S6062 8% (s6062-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 500,000 Max Cl/Cd: 68.39 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6062-il-500000-n5.txt Download as CSV file: xf-s6062-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6062 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5362 0.08635 0.08412 -0.0099 1.0000 0.0061
-8.750 -0.5390 0.08169 0.07950 -0.0125 1.0000 0.0059
-8.500 -0.5432 0.07673 0.07457 -0.0156 1.0000 0.0058
-8.250 -0.5502 0.07152 0.06940 -0.0194 1.0000 0.0059
-8.000 -0.5577 0.06530 0.06320 -0.0260 1.0000 0.0058
-7.750 -0.5600 0.05791 0.05573 -0.0320 1.0000 0.0057
-7.500 -0.5586 0.05071 0.04837 -0.0358 1.0000 0.0057
-7.250 -0.5531 0.04411 0.04154 -0.0376 1.0000 0.0059
-7.000 -0.5449 0.03801 0.03515 -0.0381 1.0000 0.0061
-6.750 -0.5353 0.03293 0.02971 -0.0378 1.0000 0.0062
-6.500 -0.5219 0.02815 0.02448 -0.0376 0.9969 0.0060
-6.250 -0.4958 0.02370 0.01949 -0.0391 0.9869 0.0059
-6.000 -0.4677 0.02052 0.01583 -0.0401 0.9784 0.0058
-5.500 -0.4101 0.01638 0.01097 -0.0412 0.9616 0.0057
-5.250 -0.3823 0.01499 0.00934 -0.0413 0.9528 0.0058
-5.000 -0.3554 0.01386 0.00800 -0.0410 0.9436 0.0059
-4.750 -0.3300 0.01294 0.00692 -0.0405 0.9333 0.0061
-4.500 -0.3048 0.01219 0.00605 -0.0399 0.9233 0.0063
-4.250 -0.2795 0.01161 0.00536 -0.0392 0.9136 0.0065
-4.000 -0.2547 0.01084 0.00447 -0.0386 0.9034 0.0069
-3.750 -0.2294 0.01021 0.00372 -0.0380 0.8931 0.0076
-3.500 -0.2034 0.00983 0.00325 -0.0376 0.8831 0.0088
-3.250 -0.1772 0.00955 0.00288 -0.0371 0.8729 0.0099
-3.000 -0.1504 0.00929 0.00251 -0.0367 0.8622 0.0106
-2.750 -0.1235 0.00908 0.00222 -0.0364 0.8517 0.0117
-2.500 -0.0970 0.00875 0.00192 -0.0361 0.8410 0.0327
-2.250 -0.0710 0.00831 0.00170 -0.0358 0.8301 0.0956
-2.000 -0.0448 0.00789 0.00153 -0.0357 0.8186 0.1722
-1.750 -0.0183 0.00758 0.00140 -0.0355 0.8069 0.2382
-1.500 0.0069 0.00697 0.00127 -0.0354 0.7949 0.3875
-1.250 0.0325 0.00655 0.00119 -0.0351 0.7824 0.5019
-1.000 0.0585 0.00628 0.00113 -0.0347 0.7694 0.5814
-0.750 0.0842 0.00605 0.00109 -0.0342 0.7560 0.6590
-0.500 0.1097 0.00587 0.00108 -0.0336 0.7420 0.7283
-0.250 0.1352 0.00576 0.00108 -0.0329 0.7276 0.7806
0.000 0.1607 0.00571 0.00108 -0.0322 0.7123 0.8209
0.250 0.1862 0.00569 0.00109 -0.0314 0.6960 0.8551
0.500 0.2114 0.00570 0.00109 -0.0306 0.6786 0.8859
0.750 0.2370 0.00573 0.00110 -0.0298 0.6600 0.9144
1.000 0.2650 0.00578 0.00111 -0.0296 0.6405 0.9392
1.250 0.2973 0.00586 0.00113 -0.0305 0.6199 0.9606
1.500 0.3329 0.00595 0.00115 -0.0321 0.5974 0.9788
1.750 0.3687 0.00607 0.00117 -0.0339 0.5735 0.9928
2.000 0.4000 0.00621 0.00122 -0.0348 0.5491 1.0000
2.250 0.4254 0.00638 0.00130 -0.0343 0.5239 1.0000
2.500 0.4507 0.00659 0.00138 -0.0339 0.4899 1.0000
2.750 0.4748 0.00699 0.00150 -0.0334 0.4255 1.0000
3.000 0.4989 0.00746 0.00165 -0.0329 0.3546 1.0000
3.250 0.5237 0.00788 0.00185 -0.0325 0.2991 1.0000
3.500 0.5485 0.00834 0.00206 -0.0322 0.2428 1.0000
3.750 0.5730 0.00885 0.00232 -0.0319 0.1846 1.0000
4.250 0.6217 0.00999 0.00296 -0.0312 0.0764 1.0000
4.500 0.6460 0.01059 0.00335 -0.0308 0.0333 1.0000
4.750 0.6708 0.01111 0.00374 -0.0304 0.0146 1.0000
5.000 0.6968 0.01142 0.00409 -0.0301 0.0128 1.0000
5.250 0.7226 0.01177 0.00450 -0.0298 0.0119 1.0000
5.500 0.7484 0.01212 0.00494 -0.0295 0.0115 1.0000
5.750 0.7738 0.01253 0.00543 -0.0291 0.0110 1.0000
6.000 0.7988 0.01301 0.00597 -0.0287 0.0106 1.0000
6.250 0.8234 0.01354 0.00659 -0.0283 0.0103 1.0000
6.500 0.8475 0.01416 0.00729 -0.0277 0.0100 1.0000
6.750 0.8710 0.01483 0.00805 -0.0271 0.0098 1.0000
7.000 0.8943 0.01551 0.00880 -0.0266 0.0094 1.0000
7.250 0.9172 0.01623 0.00962 -0.0260 0.0089 1.0000
7.500 0.9395 0.01704 0.01051 -0.0253 0.0086 1.0000
7.750 0.9611 0.01795 0.01151 -0.0245 0.0084 1.0000
8.000 0.9822 0.01894 0.01260 -0.0237 0.0081 1.0000
8.250 1.0024 0.02009 0.01385 -0.0228 0.0079 1.0000
8.500 1.0214 0.02148 0.01538 -0.0218 0.0076 1.0000
8.750 1.0391 0.02323 0.01729 -0.0206 0.0074 1.0000
9.000 1.0521 0.02633 0.02072 -0.0190 0.0071 1.0000
9.250 1.0695 0.02789 0.02248 -0.0179 0.0070 1.0000
9.500 1.0854 0.02959 0.02440 -0.0168 0.0069 1.0000
9.750 1.0999 0.03125 0.02629 -0.0155 0.0068 1.0000
10.000 1.1138 0.03268 0.02792 -0.0142 0.0066 1.0000
10.250 1.1241 0.03452 0.03000 -0.0126 0.0064 1.0000
10.500 1.1309 0.03655 0.03226 -0.0108 0.0062 1.0000
10.750 1.1321 0.03875 0.03471 -0.0086 0.0061 1.0000
11.000 1.1246 0.04124 0.03742 -0.0056 0.0060 1.0000
11.250 1.1130 0.04421 0.04061 -0.0033 0.0060 1.0000
11.500 1.1013 0.04745 0.04406 -0.0021 0.0059 1.0000
11.750 1.0874 0.05136 0.04817 -0.0022 0.0059 1.0000
12.000 1.0721 0.05599 0.05300 -0.0035 0.0058 1.0000
12.250 1.0548 0.06164 0.05884 -0.0063 0.0059 1.0000
12.500 1.0380 0.06808 0.06544 -0.0103 0.0058 1.0000
12.750 1.0141 0.07702 0.07456 -0.0166 0.0059 1.0000
13.000 0.9928 0.08671 0.08439 -0.0235 0.0060 1.0000
13.250 0.9634 0.09986 0.09768 -0.0323 0.0062 1.0000
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Polar data table (+)
Polar graphs
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