S8025 (8%) (s8025-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 100,000 Max Cl/Cd: 33.64 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8025-il-100000.txt Download as CSV file: xf-s8025-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6491 0.08849 0.08396 0.0134 1.0000 0.1176
-8.000 -0.6538 0.08390 0.07943 0.0106 1.0000 0.1195
-7.750 -0.7168 0.05944 0.05439 -0.0119 1.0000 0.0612
-7.500 -0.7076 0.05389 0.04870 -0.0122 1.0000 0.0539
-7.250 -0.7092 0.04507 0.03883 -0.0132 1.0000 0.0464
-7.000 -0.6967 0.04016 0.03353 -0.0130 1.0000 0.0452
-6.750 -0.6811 0.03572 0.02856 -0.0123 1.0000 0.0445
-6.500 -0.6619 0.03191 0.02415 -0.0114 1.0000 0.0444
-6.250 -0.6398 0.02872 0.02040 -0.0104 1.0000 0.0454
-6.000 -0.6164 0.02592 0.01716 -0.0094 1.0000 0.0485
-5.750 -0.5927 0.02407 0.01527 -0.0088 1.0000 0.0557
-5.500 -0.5682 0.02177 0.01286 -0.0078 1.0000 0.0644
-5.250 -0.5441 0.02003 0.01106 -0.0068 1.0000 0.0867
-5.000 -0.5209 0.01862 0.00976 -0.0060 1.0000 0.1266
-4.750 -0.4974 0.01757 0.00884 -0.0053 1.0000 0.1658
-4.500 -0.4737 0.01658 0.00803 -0.0046 1.0000 0.2042
-4.250 -0.4497 0.01560 0.00723 -0.0038 1.0000 0.2473
-4.000 -0.4262 0.01469 0.00658 -0.0029 1.0000 0.2999
-3.750 -0.4029 0.01385 0.00605 -0.0020 1.0000 0.3621
-3.500 -0.3803 0.01312 0.00563 -0.0008 1.0000 0.4342
-3.250 -0.3582 0.01251 0.00537 0.0007 1.0000 0.5130
-3.000 -0.3366 0.01201 0.00518 0.0025 1.0000 0.5909
-2.750 -0.3153 0.01161 0.00503 0.0046 1.0000 0.6631
-2.500 -0.2944 0.01128 0.00489 0.0071 1.0000 0.7302
-2.250 -0.2739 0.01102 0.00479 0.0098 1.0000 0.7945
-2.000 -0.2505 0.01085 0.00472 0.0122 1.0000 0.8580
-1.750 -0.2085 0.01082 0.00466 0.0108 1.0000 0.9200
-1.500 -0.1411 0.01087 0.00450 0.0037 1.0000 0.9672
-1.250 -0.0632 0.01074 0.00415 -0.0064 1.0000 1.0000
-1.000 -0.0489 0.01048 0.00385 -0.0050 1.0000 1.0000
-0.750 -0.0323 0.01032 0.00364 -0.0037 1.0000 1.0000
-0.500 -0.0145 0.01023 0.00353 -0.0024 1.0000 1.0000
-0.250 0.0035 0.01021 0.00348 -0.0010 1.0000 1.0000
0.000 0.0206 0.01024 0.00352 0.0004 1.0000 1.0000
0.250 0.0355 0.01037 0.00368 0.0019 1.0000 1.0000
0.500 0.0883 0.01052 0.00390 -0.0039 0.9726 1.0000
0.750 0.1590 0.01054 0.00394 -0.0120 0.9136 1.0000
1.000 0.1984 0.01067 0.00392 -0.0132 0.8429 1.0000
1.250 0.2207 0.01094 0.00395 -0.0110 0.7832 1.0000
1.500 0.2418 0.01125 0.00405 -0.0088 0.7306 1.0000
1.750 0.2636 0.01159 0.00416 -0.0070 0.6840 1.0000
2.000 0.2862 0.01194 0.00429 -0.0054 0.6404 1.0000
2.250 0.3094 0.01229 0.00444 -0.0041 0.5987 1.0000
2.500 0.3331 0.01265 0.00464 -0.0029 0.5595 1.0000
2.750 0.3570 0.01304 0.00483 -0.0018 0.5241 1.0000
3.000 0.3815 0.01342 0.00509 -0.0009 0.4889 1.0000
3.250 0.4061 0.01384 0.00536 -0.0001 0.4567 1.0000
3.500 0.4309 0.01428 0.00569 0.0007 0.4263 1.0000
3.750 0.4558 0.01474 0.00603 0.0014 0.3972 1.0000
4.000 0.4808 0.01522 0.00642 0.0021 0.3692 1.0000
4.250 0.5059 0.01572 0.00687 0.0027 0.3419 1.0000
4.500 0.5310 0.01624 0.00734 0.0033 0.3158 1.0000
4.750 0.5560 0.01680 0.00783 0.0039 0.2915 1.0000
5.000 0.5809 0.01740 0.00834 0.0045 0.2684 1.0000
5.250 0.6060 0.01805 0.00906 0.0051 0.2457 1.0000
5.500 0.6307 0.01875 0.00963 0.0056 0.2250 1.0000
5.750 0.6557 0.01952 0.01053 0.0062 0.2041 1.0000
6.000 0.6802 0.02032 0.01127 0.0067 0.1850 1.0000
6.250 0.7046 0.02129 0.01223 0.0073 0.1671 1.0000
6.500 0.7288 0.02223 0.01334 0.0079 0.1495 1.0000
6.750 0.7528 0.02338 0.01457 0.0085 0.1348 1.0000
7.000 0.7765 0.02462 0.01591 0.0091 0.1214 1.0000
7.250 0.7998 0.02606 0.01744 0.0097 0.1099 1.0000
7.500 0.8232 0.02786 0.01922 0.0102 0.1014 1.0000
7.750 0.8448 0.02981 0.02171 0.0111 0.0933 1.0000
8.000 0.8660 0.03191 0.02386 0.0116 0.0867 1.0000
8.250 0.8837 0.03495 0.02759 0.0125 0.0825 1.0000
8.500 0.9021 0.03760 0.03054 0.0132 0.0785 1.0000
8.750 0.9171 0.04082 0.03392 0.0135 0.0743 1.0000
9.000 0.9218 0.04541 0.03930 0.0141 0.0721 1.0000
9.250 0.9193 0.05110 0.04559 0.0140 0.0714 1.0000
9.500 0.9081 0.05741 0.05235 0.0131 0.0716 1.0000
9.750 0.8904 0.06382 0.05903 0.0112 0.0724 1.0000
10.000 0.8695 0.06976 0.06509 0.0089 0.0733 1.0000
10.250 0.8506 0.07618 0.07154 0.0050 0.0742 1.0000
10.500 0.8396 0.08298 0.07837 0.0012 0.0752 1.0000
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Polar data table (+)
Polar graphs
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