S5020 (s5020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.72 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5020-il-1000000-n5.txt Download as CSV file: xf-s5020-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5558 0.08555 0.08340 0.0207 0.7224 0.0044
-7.750 -0.5626 0.08186 0.07970 0.0188 0.7125 0.0045
-7.500 -0.5645 0.07713 0.07494 0.0147 0.7034 0.0045
-7.250 -0.5606 0.07215 0.06992 0.0104 0.6954 0.0048
-7.000 -0.5550 0.06637 0.06405 0.0060 0.6879 0.0049
-6.750 -0.5479 0.05935 0.05691 0.0016 0.6811 0.0052
-6.500 -0.5445 0.04656 0.04379 -0.0030 0.6766 0.0059
-6.250 -0.5317 0.03917 0.03608 -0.0043 0.6709 0.0061
-6.000 -0.5118 0.03574 0.03242 -0.0045 0.6633 0.0063
-5.750 -0.4907 0.03259 0.02905 -0.0045 0.6561 0.0064
-5.500 -0.4688 0.02954 0.02576 -0.0042 0.6487 0.0067
-5.250 -0.4461 0.02668 0.02266 -0.0038 0.6418 0.0071
-5.000 -0.4261 0.02045 0.01580 -0.0023 0.6356 0.0081
-4.750 -0.4022 0.01764 0.01256 -0.0015 0.6290 0.0086
-4.500 -0.3764 0.01627 0.01093 -0.0010 0.6211 0.0088
-4.250 -0.3499 0.01526 0.00971 -0.0006 0.6139 0.0090
-4.000 -0.3232 0.01443 0.00869 -0.0003 0.6058 0.0091
-3.500 -0.2706 0.01211 0.00600 0.0005 0.5907 0.0098
-3.250 -0.2436 0.01147 0.00527 0.0007 0.5832 0.0100
-3.000 -0.2164 0.01100 0.00471 0.0010 0.5751 0.0103
-2.750 -0.1890 0.01059 0.00424 0.0012 0.5672 0.0106
-2.500 -0.1615 0.01024 0.00382 0.0014 0.5591 0.0110
-2.250 -0.1340 0.00990 0.00342 0.0016 0.5507 0.0114
-2.000 -0.1065 0.00960 0.00306 0.0018 0.5428 0.0119
-1.750 -0.0789 0.00932 0.00272 0.0020 0.5340 0.0123
-1.500 -0.0512 0.00908 0.00242 0.0022 0.5259 0.0126
-1.250 -0.0235 0.00886 0.00214 0.0024 0.5171 0.0128
-1.000 0.0044 0.00868 0.00192 0.0025 0.5081 0.0132
-0.750 0.0324 0.00856 0.00175 0.0026 0.4995 0.0136
-0.250 0.0884 0.00830 0.00139 0.0028 0.4803 0.0139
0.000 0.1164 0.00816 0.00118 0.0029 0.4712 0.0146
0.250 0.1445 0.00807 0.00103 0.0030 0.4613 0.0162
0.500 0.1727 0.00802 0.00095 0.0030 0.4512 0.0178
0.750 0.2009 0.00800 0.00090 0.0031 0.4411 0.0196
1.000 0.2291 0.00798 0.00087 0.0031 0.4306 0.0285
1.250 0.2527 0.00688 0.00085 0.0033 0.4202 0.4374
1.500 0.2692 0.00557 0.00086 0.0056 0.4104 0.8522
1.750 0.3223 0.00549 0.00097 0.0004 0.3951 0.9869
2.000 0.3776 0.00561 0.00098 -0.0056 0.3782 1.0000
2.250 0.4044 0.00571 0.00101 -0.0054 0.3666 1.0000
2.500 0.4311 0.00581 0.00106 -0.0051 0.3541 1.0000
2.750 0.4579 0.00593 0.00111 -0.0048 0.3413 1.0000
3.000 0.4847 0.00606 0.00117 -0.0046 0.3280 1.0000
3.250 0.5114 0.00619 0.00125 -0.0044 0.3148 1.0000
3.500 0.5382 0.00634 0.00134 -0.0042 0.3009 1.0000
3.750 0.5649 0.00650 0.00143 -0.0040 0.2860 1.0000
4.000 0.5916 0.00668 0.00154 -0.0038 0.2713 1.0000
4.250 0.6182 0.00684 0.00165 -0.0036 0.2586 1.0000
4.500 0.6449 0.00703 0.00179 -0.0034 0.2446 1.0000
4.750 0.6715 0.00722 0.00193 -0.0032 0.2314 1.0000
5.000 0.6980 0.00742 0.00208 -0.0030 0.2190 1.0000
5.250 0.7245 0.00763 0.00224 -0.0029 0.2051 1.0000
5.500 0.7510 0.00785 0.00242 -0.0027 0.1940 1.0000
5.750 0.7774 0.00808 0.00261 -0.0025 0.1810 1.0000
6.000 0.8036 0.00833 0.00281 -0.0023 0.1683 1.0000
6.250 0.8299 0.00858 0.00302 -0.0022 0.1566 1.0000
6.500 0.8559 0.00886 0.00327 -0.0020 0.1430 1.0000
6.750 0.8817 0.00920 0.00353 -0.0019 0.1275 1.0000
7.000 0.9072 0.00958 0.00384 -0.0017 0.1090 1.0000
7.250 0.9327 0.00996 0.00415 -0.0015 0.0945 1.0000
7.500 0.9580 0.01036 0.00448 -0.0014 0.0810 1.0000
7.750 0.9833 0.01074 0.00483 -0.0012 0.0700 1.0000
8.000 1.0082 0.01119 0.00523 -0.0010 0.0573 1.0000
8.250 1.0325 0.01174 0.00569 -0.0008 0.0430 1.0000
8.500 1.0568 0.01226 0.00616 -0.0006 0.0322 1.0000
8.750 1.0802 0.01291 0.00674 -0.0004 0.0199 1.0000
9.000 1.1017 0.01389 0.00763 0.0000 0.0053 1.0000
9.250 1.1255 0.01439 0.00817 0.0003 0.0043 1.0000
9.500 1.1490 0.01492 0.00875 0.0006 0.0036 1.0000
9.750 1.1723 0.01546 0.00935 0.0009 0.0032 1.0000
10.000 1.1953 0.01598 0.00993 0.0013 0.0030 1.0000
10.250 1.2178 0.01655 0.01057 0.0016 0.0028 1.0000
10.500 1.2396 0.01718 0.01127 0.0020 0.0026 1.0000
10.750 1.2606 0.01784 0.01201 0.0025 0.0024 1.0000
11.000 1.2805 0.01862 0.01285 0.0030 0.0022 1.0000
11.250 1.2992 0.01944 0.01375 0.0036 0.0021 1.0000
11.500 1.3154 0.02046 0.01487 0.0044 0.0020 1.0000
11.750 1.3297 0.02154 0.01607 0.0053 0.0019 1.0000
12.000 1.3385 0.02299 0.01764 0.0066 0.0018 1.0000
12.250 1.3475 0.02406 0.01880 0.0079 0.0018 1.0000
12.500 1.3457 0.02573 0.02058 0.0096 0.0018 1.0000
12.750 1.3529 0.02711 0.02204 0.0103 0.0017 1.0000
13.000 1.3537 0.02930 0.02435 0.0105 0.0017 1.0000
13.250 1.3578 0.03136 0.02650 0.0105 0.0017 1.0000
13.500 1.3592 0.03382 0.02907 0.0102 0.0017 1.0000
13.750 1.3583 0.03667 0.03203 0.0096 0.0016 1.0000
14.000 1.3550 0.03995 0.03541 0.0087 0.0017 1.0000
14.250 1.3500 0.04352 0.03911 0.0076 0.0016 1.0000
14.500 1.3429 0.04752 0.04323 0.0062 0.0016 1.0000
14.750 1.3364 0.05156 0.04738 0.0047 0.0016 1.0000
15.000 1.3242 0.05651 0.05245 0.0027 0.0016 1.0000
15.250 1.3144 0.06127 0.05732 0.0007 0.0016 1.0000
15.500 1.3061 0.06603 0.06219 -0.0014 0.0015 1.0000
15.750 1.2911 0.07204 0.06833 -0.0042 0.0016 1.0000
16.000 1.2856 0.07665 0.07303 -0.0064 0.0015 1.0000
16.250 1.2595 0.08506 0.08159 -0.0105 0.0016 1.0000
16.500 1.2533 0.09012 0.08674 -0.0130 0.0015 1.0000
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Polar data table (+)
Polar graphs
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