S2062 8% (s2062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.65 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2062-il-1000000.txt Download as CSV file: xf-s2062-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S2062 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.6547 0.02572 0.02262 -0.0440 0.9997 0.0070
-7.500 -0.6280 0.02201 0.01845 -0.0460 0.9977 0.0071
-7.250 -0.5983 0.01954 0.01563 -0.0476 0.9960 0.0070
-7.000 -0.5677 0.01734 0.01313 -0.0492 0.9946 0.0071
-6.750 -0.5384 0.01571 0.01126 -0.0501 0.9925 0.0071
-6.500 -0.5080 0.01436 0.00972 -0.0510 0.9902 0.0071
-6.250 -0.4768 0.01304 0.00825 -0.0521 0.9882 0.0073
-6.000 -0.4442 0.01219 0.00731 -0.0535 0.9865 0.0077
-5.750 -0.4109 0.01128 0.00627 -0.0548 0.9851 0.0078
-5.500 -0.3768 0.01046 0.00534 -0.0563 0.9839 0.0079
-5.250 -0.3450 0.00983 0.00462 -0.0573 0.9817 0.0082
-5.000 -0.3139 0.00930 0.00402 -0.0580 0.9785 0.0087
-4.750 -0.2810 0.00886 0.00352 -0.0591 0.9759 0.0097
-4.500 -0.2480 0.00837 0.00294 -0.0602 0.9733 0.0114
-4.250 -0.2150 0.00802 0.00256 -0.0612 0.9707 0.0144
-4.000 -0.1880 0.00748 0.00221 -0.0611 0.9646 0.0482
-3.750 -0.1589 0.00722 0.00201 -0.0614 0.9593 0.0667
-3.500 -0.1304 0.00697 0.00183 -0.0615 0.9536 0.0872
-3.250 -0.1036 0.00673 0.00166 -0.0613 0.9461 0.1122
-3.000 -0.0763 0.00649 0.00152 -0.0611 0.9390 0.1447
-2.750 -0.0498 0.00622 0.00138 -0.0609 0.9306 0.1880
-2.500 -0.0232 0.00599 0.00126 -0.0606 0.9216 0.2301
-2.250 0.0036 0.00579 0.00115 -0.0603 0.9129 0.2715
-2.000 0.0302 0.00555 0.00106 -0.0601 0.9031 0.3250
-1.750 0.0568 0.00533 0.00098 -0.0598 0.8932 0.3850
-1.500 0.0833 0.00508 0.00092 -0.0596 0.8829 0.4562
-1.250 0.1097 0.00486 0.00086 -0.0593 0.8717 0.5250
-1.000 0.1358 0.00459 0.00083 -0.0589 0.8596 0.6115
-0.750 0.1618 0.00438 0.00083 -0.0584 0.8473 0.6934
-0.500 0.1880 0.00427 0.00083 -0.0579 0.8343 0.7480
-0.250 0.2144 0.00422 0.00084 -0.0574 0.8204 0.7866
0.000 0.2406 0.00420 0.00085 -0.0569 0.8054 0.8170
0.250 0.2668 0.00419 0.00086 -0.0563 0.7889 0.8429
0.500 0.2925 0.00420 0.00087 -0.0556 0.7710 0.8672
0.750 0.3180 0.00423 0.00089 -0.0549 0.7504 0.8888
1.000 0.3427 0.00427 0.00091 -0.0540 0.7281 0.9106
1.250 0.3668 0.00434 0.00094 -0.0530 0.7029 0.9323
1.750 0.4235 0.00455 0.00100 -0.0529 0.6423 0.9768
2.000 0.4589 0.00472 0.00104 -0.0546 0.6060 0.9923
2.250 0.4893 0.00492 0.00111 -0.0552 0.5691 1.0000
2.500 0.5142 0.00516 0.00119 -0.0547 0.5302 1.0000
2.750 0.5379 0.00555 0.00131 -0.0540 0.4638 1.0000
3.000 0.5624 0.00593 0.00144 -0.0534 0.4053 1.0000
3.250 0.5872 0.00630 0.00160 -0.0529 0.3514 1.0000
3.500 0.6119 0.00670 0.00178 -0.0525 0.2970 1.0000
3.750 0.6370 0.00708 0.00196 -0.0521 0.2514 1.0000
4.000 0.6618 0.00751 0.00217 -0.0517 0.2010 1.0000
4.250 0.6865 0.00795 0.00242 -0.0513 0.1554 1.0000
4.500 0.7111 0.00843 0.00269 -0.0508 0.1111 1.0000
4.750 0.7343 0.00911 0.00307 -0.0502 0.0537 1.0000
5.000 0.7579 0.00977 0.00353 -0.0495 0.0189 1.0000
5.250 0.7836 0.01013 0.00390 -0.0491 0.0159 1.0000
5.500 0.8090 0.01055 0.00439 -0.0486 0.0144 1.0000
5.750 0.8342 0.01098 0.00489 -0.0481 0.0138 1.0000
6.000 0.8594 0.01138 0.00534 -0.0476 0.0135 1.0000
6.250 0.8843 0.01183 0.00584 -0.0471 0.0130 1.0000
6.500 0.9087 0.01235 0.00644 -0.0465 0.0124 1.0000
6.750 0.9328 0.01287 0.00702 -0.0459 0.0118 1.0000
7.000 0.9564 0.01347 0.00766 -0.0452 0.0111 1.0000
7.250 0.9792 0.01416 0.00842 -0.0444 0.0107 1.0000
7.500 1.0011 0.01498 0.00931 -0.0435 0.0103 1.0000
7.750 1.0214 0.01606 0.01048 -0.0423 0.0100 1.0000
8.000 1.0387 0.01778 0.01234 -0.0407 0.0095 1.0000
8.250 1.0570 0.01958 0.01431 -0.0393 0.0091 1.0000
8.500 1.0816 0.01973 0.01452 -0.0389 0.0088 1.0000
8.750 1.1034 0.02056 0.01544 -0.0381 0.0084 1.0000
9.000 1.1240 0.02158 0.01658 -0.0371 0.0080 1.0000
9.250 1.1432 0.02285 0.01799 -0.0359 0.0077 1.0000
9.500 1.1620 0.02403 0.01929 -0.0348 0.0074 1.0000
9.750 1.1800 0.02520 0.02059 -0.0337 0.0071 1.0000
10.000 1.1969 0.02638 0.02190 -0.0324 0.0069 1.0000
10.250 1.2124 0.02762 0.02324 -0.0310 0.0066 1.0000
10.500 1.2252 0.02913 0.02486 -0.0295 0.0064 1.0000
10.750 1.2205 0.03336 0.02943 -0.0262 0.0061 1.0000
11.000 1.2052 0.03771 0.03419 -0.0218 0.0059 1.0000
11.250 1.2134 0.03791 0.03449 -0.0193 0.0058 1.0000
11.500 1.2152 0.03903 0.03572 -0.0166 0.0056 1.0000
11.750 1.2029 0.04180 0.03870 -0.0135 0.0056 1.0000
12.000 1.2058 0.04312 0.04013 -0.0120 0.0053 1.0000
12.250 1.1919 0.04655 0.04376 -0.0106 0.0052 1.0000
12.500 1.1816 0.04993 0.04730 -0.0102 0.0051 1.0000
12.750 1.1582 0.05563 0.05321 -0.0115 0.0051 1.0000
13.000 1.1396 0.06154 0.05929 -0.0143 0.0051 1.0000
13.250 1.1142 0.06979 0.06773 -0.0194 0.0052 1.0000
13.500 1.0873 0.07977 0.07787 -0.0264 0.0054 1.0000
13.750 1.0666 0.08986 0.08810 -0.0335 0.0053 1.0000
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Polar data table (+)
Polar graphs
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