S5020 (s5020-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S5020 (s5020-il) Reynolds number: 200,000 Max Cl/Cd: 63.65 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5020-il-200000-n5.txt Download as CSV file: xf-s5020-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4378 0.08516 0.08240 0.0126 0.8970 0.0200
-7.750 -0.4390 0.08143 0.07861 0.0122 0.8712 0.0202
-7.500 -0.4405 0.07758 0.07474 0.0115 0.8520 0.0203
-7.250 -0.4432 0.07361 0.07075 0.0101 0.8357 0.0204
-7.000 -0.4497 0.06956 0.06667 0.0079 0.8208 0.0204
-6.750 -0.4508 0.06493 0.06198 0.0051 0.8085 0.0205
-6.500 -0.4483 0.06012 0.05709 0.0025 0.7975 0.0206
-6.250 -0.4431 0.05518 0.05205 0.0001 0.7874 0.0207
-6.000 -0.4349 0.05011 0.04686 -0.0022 0.7775 0.0208
-5.750 -0.4247 0.04477 0.04134 -0.0044 0.7686 0.0207
-5.500 -0.4047 0.04041 0.03666 -0.0059 0.7604 0.0192
-5.250 -0.4089 0.04489 0.04055 -0.0092 0.7749 0.0130
-5.000 -0.3905 0.04078 0.03614 -0.0095 0.7644 0.0127
-4.750 -0.3700 0.03681 0.03183 -0.0094 0.7548 0.0126
-4.500 -0.3473 0.03280 0.02735 -0.0088 0.7460 0.0130
-4.250 -0.3256 0.02974 0.02393 -0.0086 0.7362 0.0142
-4.000 -0.3019 0.02857 0.02258 -0.0085 0.7266 0.0155
-3.750 -0.2770 0.02548 0.01900 -0.0076 0.7182 0.0154
-3.500 -0.2509 0.02263 0.01564 -0.0066 0.7093 0.0151
-3.250 -0.2244 0.02049 0.01306 -0.0058 0.7012 0.0152
-3.000 -0.1974 0.01884 0.01103 -0.0051 0.6922 0.0155
-2.750 -0.1702 0.01749 0.00941 -0.0045 0.6836 0.0161
-2.500 -0.1432 0.01636 0.00805 -0.0039 0.6753 0.0170
-2.250 -0.1158 0.01562 0.00714 -0.0035 0.6663 0.0189
-2.000 -0.0895 0.01467 0.00611 -0.0029 0.6581 0.0211
-1.750 -0.0629 0.01399 0.00535 -0.0025 0.6492 0.0229
-1.500 -0.0361 0.01342 0.00470 -0.0020 0.6406 0.0254
-1.250 -0.0095 0.01295 0.00413 -0.0016 0.6323 0.0302
-1.000 0.0178 0.01260 0.00371 -0.0013 0.6231 0.0371
-0.750 0.0448 0.01223 0.00329 -0.0009 0.6147 0.0532
-0.500 0.0710 0.01169 0.00299 -0.0006 0.6057 0.1275
-0.250 0.0866 0.00971 0.00283 0.0012 0.5976 0.6299
0.000 0.1697 0.00896 0.00271 -0.0091 0.5854 1.0000
0.250 0.1959 0.00901 0.00259 -0.0087 0.5760 1.0000
0.500 0.2223 0.00906 0.00251 -0.0083 0.5661 1.0000
0.750 0.2486 0.00912 0.00244 -0.0078 0.5566 1.0000
1.000 0.2749 0.00920 0.00238 -0.0074 0.5470 1.0000
1.250 0.3014 0.00927 0.00236 -0.0071 0.5365 1.0000
1.500 0.3279 0.00935 0.00234 -0.0067 0.5263 1.0000
1.750 0.3544 0.00945 0.00234 -0.0063 0.5162 1.0000
2.000 0.3809 0.00954 0.00235 -0.0060 0.5053 1.0000
2.250 0.4075 0.00964 0.00239 -0.0057 0.4940 1.0000
2.500 0.4340 0.00975 0.00245 -0.0053 0.4827 1.0000
2.750 0.4605 0.00988 0.00250 -0.0050 0.4712 1.0000
3.000 0.4870 0.01001 0.00257 -0.0047 0.4592 1.0000
3.250 0.5135 0.01015 0.00266 -0.0044 0.4468 1.0000
3.500 0.5401 0.01030 0.00276 -0.0042 0.4336 1.0000
3.750 0.5666 0.01046 0.00290 -0.0039 0.4202 1.0000
4.000 0.5931 0.01064 0.00303 -0.0037 0.4063 1.0000
4.250 0.6195 0.01083 0.00319 -0.0034 0.3923 1.0000
4.500 0.6459 0.01104 0.00336 -0.0032 0.3777 1.0000
4.750 0.6722 0.01126 0.00358 -0.0030 0.3626 1.0000
5.000 0.6985 0.01150 0.00379 -0.0028 0.3469 1.0000
5.250 0.7247 0.01175 0.00403 -0.0026 0.3305 1.0000
5.500 0.7508 0.01204 0.00429 -0.0024 0.3139 1.0000
5.750 0.7767 0.01235 0.00460 -0.0023 0.2975 1.0000
6.000 0.8025 0.01268 0.00492 -0.0021 0.2813 1.0000
6.250 0.8281 0.01305 0.00526 -0.0019 0.2651 1.0000
6.500 0.8536 0.01342 0.00563 -0.0018 0.2491 1.0000
6.750 0.8790 0.01381 0.00605 -0.0016 0.2332 1.0000
7.000 0.9041 0.01424 0.00648 -0.0014 0.2179 1.0000
7.250 0.9290 0.01469 0.00694 -0.0013 0.2026 1.0000
7.500 0.9536 0.01518 0.00744 -0.0011 0.1873 1.0000
7.750 0.9778 0.01570 0.00800 -0.0009 0.1726 1.0000
8.000 1.0018 0.01625 0.00856 -0.0007 0.1587 1.0000
8.250 1.0255 0.01682 0.00917 -0.0004 0.1456 1.0000
8.500 1.0486 0.01744 0.00982 -0.0002 0.1325 1.0000
8.750 1.0714 0.01809 0.01051 0.0001 0.1206 1.0000
9.000 1.0936 0.01878 0.01127 0.0004 0.1091 1.0000
9.250 1.1152 0.01953 0.01206 0.0007 0.0986 1.0000
9.500 1.1358 0.02036 0.01293 0.0011 0.0895 1.0000
9.750 1.1562 0.02117 0.01382 0.0016 0.0805 1.0000
10.000 1.1755 0.02205 0.01479 0.0021 0.0720 1.0000
10.250 1.1931 0.02307 0.01585 0.0026 0.0641 1.0000
10.500 1.2095 0.02413 0.01698 0.0032 0.0550 1.0000
10.750 1.2255 0.02516 0.01808 0.0038 0.0466 1.0000
11.000 1.2389 0.02635 0.01935 0.0046 0.0403 1.0000
11.250 1.2488 0.02776 0.02080 0.0054 0.0343 1.0000
11.500 1.2567 0.02913 0.02230 0.0065 0.0301 1.0000
11.750 1.2580 0.03092 0.02417 0.0076 0.0266 1.0000
12.000 1.2588 0.03304 0.02639 0.0081 0.0238 1.0000
12.250 1.2602 0.03532 0.02881 0.0083 0.0209 1.0000
12.500 1.2574 0.03820 0.03176 0.0080 0.0185 1.0000
12.750 1.2553 0.04115 0.03484 0.0075 0.0164 1.0000
13.000 1.2528 0.04429 0.03812 0.0068 0.0146 1.0000
13.250 1.2464 0.04805 0.04200 0.0057 0.0137 1.0000
13.500 1.2392 0.05207 0.04612 0.0042 0.0128 1.0000
13.750 1.2287 0.05671 0.05088 0.0024 0.0120 1.0000
14.000 1.2195 0.06132 0.05566 0.0005 0.0116 1.0000
14.250 1.2098 0.06620 0.06070 -0.0016 0.0112 1.0000
14.500 1.1994 0.07130 0.06599 -0.0039 0.0110 1.0000
14.750 1.1878 0.07693 0.07176 -0.0066 0.0107 1.0000
15.000 1.1759 0.08282 0.07781 -0.0095 0.0105 1.0000
15.250 1.1637 0.08900 0.08412 -0.0127 0.0102 1.0000
15.500 1.1517 0.09526 0.09052 -0.0158 0.0103 1.0000
15.750 1.1388 0.10196 0.09735 -0.0193 0.0100 1.0000
16.000 1.1260 0.10878 0.10430 -0.0228 0.0098 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S5020 (s5020-il)