S4062-095-87 (s4062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 1,000,000 Max Cl/Cd: 154.97 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4062-il-1000000.txt Download as CSV file: xf-s4062-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2201 0.08436 0.08255 -0.0509 0.8897 0.0106
-9.500 -0.2148 0.08113 0.07929 -0.0519 0.8850 0.0109
-9.250 -0.2117 0.07726 0.07542 -0.0534 0.8800 0.0109
-9.000 -0.2079 0.07372 0.07186 -0.0546 0.8750 0.0113
-8.750 -0.2063 0.06982 0.06795 -0.0560 0.8701 0.0117
-8.500 -0.2058 0.06565 0.06378 -0.0575 0.8648 0.0119
-8.250 -0.2072 0.06126 0.05937 -0.0591 0.8595 0.0123
-8.000 -0.2491 0.06896 0.06703 -0.0697 0.8770 0.0114
-7.750 -0.2540 0.06566 0.06372 -0.0707 0.8678 0.0120
-7.500 -0.2571 0.06144 0.05948 -0.0740 0.8591 0.0120
-7.250 -0.3125 0.02826 0.02548 -0.0982 0.8445 0.0095
-7.000 -0.3020 0.02187 0.01838 -0.0997 0.8391 0.0092
-6.750 -0.2816 0.01855 0.01458 -0.0999 0.8343 0.0090
-6.500 -0.2581 0.01648 0.01215 -0.0999 0.8301 0.0090
-6.250 -0.2331 0.01482 0.01018 -0.0998 0.8261 0.0090
-6.000 -0.2069 0.01362 0.00878 -0.0998 0.8218 0.0090
-5.750 -0.1800 0.01287 0.00788 -0.0997 0.8176 0.0094
-5.500 -0.1531 0.01214 0.00699 -0.0996 0.8137 0.0096
-5.250 -0.1259 0.01133 0.00606 -0.0996 0.8098 0.0097
-5.000 -0.0984 0.01066 0.00529 -0.0995 0.8055 0.0098
-4.750 -0.0707 0.01021 0.00474 -0.0995 0.8015 0.0101
-4.500 -0.0437 0.00932 0.00371 -0.0994 0.7976 0.0109
-4.250 -0.0155 0.00896 0.00331 -0.0995 0.7935 0.0118
-4.000 0.0128 0.00868 0.00298 -0.0996 0.7893 0.0127
-3.750 0.0410 0.00846 0.00269 -0.0996 0.7854 0.0136
-3.500 0.0693 0.00810 0.00229 -0.0996 0.7814 0.0163
-3.250 0.0977 0.00778 0.00200 -0.0997 0.7772 0.0262
-3.000 0.1258 0.00748 0.00179 -0.0998 0.7731 0.0537
-2.750 0.1539 0.00732 0.00167 -0.0999 0.7691 0.0733
-2.500 0.1825 0.00715 0.00156 -0.1001 0.7649 0.0937
-2.250 0.2109 0.00699 0.00147 -0.1002 0.7606 0.1184
-2.000 0.2391 0.00682 0.00138 -0.1003 0.7565 0.1528
-1.750 0.2675 0.00667 0.00132 -0.1005 0.7523 0.1884
-1.500 0.2959 0.00652 0.00127 -0.1006 0.7477 0.2236
-1.250 0.3242 0.00638 0.00122 -0.1008 0.7432 0.2653
-1.000 0.3525 0.00626 0.00118 -0.1009 0.7386 0.3106
-0.750 0.3808 0.00608 0.00116 -0.1010 0.7332 0.3667
-0.500 0.4087 0.00593 0.00114 -0.1011 0.7270 0.4273
-0.250 0.4367 0.00573 0.00114 -0.1012 0.7202 0.5046
0.000 0.4642 0.00553 0.00114 -0.1012 0.7131 0.5926
0.250 0.4912 0.00527 0.00117 -0.1010 0.7061 0.7020
0.500 0.5159 0.00497 0.00122 -0.1002 0.6993 0.8278
0.750 0.5472 0.00469 0.00120 -0.1006 0.6932 0.9925
1.000 0.5763 0.00473 0.00120 -0.1008 0.6863 1.0000
1.250 0.6044 0.00479 0.00122 -0.1009 0.6795 1.0000
1.500 0.6326 0.00484 0.00124 -0.1009 0.6720 1.0000
1.750 0.6607 0.00491 0.00126 -0.1009 0.6648 1.0000
2.000 0.6887 0.00497 0.00129 -0.1010 0.6566 1.0000
2.250 0.7167 0.00504 0.00134 -0.1010 0.6482 1.0000
2.750 0.7724 0.00521 0.00144 -0.1010 0.6285 1.0000
3.000 0.8001 0.00530 0.00150 -0.1010 0.6170 1.0000
3.250 0.8275 0.00542 0.00158 -0.1009 0.6038 1.0000
3.500 0.8548 0.00554 0.00166 -0.1008 0.5890 1.0000
3.750 0.8818 0.00569 0.00175 -0.1007 0.5714 1.0000
4.000 0.9083 0.00589 0.00187 -0.1005 0.5508 1.0000
4.250 0.9342 0.00613 0.00202 -0.1002 0.5237 1.0000
4.500 0.9595 0.00643 0.00219 -0.0999 0.4905 1.0000
4.750 0.9832 0.00686 0.00243 -0.0993 0.4449 1.0000
5.000 1.0054 0.00745 0.00275 -0.0985 0.3895 1.0000
5.250 1.0278 0.00800 0.00307 -0.0978 0.3409 1.0000
5.500 1.0513 0.00844 0.00336 -0.0972 0.3083 1.0000
5.750 1.0751 0.00884 0.00364 -0.0967 0.2807 1.0000
6.000 1.0979 0.00930 0.00396 -0.0960 0.2496 1.0000
6.250 1.1208 0.00975 0.00428 -0.0953 0.2219 1.0000
6.500 1.1437 0.01018 0.00459 -0.0947 0.1981 1.0000
6.750 1.1660 0.01064 0.00494 -0.0939 0.1745 1.0000
7.000 1.1887 0.01105 0.00527 -0.0933 0.1559 1.0000
7.250 1.2101 0.01154 0.00565 -0.0924 0.1350 1.0000
7.500 1.2317 0.01200 0.00603 -0.0915 0.1168 1.0000
7.750 1.2524 0.01251 0.00645 -0.0905 0.0993 1.0000
8.000 1.2722 0.01305 0.00691 -0.0894 0.0823 1.0000
8.250 1.2919 0.01358 0.00737 -0.0883 0.0681 1.0000
8.500 1.3110 0.01412 0.00785 -0.0871 0.0559 1.0000
8.750 1.3294 0.01468 0.00836 -0.0857 0.0457 1.0000
9.000 1.3466 0.01528 0.00891 -0.0842 0.0362 1.0000
9.250 1.3595 0.01600 0.00957 -0.0819 0.0248 1.0000
9.500 1.3702 0.01678 0.01029 -0.0793 0.0175 1.0000
9.750 1.3839 0.01741 0.01095 -0.0772 0.0151 1.0000
10.000 1.3962 0.01815 0.01171 -0.0751 0.0133 1.0000
10.250 1.4086 0.01894 0.01256 -0.0730 0.0123 1.0000
10.500 1.4227 0.01963 0.01331 -0.0712 0.0118 1.0000
10.750 1.4359 0.02039 0.01415 -0.0694 0.0113 1.0000
11.000 1.4485 0.02123 0.01504 -0.0677 0.0107 1.0000
11.250 1.4598 0.02216 0.01603 -0.0658 0.0102 1.0000
11.500 1.4671 0.02344 0.01738 -0.0636 0.0094 1.0000
11.750 1.4702 0.02506 0.01912 -0.0611 0.0091 1.0000
12.000 1.4830 0.02598 0.02010 -0.0598 0.0088 1.0000
12.250 1.4920 0.02721 0.02142 -0.0581 0.0087 1.0000
12.500 1.5014 0.02845 0.02274 -0.0566 0.0084 1.0000
12.750 1.5091 0.02986 0.02424 -0.0551 0.0082 1.0000
13.000 1.5179 0.03121 0.02566 -0.0537 0.0078 1.0000
13.250 1.5254 0.03271 0.02723 -0.0524 0.0075 1.0000
13.500 1.5309 0.03441 0.02902 -0.0511 0.0073 1.0000
13.750 1.5345 0.03636 0.03104 -0.0498 0.0070 1.0000
14.000 1.5321 0.03896 0.03374 -0.0484 0.0068 1.0000
14.250 1.5216 0.04251 0.03744 -0.0469 0.0065 1.0000
14.500 1.5160 0.04573 0.04079 -0.0459 0.0064 1.0000
14.750 1.5235 0.04761 0.04276 -0.0455 0.0063 1.0000
15.000 1.5247 0.05030 0.04556 -0.0451 0.0062 1.0000
15.250 1.5270 0.05295 0.04831 -0.0449 0.0060 1.0000
15.500 1.5274 0.05593 0.05140 -0.0449 0.0059 1.0000
15.750 1.5250 0.05939 0.05499 -0.0450 0.0058 1.0000
16.000 1.5237 0.06287 0.05858 -0.0455 0.0056 1.0000
16.250 1.5214 0.06658 0.06240 -0.0461 0.0055 1.0000
16.500 1.5146 0.07111 0.06706 -0.0472 0.0054 1.0000
16.750 1.5089 0.07565 0.07171 -0.0484 0.0053 1.0000
17.000 1.5042 0.08023 0.07640 -0.0500 0.0052 1.0000
17.250 1.4942 0.08583 0.08214 -0.0520 0.0051 1.0000
17.500 1.4865 0.09124 0.08766 -0.0542 0.0050 1.0000
17.750 1.4750 0.09751 0.09406 -0.0570 0.0050 1.0000
18.000 1.4652 0.10369 0.10035 -0.0599 0.0049 1.0000
18.250 1.4528 0.11048 0.10727 -0.0632 0.0049 1.0000
18.500 1.4399 0.11756 0.11447 -0.0669 0.0048 1.0000
18.750 1.4266 0.12482 0.12186 -0.0708 0.0048 1.0000
19.000 1.4130 0.13228 0.12944 -0.0750 0.0047 1.0000
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Polar data table (+)
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