280 0.01576 -0.0087 1.0000 0.0083
-7.000 -0.7168 0.02135 0.01410 -0.0080 1.0000 0.0087
-6.750 -0.6935 0.02019 0.01275 -0.0073 1.0000 0.0095
-6.500 -0.6707 0.01905 0.01154 -0.0068 1.0000 0.0106
-6.250 -0.6467 0.01812 0.01051 -0.0062 1.0000 0.0119
-6.000 -0.6226 0.01713 0.00934 -0.0056 1.0000 0.0129
-5.750 -0.5986 0.01608 0.00816 -0.0049 1.0000 0.0143
-5.500 -0.5740 0.01524 0.00722 -0.0043 1.0000 0.0170
-5.250 -0.5492 0.01438 0.00634 -0.0037 1.0000 0.0244
-5.000 -0.5245 0.01360 0.00567 -0.0032 1.0000 0.0455
-4.750 -0.4993 0.01300 0.00517 -0.0028 1.0000 0.0718
-4.500 -0.4739 0.01249 0.00477 -0.0024 1.0000 0.0987
-4.250 -0.4484 0.01202 0.00440 -0.0021 1.0000 0.1254
-4.000 -0.4228 0.01159 0.00405 -0.0017 1.0000 0.1533
-3.750 -0.3971 0.01120 0.00374 -0.0012 1.0000 0.1803
-3.500 -0.3715 0.01084 0.00344 -0.0008 1.0000 0.2110
-3.250 -0.3459 0.01047 0.00320 -0.0004 1.0000 0.2459
-2.750 -0.2951 0.00981 0.00279 0.0006 1.0000 0.3241
-2.500 -0.2703 0.00945 0.00263 0.0012 1.0000 0.3754
-2.250 -0.2457 0.00913 0.00250 0.0018 1.0000 0.4265
-2.000 -0.2211 0.00885 0.00241 0.0025 1.0000 0.4749
-1.750 -0.1916 0.00858 0.00233 0.0022 0.9899 0.5280
-1.500 -0.1533 0.00834 0.00229 0.0001 0.9522 0.5866
-1.250 -0.1141 0.00816 0.00226 -0.0019 0.9036 0.6417
-1.000 -0.0815 0.00805 0.00220 -0.0022 0.8481 0.6912
-0.750 -0.0559 0.00802 0.00216 -0.0010 0.7949 0.7349
-0.500 -0.0322 0.00804 0.00213 0.0006 0.7470 0.7762
-0.250 -0.0082 0.00808 0.00211 0.0021 0.7035 0.8202
0.000 0.0185 0.00814 0.00210 0.0031 0.6635 0.8669
0.250 0.0514 0.00825 0.00209 0.0026 0.6241 0.9111
0.500 0.0898 0.00838 0.00206 0.0007 0.5851 0.9461
0.750 0.1287 0.00852 0.00204 -0.0014 0.5483 0.9745
1.000 0.1675 0.00868 0.00202 -0.0037 0.5126 0.9972
1.250 0.1942 0.00885 0.00203 -0.0035 0.4823 1.0000
1.750 0.2437 0.00923 0.00212 -0.0022 0.4242 1.0000
2.000 0.2690 0.00942 0.00219 -0.0016 0.3977 1.0000
2.250 0.2944 0.00961 0.00228 -0.0011 0.3738 1.0000
2.500 0.3200 0.00982 0.00240 -0.0006 0.3514 1.0000
2.750 0.3458 0.01003 0.00253 -0.0001 0.3292 1.0000
3.000 0.3717 0.01025 0.00267 0.0003 0.3092 1.0000
3.250 0.3977 0.01048 0.00284 0.0007 0.2885 1.0000
3.500 0.4237 0.01074 0.00303 0.0011 0.2679 1.0000
3.750 0.4497 0.01099 0.00323 0.0014 0.2476 1.0000
4.000 0.4758 0.01126 0.00345 0.0018 0.2279 1.0000
4.250 0.5018 0.01156 0.00371 0.0021 0.2103 1.0000
4.500 0.5280 0.01184 0.00398 0.0025 0.1939 1.0000
4.750 0.5540 0.01216 0.00427 0.0028 0.1773 1.0000
5.000 0.5800 0.01249 0.00459 0.0031 0.1620 1.0000
5.250 0.6060 0.01284 0.00496 0.0035 0.1481 1.0000
5.500 0.6319 0.01322 0.00533 0.0038 0.1332 1.0000
5.750 0.6576 0.01363 0.00572 0.0041 0.1184 1.0000
6.000 0.6832 0.01407 0.00615 0.0044 0.1049 1.0000
6.250 0.7087 0.01452 0.00665 0.0048 0.0928 1.0000
6.500 0.7340 0.01501 0.00716 0.0051 0.0815 1.0000
6.750 0.7591 0.01556 0.00773 0.0055 0.0721 1.0000
7.000 0.7839 0.01616 0.00835 0.0059 0.0637 1.0000
7.250 0.8087 0.01675 0.00904 0.0063 0.0565 1.0000
7.500 0.8327 0.01750 0.00983 0.0067 0.0498 1.0000
7.750 0.8570 0.01817 0.01064 0.0072 0.0449 1.0000
8.000 0.8801 0.01905 0.01158 0.0076 0.0407 1.0000
8.250 0.9031 0.01996 0.01262 0.0082 0.0376 1.0000
8.500 0.9263 0.02076 0.01357 0.0087 0.0342 1.0000
8.750 0.9485 0.02172 0.01463 0.0092 0.0316 1.0000
9.000 0.9685 0.02307 0.01608 0.0099 0.0293 1.0000
9.250 0.9906 0.02399 0.01724 0.0104 0.0269 1.0000
9.500 1.0123 0.02483 0.01822 0.0108 0.0241 1.0000
9.750 1.0300 0.02627 0.01972 0.0114 0.0215 1.0000
10.000 1.0505 0.02729 0.02101 0.0120 0.0195 1.0000
10.250 1.0691 0.02848 0.02237 0.0125 0.0175 1.0000
10.500 1.0852 0.02991 0.02395 0.0131 0.0160 1.0000
10.750 1.0956 0.03206 0.02629 0.0140 0.0148 1.0000
11.000 1.1057 0.03416 0.02868 0.0148 0.0138 1.0000
11.250 1.1122 0.03640 0.03121 0.0157 0.0128 1.0000
11.500 1.1154 0.03867 0.03369 0.0164 0.0121 1.0000
11.750 1.1115 0.04101 0.03619 0.0174 0.0116 1.0000
12.000 1.1027 0.04432 0.03965 0.0165 0.0113 1.0000
12.250 1.0913 0.04909 0.04461 0.0132 0.0112 1.0000
12.500 1.0782 0.05514 0.05084 0.0085 0.0111 1.0000
12.750 1.0601 0.06257 0.05848 0.0030 0.0113 1.0000
13.000 1.0416 0.07039 0.06644 -0.0026 0.0112 1.0000
13.250 1.0112 0.08070 0.07697 -0.0092 0.0117 1.0000
13.500 0.9780 0.09209 0.08850 -0.0163 0.0121 1.0000
13.750 0.9326 0.10692 0.10349 -0.0251 0.0131 1.0000
14.000 0.8861 0.12332 0.11995 -0.0340 0.0141 1.0000
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Polar data table (+)
Polar graphs
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