S6062 8% (s6062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S6062 8% (s6062-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.17 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6062-il-1000000-n5.txt Download as CSV file: xf-s6062-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5553 0.08057 0.07900 -0.0123 1.0000 0.0035
-8.750 -0.5627 0.07524 0.07370 -0.0157 1.0000 0.0034
-8.500 -0.5741 0.06955 0.06805 -0.0199 1.0000 0.0033
-8.250 -0.5856 0.06195 0.06045 -0.0279 1.0000 0.0034
-8.000 -0.5912 0.05320 0.05159 -0.0340 1.0000 0.0033
-7.750 -0.5964 0.04335 0.04149 -0.0375 1.0000 0.0033
-7.500 -0.6037 0.03179 0.02940 -0.0381 1.0000 0.0033
-7.250 -0.5862 0.02585 0.02293 -0.0396 0.9859 0.0034
-7.000 -0.5611 0.02251 0.01917 -0.0408 0.9730 0.0035
-6.750 -0.5355 0.02080 0.01718 -0.0411 0.9605 0.0036
-6.500 -0.5122 0.01940 0.01551 -0.0407 0.9479 0.0036
-6.250 -0.4897 0.01800 0.01384 -0.0400 0.9360 0.0037
-6.000 -0.4680 0.01617 0.01171 -0.0392 0.9249 0.0037
-5.750 -0.4447 0.01490 0.01021 -0.0384 0.9145 0.0037
-5.500 -0.4207 0.01361 0.00870 -0.0377 0.9041 0.0037
-5.250 -0.3962 0.01247 0.00738 -0.0371 0.8943 0.0037
-5.000 -0.3718 0.01133 0.00606 -0.0365 0.8846 0.0038
-4.750 -0.3471 0.01034 0.00488 -0.0359 0.8743 0.0040
-4.500 -0.3212 0.00972 0.00416 -0.0356 0.8641 0.0042
-4.250 -0.2948 0.00930 0.00366 -0.0353 0.8541 0.0045
-4.000 -0.2681 0.00896 0.00324 -0.0350 0.8438 0.0048
-3.750 -0.2411 0.00867 0.00288 -0.0348 0.8331 0.0053
-3.500 -0.2139 0.00841 0.00253 -0.0346 0.8225 0.0057
-3.250 -0.1866 0.00819 0.00223 -0.0345 0.8118 0.0060
-3.000 -0.1592 0.00801 0.00198 -0.0343 0.8005 0.0064
-2.750 -0.1318 0.00785 0.00174 -0.0342 0.7889 0.0071
-2.500 -0.1041 0.00768 0.00148 -0.0341 0.7767 0.0082
-2.250 -0.0765 0.00755 0.00129 -0.0339 0.7642 0.0107
-2.000 -0.0492 0.00729 0.00112 -0.0339 0.7514 0.0406
-1.750 -0.0219 0.00707 0.00099 -0.0338 0.7381 0.0803
-1.500 0.0049 0.00672 0.00087 -0.0338 0.7243 0.1583
-1.250 0.0320 0.00646 0.00078 -0.0338 0.7099 0.2285
-1.000 0.0585 0.00606 0.00071 -0.0338 0.6950 0.3429
-0.750 0.0853 0.00579 0.00066 -0.0337 0.6793 0.4318
-0.500 0.1125 0.00565 0.00062 -0.0337 0.6628 0.4892
-0.250 0.1395 0.00548 0.00060 -0.0336 0.6447 0.5591
0.000 0.1663 0.00533 0.00060 -0.0335 0.6255 0.6301
0.250 0.1930 0.00523 0.00061 -0.0333 0.6063 0.6899
0.500 0.2198 0.00517 0.00063 -0.0330 0.5867 0.7391
0.750 0.2465 0.00515 0.00067 -0.0327 0.5669 0.7808
1.000 0.2730 0.00516 0.00071 -0.0324 0.5464 0.8166
1.250 0.2992 0.00519 0.00076 -0.0320 0.5248 0.8487
1.500 0.3253 0.00524 0.00082 -0.0315 0.5023 0.8761
1.750 0.3510 0.00531 0.00088 -0.0310 0.4785 0.9012
2.000 0.3756 0.00549 0.00096 -0.0302 0.4365 0.9280
2.250 0.4010 0.00586 0.00108 -0.0298 0.3624 0.9556
2.500 0.4330 0.00619 0.00120 -0.0309 0.3054 0.9761
2.750 0.4662 0.00665 0.00136 -0.0325 0.2364 0.9915
3.000 0.4960 0.00705 0.00153 -0.0332 0.1831 1.0000
3.250 0.5213 0.00744 0.00173 -0.0329 0.1375 1.0000
3.500 0.5464 0.00790 0.00196 -0.0326 0.0871 1.0000
3.750 0.5711 0.00844 0.00226 -0.0323 0.0352 1.0000
4.000 0.5969 0.00882 0.00252 -0.0320 0.0120 1.0000
4.250 0.6237 0.00901 0.00273 -0.0318 0.0110 1.0000
4.500 0.6504 0.00921 0.00294 -0.0317 0.0104 1.0000
4.750 0.6770 0.00944 0.00319 -0.0315 0.0098 1.0000
5.000 0.7035 0.00969 0.00346 -0.0313 0.0093 1.0000
5.250 0.7298 0.00998 0.00377 -0.0311 0.0088 1.0000
5.500 0.7558 0.01033 0.00418 -0.0308 0.0081 1.0000
5.750 0.7813 0.01078 0.00470 -0.0305 0.0076 1.0000
6.000 0.8062 0.01133 0.00533 -0.0300 0.0073 1.0000
6.250 0.8308 0.01190 0.00596 -0.0296 0.0070 1.0000
6.500 0.8565 0.01224 0.00633 -0.0293 0.0069 1.0000
6.750 0.8813 0.01273 0.00687 -0.0289 0.0068 1.0000
7.000 0.9057 0.01326 0.00749 -0.0285 0.0067 1.0000
7.250 0.9298 0.01384 0.00813 -0.0280 0.0066 1.0000
7.500 0.9536 0.01445 0.00881 -0.0275 0.0064 1.0000
7.750 0.9769 0.01510 0.00953 -0.0270 0.0063 1.0000
8.000 0.9998 0.01581 0.01032 -0.0264 0.0061 1.0000
8.250 1.0224 0.01655 0.01114 -0.0257 0.0059 1.0000
8.500 1.0445 0.01735 0.01203 -0.0251 0.0058 1.0000
8.750 1.0659 0.01824 0.01303 -0.0243 0.0056 1.0000
9.000 1.0872 0.01911 0.01400 -0.0236 0.0054 1.0000
9.250 1.1079 0.02004 0.01504 -0.0228 0.0052 1.0000
9.500 1.1278 0.02106 0.01616 -0.0219 0.0050 1.0000
9.750 1.1479 0.02191 0.01710 -0.0211 0.0049 1.0000
10.000 1.1684 0.02260 0.01786 -0.0205 0.0047 1.0000
10.250 1.1864 0.02362 0.01898 -0.0195 0.0046 1.0000
10.500 1.2029 0.02477 0.02024 -0.0184 0.0044 1.0000
10.750 1.2167 0.02616 0.02176 -0.0170 0.0043 1.0000
11.000 1.2244 0.02824 0.02404 -0.0151 0.0042 1.0000
11.250 1.2242 0.03104 0.02709 -0.0125 0.0041 1.0000
11.500 1.2158 0.03369 0.02998 -0.0088 0.0040 1.0000
11.750 1.2136 0.03544 0.03189 -0.0061 0.0040 1.0000
12.000 1.2120 0.03729 0.03388 -0.0042 0.0040 1.0000
12.250 1.2100 0.03936 0.03609 -0.0028 0.0040 1.0000
12.500 1.2062 0.04184 0.03871 -0.0020 0.0039 1.0000
12.750 1.1938 0.04566 0.04272 -0.0019 0.0039 1.0000
13.000 1.1882 0.04903 0.04622 -0.0026 0.0039 1.0000
13.250 1.1765 0.05364 0.05099 -0.0044 0.0039 1.0000
13.500 1.1735 0.05743 0.05490 -0.0063 0.0038 1.0000
13.750 1.1532 0.06455 0.06221 -0.0105 0.0038 1.0000
14.000 1.1420 0.07078 0.06856 -0.0145 0.0038 1.0000
14.250 1.1087 0.08222 0.08019 -0.0220 0.0039 1.0000
14.500 1.0698 0.09624 0.09439 -0.0310 0.0039 1.0000
14.750 1.0409 0.10887 0.10715 -0.0387 0.0040 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S6062 8% (s6062-il)