S2062 8% (s2062-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 50,000 Max Cl/Cd: 35.95 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2062-il-50000.txt Download as CSV file: xf-s2062-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4657 0.09594 0.08914 -0.0084 1.0000 0.2654
-7.750 -0.4683 0.09317 0.08647 -0.0085 1.0000 0.2770
-7.500 -0.4882 0.09217 0.08564 -0.0089 1.0000 0.2880
-7.250 -0.4882 0.08914 0.08269 -0.0078 1.0000 0.3023
-7.000 -0.4808 0.08556 0.07912 -0.0065 1.0000 0.3161
-6.750 -0.4830 0.08264 0.07630 -0.0059 1.0000 0.3306
-6.500 -0.4790 0.07913 0.07287 -0.0046 1.0000 0.3456
-6.250 -0.5008 0.06238 0.05571 -0.0366 1.0000 0.1615
-6.000 -0.4888 0.05467 0.04766 -0.0396 1.0000 0.1299
-5.750 -0.4781 0.04834 0.04071 -0.0417 1.0000 0.1175
-5.500 -0.4631 0.04396 0.03606 -0.0416 1.0000 0.1148
-5.250 -0.4459 0.03953 0.03110 -0.0415 1.0000 0.1123
-5.000 -0.4261 0.03574 0.02673 -0.0411 1.0000 0.1139
-4.750 -0.4054 0.03272 0.02327 -0.0404 1.0000 0.1230
-4.500 -0.3823 0.02984 0.01978 -0.0395 1.0000 0.1344
-4.250 -0.3605 0.02774 0.01761 -0.0384 1.0000 0.1569
-4.000 -0.3375 0.02573 0.01536 -0.0373 1.0000 0.1881
-3.750 -0.3154 0.02400 0.01374 -0.0361 1.0000 0.2246
-3.500 -0.2923 0.02242 0.01221 -0.0348 1.0000 0.2673
-3.250 -0.2696 0.02097 0.01093 -0.0335 1.0000 0.3225
-3.000 -0.2476 0.01954 0.00984 -0.0320 1.0000 0.4061
-2.750 -0.2305 0.01788 0.00913 -0.0290 1.0000 0.5510
-2.500 -0.2297 0.01680 0.00920 -0.0203 1.0000 0.7673
-2.250 -0.1482 0.01632 0.00814 -0.0280 1.0000 1.0000
-2.000 -0.1359 0.01617 0.00759 -0.0265 1.0000 1.0000
-1.750 -0.1188 0.01613 0.00721 -0.0254 1.0000 1.0000
-1.500 -0.0998 0.01616 0.00692 -0.0245 1.0000 1.0000
-1.250 -0.0799 0.01622 0.00672 -0.0238 1.0000 1.0000
-1.000 -0.0595 0.01633 0.00659 -0.0231 1.0000 1.0000
-0.750 -0.0389 0.01647 0.00650 -0.0225 1.0000 1.0000
-0.500 -0.0182 0.01665 0.00649 -0.0219 1.0000 1.0000
-0.250 0.0025 0.01686 0.00655 -0.0213 1.0000 1.0000
0.000 0.0232 0.01711 0.00666 -0.0208 1.0000 1.0000
0.250 0.0437 0.01739 0.00683 -0.0203 1.0000 1.0000
0.500 0.0639 0.01772 0.00704 -0.0199 1.0000 1.0000
0.750 0.0840 0.01808 0.00734 -0.0195 1.0000 1.0000
1.000 0.1036 0.01850 0.00769 -0.0191 1.0000 1.0000
1.250 0.1230 0.01896 0.00812 -0.0188 1.0000 1.0000
1.500 0.1419 0.01948 0.00862 -0.0185 1.0000 1.0000
1.750 0.1604 0.02005 0.00919 -0.0183 1.0000 1.0000
2.000 0.1784 0.02070 0.00984 -0.0182 1.0000 1.0000
2.250 0.1958 0.02143 0.01059 -0.0181 1.0000 1.0000
2.500 0.2126 0.02223 0.01144 -0.0181 1.0000 1.0000
2.750 0.2688 0.02371 0.01306 -0.0255 0.9802 1.0000
3.000 0.3332 0.02502 0.01457 -0.0338 0.9535 1.0000
3.250 0.3945 0.02594 0.01577 -0.0408 0.9249 1.0000
3.500 0.4532 0.02649 0.01660 -0.0465 0.8947 1.0000
3.750 0.5137 0.02662 0.01707 -0.0516 0.8631 1.0000
4.000 0.5855 0.02597 0.01693 -0.0571 0.8307 1.0000
4.250 0.6360 0.02518 0.01652 -0.0582 0.7940 1.0000
4.500 0.6847 0.02395 0.01569 -0.0578 0.7544 1.0000
4.750 0.7229 0.02284 0.01483 -0.0554 0.7081 1.0000
5.000 0.7530 0.02209 0.01417 -0.0519 0.6532 1.0000
5.250 0.7778 0.02182 0.01379 -0.0480 0.5887 1.0000
5.500 0.7963 0.02215 0.01393 -0.0440 0.5128 1.0000
5.750 0.8111 0.02295 0.01430 -0.0401 0.4277 1.0000
6.000 0.8214 0.02434 0.01507 -0.0361 0.3309 1.0000
6.250 0.8273 0.02633 0.01626 -0.0323 0.2285 1.0000
6.500 0.8425 0.02906 0.01837 -0.0301 0.1580 1.0000
6.750 0.8684 0.03188 0.02089 -0.0291 0.1286 1.0000
7.000 0.8970 0.03485 0.02402 -0.0285 0.1155 1.0000
7.250 0.9206 0.03766 0.02731 -0.0272 0.1069 1.0000
7.500 0.9424 0.04080 0.03062 -0.0264 0.1000 1.0000
7.750 0.9605 0.04445 0.03490 -0.0248 0.0981 1.0000
8.000 0.9746 0.04854 0.03956 -0.0231 0.0976 1.0000
8.250 0.9847 0.05296 0.04451 -0.0215 0.0981 1.0000
8.500 0.9911 0.05765 0.04965 -0.0200 0.0993 1.0000
8.750 0.9975 0.06263 0.05494 -0.0188 0.1007 1.0000
9.000 0.9827 0.06786 0.06086 -0.0172 0.1045 1.0000
9.250 0.9579 0.07393 0.06734 -0.0167 0.1086 1.0000
9.500 0.9438 0.07943 0.07298 -0.0167 0.1117 1.0000
9.750 0.9520 0.08499 0.07860 -0.0167 0.1154 1.0000
10.000 0.8802 0.09271 0.08640 -0.0227 0.1194 1.0000
10.250 0.8621 0.10146 0.09509 -0.0284 0.1260 1.0000
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Polar data table (+)
Polar graphs
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