S4062-095-87 (s4062-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 100,000 Max Cl/Cd: 61.9 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4062-il-100000-n5.txt Download as CSV file: xf-s4062-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4062-095-87
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3252 0.10630 0.10162 -0.0448 1.0000 0.0493
-9.000 -0.3256 0.09978 0.09509 -0.0427 1.0000 0.0291
-8.750 -0.3329 0.09834 0.09372 -0.0399 1.0000 0.0284
-8.500 -0.3204 0.09426 0.08965 -0.0433 0.9933 0.0273
-8.250 -0.3090 0.08950 0.08489 -0.0481 0.9864 0.0259
-7.750 -0.2918 0.07691 0.07233 -0.0627 0.9699 0.0228
-7.500 -0.2786 0.07186 0.06728 -0.0692 0.9616 0.0226
-7.250 -0.2650 0.06643 0.06184 -0.0765 0.9532 0.0223
-7.000 -0.2484 0.05809 0.05339 -0.0879 0.9452 0.0225
-6.750 -0.2376 0.05100 0.04612 -0.0948 0.9352 0.0223
-6.500 -0.2242 0.04363 0.03831 -0.1013 0.9271 0.0224
-6.250 -0.2087 0.03765 0.03166 -0.1051 0.9193 0.0228
-6.000 -0.1884 0.03338 0.02670 -0.1070 0.9134 0.0232
-5.750 -0.1680 0.03054 0.02343 -0.1074 0.9070 0.0236
-5.500 -0.1414 0.02813 0.02062 -0.1083 0.9030 0.0242
-5.250 -0.1183 0.02631 0.01845 -0.1081 0.8973 0.0252
-5.000 -0.0930 0.02469 0.01649 -0.1079 0.8920 0.0264
-4.750 -0.0644 0.02319 0.01467 -0.1081 0.8884 0.0283
-4.500 -0.0400 0.02218 0.01350 -0.1078 0.8831 0.0320
-4.250 -0.0145 0.02131 0.01249 -0.1074 0.8779 0.0364
-4.000 0.0134 0.02025 0.01130 -0.1075 0.8741 0.0419
-3.750 0.0393 0.01956 0.01057 -0.1072 0.8693 0.0545
-3.500 0.0642 0.01900 0.01001 -0.1068 0.8638 0.0773
-3.250 0.0922 0.01848 0.00952 -0.1070 0.8599 0.1073
-3.000 0.1197 0.01806 0.00913 -0.1070 0.8559 0.1388
-2.750 0.1436 0.01781 0.00892 -0.1064 0.8499 0.1703
-2.500 0.1712 0.01747 0.00862 -0.1064 0.8458 0.2086
-2.250 0.2001 0.01711 0.00834 -0.1065 0.8427 0.2545
-2.000 0.2227 0.01697 0.00833 -0.1058 0.8360 0.3047
-1.750 0.2494 0.01668 0.00819 -0.1056 0.8317 0.3718
-1.500 0.2772 0.01630 0.00805 -0.1054 0.8285 0.4599
-1.250 0.2987 0.01610 0.00816 -0.1043 0.8221 0.5621
-1.000 0.3206 0.01570 0.00815 -0.1025 0.8175 0.6976
-0.750 0.3601 0.01512 0.00793 -0.1036 0.8150 0.9465
-0.500 0.3896 0.01524 0.00788 -0.1041 0.8098 1.0000
-0.250 0.4151 0.01540 0.00789 -0.1037 0.8040 1.0000
0.000 0.4436 0.01545 0.00779 -0.1037 0.8002 1.0000
0.250 0.4685 0.01565 0.00788 -0.1033 0.7943 1.0000
0.500 0.4946 0.01579 0.00793 -0.1030 0.7887 1.0000
0.750 0.5237 0.01581 0.00783 -0.1029 0.7849 1.0000
1.000 0.5472 0.01606 0.00804 -0.1023 0.7776 1.0000
1.250 0.5748 0.01612 0.00803 -0.1021 0.7724 1.0000
1.500 0.6018 0.01620 0.00806 -0.1018 0.7668 1.0000
1.750 0.6271 0.01632 0.00816 -0.1013 0.7594 1.0000
2.000 0.6561 0.01625 0.00803 -0.1011 0.7538 1.0000
2.500 0.7073 0.01634 0.00811 -0.0998 0.7366 1.0000
2.750 0.7344 0.01628 0.00805 -0.0993 0.7281 1.0000
3.000 0.7593 0.01635 0.00813 -0.0986 0.7182 1.0000
3.250 0.7877 0.01624 0.00803 -0.0982 0.7102 1.0000
3.500 0.8126 0.01631 0.00814 -0.0975 0.6996 1.0000
3.750 0.8376 0.01637 0.00824 -0.0968 0.6887 1.0000
4.000 0.8638 0.01637 0.00828 -0.0961 0.6779 1.0000
4.250 0.8904 0.01635 0.00831 -0.0955 0.6664 1.0000
4.500 0.9162 0.01636 0.00836 -0.0948 0.6534 1.0000
4.750 0.9408 0.01642 0.00848 -0.0940 0.6385 1.0000
5.000 0.9645 0.01654 0.00869 -0.0931 0.6212 1.0000
5.250 0.9884 0.01663 0.00884 -0.0921 0.6018 1.0000
5.500 1.0128 0.01671 0.00893 -0.0911 0.5801 1.0000
5.750 1.0356 0.01687 0.00910 -0.0900 0.5535 1.0000
6.000 1.0578 0.01709 0.00931 -0.0887 0.5216 1.0000
6.250 1.0786 0.01743 0.00955 -0.0873 0.4834 1.0000
6.500 1.0975 0.01792 0.00988 -0.0856 0.4412 1.0000
6.750 1.1143 0.01860 0.01036 -0.0838 0.3994 1.0000
7.000 1.1296 0.01940 0.01100 -0.0819 0.3609 1.0000
7.250 1.1443 0.02025 0.01170 -0.0799 0.3264 1.0000
7.500 1.1583 0.02113 0.01247 -0.0780 0.2955 1.0000
7.750 1.1721 0.02203 0.01327 -0.0761 0.2677 1.0000
8.000 1.1854 0.02294 0.01412 -0.0742 0.2430 1.0000
8.250 1.1974 0.02386 0.01499 -0.0721 0.2206 1.0000
8.500 1.2091 0.02478 0.01592 -0.0700 0.2005 1.0000
8.750 1.2205 0.02577 0.01690 -0.0680 0.1813 1.0000
9.000 1.2310 0.02684 0.01795 -0.0659 0.1639 1.0000
9.250 1.2414 0.02796 0.01908 -0.0640 0.1465 1.0000
9.500 1.2513 0.02917 0.02030 -0.0621 0.1286 1.0000
9.750 1.2595 0.03052 0.02159 -0.0603 0.1109 1.0000
10.000 1.2674 0.03196 0.02300 -0.0585 0.0935 1.0000
10.250 1.2754 0.03345 0.02449 -0.0568 0.0792 1.0000
10.500 1.2823 0.03508 0.02614 -0.0552 0.0682 1.0000
10.750 1.2872 0.03692 0.02799 -0.0534 0.0598 1.0000
11.000 1.2933 0.03873 0.02993 -0.0518 0.0524 1.0000
11.250 1.2960 0.04088 0.03213 -0.0502 0.0468 1.0000
11.500 1.2997 0.04300 0.03436 -0.0488 0.0416 1.0000
11.750 1.2998 0.04550 0.03692 -0.0474 0.0382 1.0000
12.000 1.3029 0.04785 0.03949 -0.0461 0.0352 1.0000
12.250 1.3044 0.05039 0.04217 -0.0450 0.0330 1.0000
12.500 1.3046 0.05313 0.04502 -0.0441 0.0315 1.0000
12.750 1.3027 0.05621 0.04818 -0.0432 0.0302 1.0000
13.000 1.3059 0.05894 0.05113 -0.0424 0.0290 1.0000
13.250 1.3078 0.06185 0.05426 -0.0418 0.0276 1.0000
13.500 1.3081 0.06495 0.05755 -0.0414 0.0263 1.0000
13.750 1.3072 0.06821 0.06098 -0.0413 0.0253 1.0000
14.000 1.3047 0.07174 0.06464 -0.0415 0.0243 1.0000
14.250 1.3020 0.07544 0.06845 -0.0418 0.0236 1.0000
14.500 1.2994 0.07935 0.07249 -0.0420 0.0231 1.0000
14.750 1.2949 0.08373 0.07712 -0.0427 0.0227 1.0000
15.000 1.2879 0.08865 0.08232 -0.0439 0.0224 1.0000
15.250 1.2791 0.09400 0.08797 -0.0455 0.0221 1.0000
15.500 1.2680 0.09994 0.09417 -0.0478 0.0219 1.0000
15.750 1.2548 0.10652 0.10101 -0.0508 0.0217 1.0000
16.000 1.2398 0.11380 0.10853 -0.0546 0.0217 1.0000
16.250 1.2231 0.12182 0.11679 -0.0592 0.0217 1.0000
16.500 1.2045 0.13081 0.12596 -0.0648 0.0217 1.0000
16.750 1.1841 0.14090 0.13625 -0.0714 0.0219 1.0000
17.000 1.1616 0.15234 0.14785 -0.0790 0.0222 1.0000
17.250 1.1370 0.16537 0.16099 -0.0875 0.0225 1.0000
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Polar data table (+)
Polar graphs
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