S6063 7.05% (s6063-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 500,000 Max Cl/Cd: 74.79 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6063-il-500000.txt Download as CSV file: xf-s6063-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S6063 7.05%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.5221 0.05473 0.05230 -0.0322 1.0000 0.0172
-6.750 -0.5246 0.04598 0.04326 -0.0354 1.0000 0.0176
-6.500 -0.5169 0.04126 0.03841 -0.0365 1.0000 0.0185
-6.250 -0.5002 0.03967 0.03679 -0.0367 1.0000 0.0196
-6.000 -0.4825 0.03730 0.03427 -0.0369 1.0000 0.0215
-5.750 -0.4589 0.03528 0.03194 -0.0363 1.0000 0.0249
-5.500 -0.4378 0.03427 0.03056 -0.0353 1.0000 0.0255
-5.250 -0.4331 0.02688 0.02284 -0.0348 1.0000 0.0277
-5.000 -0.4163 0.02529 0.02118 -0.0335 1.0000 0.0291
-4.750 -0.4000 0.02377 0.01950 -0.0319 1.0000 0.0314
-4.500 -0.3787 0.02475 0.02028 -0.0297 0.9999 0.0359
-4.250 -0.3447 0.01627 0.01077 -0.0298 0.9972 0.0179
-4.000 -0.3102 0.01343 0.00769 -0.0309 0.9947 0.0145
-3.750 -0.2761 0.01174 0.00578 -0.0318 0.9910 0.0135
-3.500 -0.2402 0.01069 0.00463 -0.0335 0.9873 0.0141
-3.250 -0.2024 0.00995 0.00381 -0.0355 0.9844 0.0153
-3.000 -0.1672 0.00943 0.00323 -0.0371 0.9797 0.0166
-2.750 -0.1318 0.00893 0.00262 -0.0386 0.9746 0.0187
-2.500 -0.0965 0.00854 0.00219 -0.0400 0.9695 0.0256
-2.250 -0.0676 0.00759 0.00187 -0.0406 0.9607 0.1805
-2.000 -0.0397 0.00698 0.00172 -0.0408 0.9514 0.3135
-1.750 -0.0154 0.00619 0.00164 -0.0404 0.9411 0.5118
-1.500 0.0072 0.00567 0.00158 -0.0391 0.9299 0.6583
-1.250 0.0271 0.00521 0.00160 -0.0369 0.9178 0.7983
-1.000 0.0478 0.00502 0.00160 -0.0347 0.9057 0.8755
-0.750 0.0717 0.00494 0.00157 -0.0331 0.8939 0.9272
-0.500 0.1062 0.00491 0.00148 -0.0341 0.8828 0.9640
-0.250 0.1465 0.00488 0.00139 -0.0366 0.8713 0.9862
0.000 0.1874 0.00487 0.00129 -0.0393 0.8584 1.0000
0.250 0.2112 0.00490 0.00124 -0.0383 0.8423 1.0000
0.500 0.2355 0.00494 0.00121 -0.0375 0.8255 1.0000
0.750 0.2601 0.00499 0.00118 -0.0367 0.8074 1.0000
1.000 0.2852 0.00506 0.00116 -0.0359 0.7886 1.0000
1.250 0.3107 0.00514 0.00117 -0.0353 0.7677 1.0000
1.500 0.3363 0.00523 0.00118 -0.0347 0.7456 1.0000
1.750 0.3621 0.00534 0.00120 -0.0342 0.7212 1.0000
2.000 0.3880 0.00547 0.00124 -0.0337 0.6937 1.0000
2.250 0.4139 0.00562 0.00129 -0.0332 0.6628 1.0000
2.500 0.4390 0.00587 0.00136 -0.0325 0.6126 1.0000
2.750 0.4637 0.00621 0.00144 -0.0319 0.5499 1.0000
3.000 0.4890 0.00654 0.00156 -0.0315 0.4942 1.0000
3.250 0.5137 0.00701 0.00171 -0.0310 0.4174 1.0000
3.500 0.5378 0.00762 0.00194 -0.0306 0.3255 1.0000
3.750 0.5617 0.00832 0.00222 -0.0303 0.2286 1.0000
4.000 0.5848 0.00926 0.00263 -0.0299 0.1156 1.0000
4.250 0.6077 0.01035 0.00323 -0.0293 0.0227 1.0000
4.500 0.6338 0.01078 0.00369 -0.0289 0.0183 1.0000
4.750 0.6596 0.01130 0.00434 -0.0285 0.0171 1.0000
5.000 0.6851 0.01186 0.00500 -0.0280 0.0168 1.0000
5.250 0.7103 0.01246 0.00567 -0.0275 0.0162 1.0000
5.500 0.7350 0.01312 0.00641 -0.0270 0.0154 1.0000
5.750 0.7589 0.01397 0.00736 -0.0263 0.0151 1.0000
6.000 0.7823 0.01496 0.00845 -0.0255 0.0148 1.0000
6.250 0.8054 0.01612 0.00972 -0.0247 0.0145 1.0000
6.500 0.8283 0.01762 0.01135 -0.0237 0.0145 1.0000
6.750 0.8512 0.01967 0.01359 -0.0226 0.0151 1.0000
7.000 0.8726 0.02295 0.01716 -0.0214 0.0165 1.0000
8.500 0.9627 0.04480 0.04136 -0.0124 0.0224 1.0000
8.750 0.9696 0.04789 0.04471 -0.0112 0.0209 1.0000
9.000 0.9754 0.05049 0.04747 -0.0103 0.0197 1.0000
9.250 0.9779 0.05337 0.05049 -0.0094 0.0192 1.0000
9.500 0.9838 0.05570 0.05284 -0.0088 0.0185 1.0000
9.750 0.9747 0.05950 0.05678 -0.0078 0.0182 1.0000
10.000 0.9567 0.06295 0.06036 -0.0061 0.0180 1.0000
10.250 0.9375 0.06680 0.06435 -0.0064 0.0181 1.0000
10.500 0.9149 0.07229 0.07002 -0.0098 0.0184 1.0000
10.750 0.8430 0.10030 0.09823 -0.0327 0.0206 1.0000
11.000 0.8349 0.10770 0.10561 -0.0370 0.0205 1.0000
11.250 0.8314 0.11353 0.11142 -0.0402 0.0200 1.0000
11.500 0.8304 0.11863 0.11651 -0.0427 0.0194 1.0000
11.750 0.7003 0.12483 0.12288 -0.0428 0.0230 1.0000
12.000 0.6962 0.13024 0.12828 -0.0455 0.0220 1.0000
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Polar data table (+)
Polar graphs
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