S4062-095-87 (s4062-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 200,000 Max Cl/Cd: 86.3 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4062-il-200000-n5.txt Download as CSV file: xf-s4062-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2682 0.08608 0.08262 -0.0585 0.9658 0.0163
-8.500 -0.2562 0.08139 0.07792 -0.0634 0.9575 0.0156
-8.000 -0.2577 0.06687 0.06341 -0.0757 0.9315 0.0133
-7.750 -0.2569 0.06300 0.05954 -0.0790 0.9195 0.0132
-7.500 -0.2556 0.05745 0.05396 -0.0848 0.9084 0.0130
-7.250 -0.2522 0.05038 0.04679 -0.0920 0.8988 0.0128
-7.000 -0.2528 0.03895 0.03494 -0.1004 0.8888 0.0125
-6.750 -0.2450 0.03165 0.02695 -0.1040 0.8811 0.0123
-6.500 -0.2290 0.02708 0.02170 -0.1050 0.8752 0.0123
-6.250 -0.2084 0.02399 0.01800 -0.1052 0.8705 0.0125
-6.000 -0.1852 0.02178 0.01531 -0.1051 0.8650 0.0128
-5.750 -0.1607 0.02013 0.01325 -0.1048 0.8606 0.0131
-5.500 -0.1360 0.01874 0.01161 -0.1045 0.8568 0.0136
-5.250 -0.1103 0.01800 0.01079 -0.1045 0.8516 0.0150
-5.000 -0.0842 0.01720 0.00983 -0.1043 0.8472 0.0164
-4.750 -0.0581 0.01634 0.00878 -0.1040 0.8435 0.0174
-4.500 -0.0319 0.01550 0.00782 -0.1038 0.8388 0.0186
-4.250 -0.0053 0.01490 0.00713 -0.1037 0.8341 0.0204
-4.000 0.0217 0.01434 0.00644 -0.1034 0.8303 0.0232
-3.750 0.0487 0.01382 0.00588 -0.1033 0.8264 0.0305
-3.500 0.0756 0.01332 0.00541 -0.1032 0.8214 0.0465
-3.250 0.1028 0.01294 0.00508 -0.1031 0.8172 0.0699
-3.000 0.1300 0.01263 0.00483 -0.1031 0.8138 0.1018
-2.750 0.1572 0.01238 0.00463 -0.1031 0.8089 0.1283
-2.500 0.1846 0.01215 0.00445 -0.1030 0.8044 0.1561
-2.250 0.2120 0.01193 0.00425 -0.1030 0.8006 0.1871
-2.000 0.2394 0.01172 0.00412 -0.1029 0.7965 0.2232
-1.750 0.2666 0.01154 0.00402 -0.1029 0.7915 0.2652
-1.500 0.2938 0.01132 0.00392 -0.1028 0.7873 0.3146
-1.250 0.3211 0.01109 0.00382 -0.1027 0.7839 0.3745
-1.000 0.3475 0.01087 0.00383 -0.1026 0.7785 0.4483
-0.750 0.3735 0.01060 0.00381 -0.1022 0.7739 0.5355
-0.500 0.3985 0.01028 0.00379 -0.1014 0.7702 0.6397
-0.250 0.4204 0.00996 0.00385 -0.0998 0.7650 0.7650
0.000 0.4557 0.00961 0.00376 -0.1006 0.7604 0.9552
0.250 0.4874 0.00962 0.00366 -0.1013 0.7562 1.0000
0.500 0.5147 0.00970 0.00367 -0.1012 0.7507 1.0000
0.750 0.5420 0.00976 0.00366 -0.1011 0.7448 1.0000
1.000 0.5696 0.00980 0.00361 -0.1009 0.7397 1.0000
1.250 0.5964 0.00987 0.00364 -0.1007 0.7313 1.0000
1.500 0.6237 0.00989 0.00359 -0.1004 0.7237 1.0000
1.750 0.6505 0.00994 0.00359 -0.1001 0.7144 1.0000
2.000 0.6774 0.00999 0.00361 -0.0998 0.7052 1.0000
2.250 0.7047 0.01004 0.00360 -0.0996 0.6970 1.0000
2.500 0.7313 0.01012 0.00369 -0.0993 0.6873 1.0000
2.750 0.7583 0.01020 0.00374 -0.0991 0.6782 1.0000
3.000 0.7851 0.01028 0.00379 -0.0988 0.6686 1.0000
3.250 0.8116 0.01037 0.00391 -0.0985 0.6574 1.0000
3.500 0.8380 0.01047 0.00400 -0.0981 0.6458 1.0000
3.750 0.8644 0.01058 0.00411 -0.0978 0.6333 1.0000
4.000 0.8904 0.01071 0.00424 -0.0974 0.6188 1.0000
4.250 0.9161 0.01085 0.00436 -0.0969 0.6024 1.0000
4.500 0.9414 0.01101 0.00449 -0.0964 0.5831 1.0000
4.750 0.9660 0.01121 0.00465 -0.0957 0.5597 1.0000
5.000 0.9899 0.01147 0.00485 -0.0949 0.5316 1.0000
5.250 1.0124 0.01182 0.00508 -0.0940 0.4971 1.0000
5.500 1.0332 0.01229 0.00537 -0.0928 0.4562 1.0000
5.750 1.0523 0.01288 0.00578 -0.0914 0.4130 1.0000
6.000 1.0705 0.01354 0.00625 -0.0899 0.3721 1.0000
6.250 1.0882 0.01424 0.00677 -0.0884 0.3352 1.0000
6.500 1.1060 0.01493 0.00732 -0.0870 0.3014 1.0000
6.750 1.1235 0.01563 0.00788 -0.0856 0.2708 1.0000
7.000 1.1410 0.01631 0.00848 -0.0842 0.2443 1.0000
7.250 1.1587 0.01697 0.00907 -0.0828 0.2216 1.0000
7.500 1.1762 0.01761 0.00967 -0.0814 0.2029 1.0000
7.750 1.1936 0.01825 0.01029 -0.0799 0.1845 1.0000
8.000 1.2091 0.01897 0.01096 -0.0783 0.1651 1.0000
8.250 1.2227 0.01971 0.01166 -0.0763 0.1461 1.0000
8.500 1.2352 0.02052 0.01240 -0.0743 0.1262 1.0000
8.750 1.2466 0.02144 0.01322 -0.0722 0.1059 1.0000
9.000 1.2586 0.02235 0.01408 -0.0703 0.0892 1.0000
9.250 1.2709 0.02329 0.01500 -0.0685 0.0762 1.0000
9.500 1.2827 0.02429 0.01599 -0.0667 0.0646 1.0000
9.750 1.2941 0.02535 0.01706 -0.0650 0.0545 1.0000
10.000 1.3048 0.02648 0.01821 -0.0632 0.0461 1.0000
10.250 1.3143 0.02775 0.01947 -0.0615 0.0390 1.0000
10.500 1.3246 0.02897 0.02079 -0.0598 0.0332 1.0000
10.750 1.3326 0.03044 0.02230 -0.0581 0.0287 1.0000
11.000 1.3409 0.03188 0.02385 -0.0564 0.0254 1.0000
11.250 1.3462 0.03363 0.02563 -0.0547 0.0229 1.0000
11.500 1.3540 0.03519 0.02735 -0.0533 0.0210 1.0000
11.750 1.3606 0.03689 0.02918 -0.0519 0.0196 1.0000
12.000 1.3653 0.03881 0.03119 -0.0505 0.0185 1.0000
12.250 1.3665 0.04111 0.03359 -0.0492 0.0176 1.0000
12.500 1.3690 0.04337 0.03599 -0.0479 0.0171 1.0000
12.750 1.3718 0.04567 0.03845 -0.0469 0.0166 1.0000
13.000 1.3734 0.04816 0.04109 -0.0460 0.0161 1.0000
13.250 1.3748 0.05075 0.04383 -0.0452 0.0156 1.0000
13.500 1.3754 0.05349 0.04671 -0.0446 0.0151 1.0000
13.750 1.3759 0.05632 0.04968 -0.0442 0.0146 1.0000
14.000 1.3755 0.05937 0.05288 -0.0440 0.0140 1.0000
14.250 1.3733 0.06275 0.05638 -0.0441 0.0137 1.0000
14.500 1.3694 0.06647 0.06022 -0.0443 0.0133 1.0000
14.750 1.3641 0.07053 0.06439 -0.0447 0.0130 1.0000
15.000 1.3616 0.07440 0.06845 -0.0452 0.0127 1.0000
15.250 1.3581 0.07852 0.07277 -0.0460 0.0125 1.0000
15.500 1.3537 0.08292 0.07736 -0.0471 0.0124 1.0000
15.750 1.3480 0.08768 0.08232 -0.0485 0.0121 1.0000
16.000 1.3413 0.09276 0.08760 -0.0502 0.0119 1.0000
16.250 1.3336 0.09818 0.09321 -0.0524 0.0118 1.0000
16.500 1.3248 0.10400 0.09922 -0.0549 0.0115 1.0000
16.750 1.3153 0.11017 0.10559 -0.0579 0.0114 1.0000
17.000 1.3052 0.11666 0.11226 -0.0613 0.0112 1.0000
17.250 1.2943 0.12352 0.11931 -0.0651 0.0111 1.0000
17.500 1.2828 0.13073 0.12669 -0.0693 0.0109 1.0000
17.750 1.2702 0.13845 0.13460 -0.0740 0.0109 1.0000
18.000 1.2570 0.14660 0.14292 -0.0791 0.0108 1.0000
18.250 1.2420 0.15558 0.15207 -0.0848 0.0108 1.0000
18.500 1.2236 0.16590 0.16258 -0.0916 0.0109 1.0000
18.750 1.1969 0.17956 0.17644 -0.1005 0.0112 1.0000
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Polar data table (+)
Polar graphs
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