S6061 9% (s6061-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 100,000 Max Cl/Cd: 50.11 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6061-il-100000-n5.txt Download as CSV file: xf-s6061-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5007 0.08868 0.08382 -0.0194 1.0000 0.0205
-8.750 -0.5024 0.08398 0.07919 -0.0221 1.0000 0.0201
-8.500 -0.5057 0.07898 0.07425 -0.0253 1.0000 0.0196
-8.250 -0.5116 0.07345 0.06879 -0.0298 1.0000 0.0194
-8.000 -0.5201 0.06744 0.06279 -0.0348 1.0000 0.0189
-7.750 -0.5267 0.06114 0.05641 -0.0385 1.0000 0.0184
-7.500 -0.5315 0.05504 0.05011 -0.0406 1.0000 0.0178
-7.250 -0.5342 0.04910 0.04385 -0.0415 1.0000 0.0173
-7.000 -0.5341 0.04339 0.03769 -0.0412 1.0000 0.0168
-6.750 -0.5268 0.03980 0.03369 -0.0402 1.0000 0.0169
-6.500 -0.5159 0.03749 0.03118 -0.0390 1.0000 0.0176
-6.250 -0.5044 0.03520 0.02863 -0.0375 1.0000 0.0185
-6.000 -0.4923 0.03280 0.02587 -0.0358 1.0000 0.0195
-5.750 -0.4791 0.03040 0.02306 -0.0339 1.0000 0.0201
-5.500 -0.4643 0.02803 0.02027 -0.0320 1.0000 0.0205
-5.250 -0.4479 0.02596 0.01782 -0.0301 1.0000 0.0209
-5.000 -0.4302 0.02420 0.01575 -0.0284 1.0000 0.0213
-4.750 -0.3993 0.02236 0.01359 -0.0291 0.9954 0.0222
-4.500 -0.3664 0.02059 0.01162 -0.0304 0.9890 0.0235
-4.250 -0.3314 0.01938 0.01033 -0.0322 0.9832 0.0269
-4.000 -0.2985 0.01835 0.00917 -0.0335 0.9758 0.0328
-3.750 -0.2622 0.01726 0.00794 -0.0353 0.9702 0.0436
-3.500 -0.2312 0.01605 0.00706 -0.0364 0.9623 0.0951
-3.250 -0.1969 0.01490 0.00651 -0.0385 0.9567 0.2178
-3.000 -0.1681 0.01407 0.00616 -0.0392 0.9478 0.3421
-2.750 -0.1383 0.01327 0.00595 -0.0398 0.9406 0.4949
-2.500 -0.1112 0.01277 0.00591 -0.0391 0.9320 0.6362
-2.250 -0.0842 0.01258 0.00589 -0.0379 0.9235 0.7345
-2.000 -0.0543 0.01251 0.00584 -0.0373 0.9159 0.8024
-1.750 -0.0255 0.01249 0.00578 -0.0366 0.9065 0.8508
-1.500 0.0101 0.01247 0.00566 -0.0374 0.8995 0.8901
-1.250 0.0486 0.01245 0.00550 -0.0389 0.8910 0.9214
-1.000 0.0925 0.01240 0.00532 -0.0418 0.8836 0.9467
-0.750 0.1381 0.01233 0.00512 -0.0451 0.8754 0.9676
-0.500 0.1862 0.01223 0.00489 -0.0492 0.8663 0.9845
-0.250 0.2326 0.01209 0.00464 -0.0530 0.8570 1.0000
0.000 0.2542 0.01208 0.00454 -0.0519 0.8437 1.0000
0.250 0.2757 0.01208 0.00445 -0.0506 0.8302 1.0000
0.500 0.2973 0.01209 0.00439 -0.0494 0.8166 1.0000
0.750 0.3191 0.01212 0.00435 -0.0481 0.8028 1.0000
1.000 0.3413 0.01216 0.00434 -0.0469 0.7889 1.0000
1.250 0.3638 0.01221 0.00434 -0.0458 0.7749 1.0000
1.500 0.3867 0.01227 0.00435 -0.0447 0.7608 1.0000
1.750 0.4099 0.01234 0.00438 -0.0436 0.7463 1.0000
2.000 0.4335 0.01242 0.00443 -0.0426 0.7311 1.0000
2.250 0.4574 0.01251 0.00452 -0.0417 0.7151 1.0000
2.500 0.4815 0.01261 0.00460 -0.0408 0.6986 1.0000
2.750 0.5059 0.01272 0.00470 -0.0399 0.6818 1.0000
3.000 0.5305 0.01284 0.00480 -0.0391 0.6645 1.0000
3.250 0.5551 0.01297 0.00495 -0.0383 0.6462 1.0000
3.500 0.5797 0.01312 0.00511 -0.0375 0.6258 1.0000
3.750 0.6043 0.01329 0.00526 -0.0366 0.6047 1.0000
4.000 0.6287 0.01347 0.00546 -0.0358 0.5813 1.0000
4.250 0.6531 0.01369 0.00572 -0.0350 0.5565 1.0000
4.500 0.6773 0.01393 0.00596 -0.0342 0.5296 1.0000
4.750 0.7012 0.01421 0.00623 -0.0334 0.4998 1.0000
5.000 0.7246 0.01453 0.00652 -0.0324 0.4670 1.0000
5.250 0.7477 0.01492 0.00691 -0.0316 0.4308 1.0000
5.500 0.7701 0.01538 0.00730 -0.0306 0.3917 1.0000
5.750 0.7918 0.01594 0.00776 -0.0296 0.3492 1.0000
6.000 0.8117 0.01668 0.00827 -0.0285 0.2940 1.0000
6.250 0.8304 0.01760 0.00888 -0.0274 0.2315 1.0000
6.500 0.8485 0.01866 0.00960 -0.0265 0.1665 1.0000
6.750 0.8659 0.01990 0.01047 -0.0254 0.1069 1.0000
7.000 0.8836 0.02118 0.01159 -0.0243 0.0658 1.0000
7.250 0.9002 0.02262 0.01291 -0.0230 0.0463 1.0000
7.500 0.9180 0.02386 0.01427 -0.0217 0.0391 1.0000
7.750 0.9335 0.02530 0.01579 -0.0202 0.0352 1.0000
8.000 0.9492 0.02669 0.01734 -0.0187 0.0331 1.0000
8.250 0.9659 0.02798 0.01881 -0.0173 0.0305 1.0000
8.500 0.9821 0.02929 0.02023 -0.0161 0.0279 1.0000
8.750 0.9966 0.03086 0.02190 -0.0147 0.0263 1.0000
9.000 1.0104 0.03299 0.02416 -0.0133 0.0252 1.0000
9.250 1.0276 0.03497 0.02633 -0.0121 0.0245 1.0000
9.500 1.0447 0.03715 0.02878 -0.0110 0.0239 1.0000
9.750 1.0600 0.03962 0.03155 -0.0097 0.0233 1.0000
10.000 1.0718 0.04225 0.03453 -0.0083 0.0226 1.0000
10.250 1.0793 0.04469 0.03730 -0.0067 0.0215 1.0000
10.500 1.0830 0.04697 0.03985 -0.0049 0.0204 1.0000
10.750 1.0818 0.04944 0.04257 -0.0028 0.0197 1.0000
11.000 1.0771 0.05228 0.04567 -0.0010 0.0194 1.0000
11.250 1.0692 0.05548 0.04913 0.0004 0.0192 1.0000
11.500 1.0582 0.05914 0.05306 0.0012 0.0191 1.0000
11.750 1.0453 0.06312 0.05727 0.0010 0.0189 1.0000
12.000 1.0289 0.06792 0.06233 -0.0001 0.0190 1.0000
12.250 1.0108 0.07337 0.06801 -0.0023 0.0190 1.0000
12.500 0.9898 0.07993 0.07480 -0.0060 0.0192 1.0000
12.750 0.9654 0.08802 0.08309 -0.0113 0.0194 1.0000
13.000 0.9339 0.09903 0.09430 -0.0191 0.0199 1.0000
13.250 0.8944 0.11470 0.11008 -0.0298 0.0210 1.0000
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Polar data table (+)
Polar graphs
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