S5020 (s5020-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 100,000 Max Cl/Cd: 48.93 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5020-il-100000-n5.txt Download as CSV file: xf-s5020-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S5020
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4391 0.09378 0.08994 0.0091 1.0000 0.0518
-8.000 -0.4434 0.08981 0.08603 0.0048 1.0000 0.0521
-7.750 -0.4479 0.08560 0.08188 0.0002 1.0000 0.0522
-7.500 -0.4500 0.08098 0.07726 -0.0044 1.0000 0.0524
-7.250 -0.4483 0.07604 0.07226 -0.0085 1.0000 0.0525
-7.000 -0.4376 0.06933 0.06571 -0.0068 1.0000 0.0536
-6.750 -0.4272 0.06479 0.06120 -0.0071 1.0000 0.0547
-6.500 -0.4144 0.05968 0.05607 -0.0095 0.9382 0.0561
-6.250 -0.4063 0.05508 0.05134 -0.0115 0.9046 0.0573
-6.000 -0.4001 0.05078 0.04691 -0.0128 0.8826 0.0584
-5.750 -0.3921 0.04636 0.04233 -0.0140 0.8650 0.0592
-5.500 -0.3949 0.05070 0.04582 -0.0195 0.8978 0.0375
-5.250 -0.3779 0.04707 0.04188 -0.0197 0.8765 0.0375
-5.000 -0.3602 0.04366 0.03812 -0.0194 0.8593 0.0375
-4.750 -0.3421 0.04027 0.03442 -0.0189 0.8444 0.0359
-4.500 -0.3216 0.03681 0.03054 -0.0183 0.8309 0.0340
-4.250 -0.2992 0.03340 0.02660 -0.0174 0.8183 0.0322
-4.000 -0.2751 0.03034 0.02292 -0.0163 0.8065 0.0309
-3.750 -0.2505 0.02802 0.02007 -0.0152 0.7952 0.0304
-3.500 -0.2256 0.02611 0.01775 -0.0143 0.7845 0.0303
-3.250 -0.2006 0.02452 0.01583 -0.0135 0.7741 0.0312
-3.000 -0.1749 0.02341 0.01455 -0.0130 0.7629 0.0336
-2.750 -0.1483 0.02218 0.01303 -0.0123 0.7526 0.0350
-2.500 -0.1218 0.02090 0.01149 -0.0114 0.7431 0.0353
-2.250 -0.0950 0.01980 0.01020 -0.0107 0.7331 0.0358
-2.000 -0.0684 0.01884 0.00909 -0.0100 0.7230 0.0365
-1.750 -0.0427 0.01804 0.00818 -0.0092 0.7138 0.0375
-1.500 -0.0171 0.01737 0.00740 -0.0084 0.7042 0.0388
-1.250 0.0085 0.01675 0.00669 -0.0077 0.6943 0.0409
-1.000 0.0343 0.01632 0.00618 -0.0071 0.6851 0.0474
-0.750 0.0606 0.01591 0.00565 -0.0065 0.6757 0.0560
-0.250 0.1593 0.01235 0.00480 -0.0142 0.6549 1.0000
0.000 0.1844 0.01242 0.00461 -0.0134 0.6458 1.0000
0.250 0.2103 0.01251 0.00451 -0.0129 0.6350 1.0000
0.500 0.2360 0.01260 0.00443 -0.0123 0.6250 1.0000
0.750 0.2614 0.01269 0.00433 -0.0117 0.6155 1.0000
1.000 0.2872 0.01279 0.00430 -0.0112 0.6049 1.0000
1.250 0.3132 0.01291 0.00430 -0.0107 0.5943 1.0000
1.500 0.3390 0.01302 0.00429 -0.0102 0.5840 1.0000
1.750 0.3646 0.01313 0.00428 -0.0095 0.5740 1.0000
2.000 0.3908 0.01326 0.00434 -0.0091 0.5626 1.0000
2.250 0.4169 0.01339 0.00440 -0.0087 0.5511 1.0000
2.500 0.4429 0.01352 0.00449 -0.0083 0.5399 1.0000
2.750 0.4688 0.01366 0.00456 -0.0078 0.5286 1.0000
3.000 0.4948 0.01381 0.00463 -0.0073 0.5172 1.0000
3.250 0.5209 0.01397 0.00476 -0.0069 0.5048 1.0000
3.500 0.5470 0.01413 0.00493 -0.0065 0.4919 1.0000
3.750 0.5731 0.01431 0.00509 -0.0061 0.4786 1.0000
4.000 0.5991 0.01450 0.00526 -0.0058 0.4652 1.0000
4.250 0.6250 0.01470 0.00545 -0.0054 0.4512 1.0000
4.500 0.6509 0.01491 0.00569 -0.0050 0.4368 1.0000
4.750 0.6768 0.01515 0.00592 -0.0047 0.4222 1.0000
5.000 0.7025 0.01540 0.00617 -0.0043 0.4070 1.0000
5.250 0.7281 0.01567 0.00644 -0.0039 0.3916 1.0000
5.500 0.7537 0.01597 0.00680 -0.0036 0.3753 1.0000
5.750 0.7791 0.01630 0.00716 -0.0033 0.3583 1.0000
6.000 0.8043 0.01666 0.00754 -0.0030 0.3412 1.0000
6.250 0.8291 0.01705 0.00794 -0.0027 0.3238 1.0000
6.750 0.8783 0.01795 0.00894 -0.0021 0.2891 1.0000
7.000 0.9024 0.01846 0.00949 -0.0017 0.2719 1.0000
7.250 0.9261 0.01902 0.01008 -0.0014 0.2548 1.0000
7.500 0.9494 0.01962 0.01072 -0.0011 0.2385 1.0000
7.750 0.9723 0.02027 0.01141 -0.0007 0.2223 1.0000
8.000 0.9948 0.02096 0.01222 -0.0004 0.2063 1.0000
8.250 1.0167 0.02170 0.01303 0.0000 0.1908 1.0000
8.500 1.0380 0.02250 0.01391 0.0004 0.1759 1.0000
8.750 1.0585 0.02336 0.01485 0.0009 0.1618 1.0000
9.000 1.0782 0.02428 0.01585 0.0014 0.1486 1.0000
9.250 1.0970 0.02527 0.01698 0.0020 0.1366 1.0000
9.500 1.1145 0.02634 0.01813 0.0026 0.1252 1.0000
9.750 1.1303 0.02753 0.01937 0.0032 0.1150 1.0000
10.000 1.1462 0.02869 0.02073 0.0039 0.1051 1.0000
10.250 1.1597 0.02998 0.02214 0.0047 0.0947 1.0000
10.500 1.1706 0.03137 0.02363 0.0054 0.0839 1.0000
10.750 1.1786 0.03290 0.02524 0.0060 0.0728 1.0000
11.000 1.1819 0.03464 0.02702 0.0068 0.0618 1.0000
11.250 1.1809 0.03680 0.02919 0.0074 0.0526 1.0000
11.500 1.1807 0.03921 0.03177 0.0075 0.0444 1.0000
11.750 1.1786 0.04200 0.03467 0.0073 0.0392 1.0000
12.000 1.1722 0.04550 0.03824 0.0065 0.0339 1.0000
12.250 1.1651 0.04927 0.04214 0.0055 0.0304 1.0000
12.500 1.1564 0.05347 0.04649 0.0041 0.0272 1.0000
12.750 1.1458 0.05812 0.05125 0.0022 0.0256 1.0000
13.000 1.1326 0.06339 0.05661 -0.0002 0.0244 1.0000
13.250 1.1199 0.06878 0.06212 -0.0026 0.0233 1.0000
13.500 1.1092 0.07406 0.06757 -0.0050 0.0226 1.0000
13.750 1.0964 0.07988 0.07355 -0.0077 0.0216 1.0000
14.000 1.0854 0.08563 0.07944 -0.0104 0.0211 1.0000
14.250 1.0739 0.09173 0.08568 -0.0134 0.0204 1.0000
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Polar data table (+)
Polar graphs
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