S6061 9% (s6061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.96 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6061-il-1000000.txt Download as CSV file: xf-s6061-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4492 0.07705 0.07562 -0.0176 1.0000 0.0098
-9.250 -0.4538 0.07175 0.07034 -0.0197 1.0000 0.0099
-5.750 -0.4217 0.01458 0.00992 -0.0437 0.9354 0.0080
-5.500 -0.3997 0.01267 0.00772 -0.0423 0.9259 0.0075
-5.250 -0.3763 0.01156 0.00644 -0.0413 0.9164 0.0074
-5.000 -0.3516 0.01078 0.00555 -0.0406 0.9072 0.0076
-4.750 -0.3266 0.01017 0.00483 -0.0399 0.8986 0.0080
-4.500 -0.3007 0.00970 0.00427 -0.0395 0.8895 0.0088
-4.250 -0.2742 0.00936 0.00386 -0.0391 0.8808 0.0092
-4.000 -0.2485 0.00883 0.00319 -0.0386 0.8722 0.0098
-3.750 -0.2217 0.00841 0.00269 -0.0383 0.8630 0.0107
-3.500 -0.1946 0.00816 0.00239 -0.0381 0.8543 0.0123
-3.250 -0.1675 0.00789 0.00204 -0.0378 0.8452 0.0164
-3.000 -0.1412 0.00737 0.00173 -0.0376 0.8357 0.0674
-2.750 -0.1144 0.00705 0.00155 -0.0375 0.8265 0.1127
-2.500 -0.0877 0.00674 0.00140 -0.0374 0.8166 0.1678
-2.250 -0.0611 0.00635 0.00126 -0.0373 0.8061 0.2500
-2.000 -0.0349 0.00590 0.00114 -0.0372 0.7956 0.3561
-1.750 -0.0086 0.00553 0.00104 -0.0371 0.7850 0.4539
-1.500 0.0178 0.00522 0.00096 -0.0369 0.7739 0.5463
-1.250 0.0442 0.00494 0.00092 -0.0367 0.7625 0.6333
-1.000 0.0709 0.00477 0.00090 -0.0364 0.7511 0.6961
-0.750 0.0979 0.00468 0.00088 -0.0361 0.7395 0.7409
-0.500 0.1248 0.00462 0.00087 -0.0358 0.7273 0.7763
-0.250 0.1518 0.00459 0.00087 -0.0355 0.7146 0.8062
0.000 0.1788 0.00458 0.00087 -0.0352 0.7016 0.8309
0.250 0.2057 0.00458 0.00088 -0.0348 0.6885 0.8530
0.500 0.2324 0.00459 0.00090 -0.0344 0.6753 0.8733
0.750 0.2588 0.00460 0.00092 -0.0340 0.6620 0.8928
1.000 0.2849 0.00463 0.00094 -0.0335 0.6482 0.9116
1.250 0.3107 0.00466 0.00097 -0.0328 0.6338 0.9296
1.500 0.3367 0.00471 0.00100 -0.0322 0.6187 0.9479
1.750 0.3654 0.00477 0.00102 -0.0323 0.6028 0.9652
2.000 0.3989 0.00485 0.00105 -0.0335 0.5857 0.9783
2.250 0.4347 0.00494 0.00110 -0.0353 0.5672 0.9874
2.500 0.4706 0.00506 0.00115 -0.0371 0.5475 0.9945
2.750 0.5080 0.00518 0.00120 -0.0393 0.5249 0.9998
3.000 0.5326 0.00533 0.00126 -0.0388 0.5030 1.0000
3.250 0.5574 0.00548 0.00136 -0.0382 0.4805 1.0000
3.500 0.5822 0.00571 0.00146 -0.0377 0.4486 1.0000
3.750 0.6060 0.00612 0.00161 -0.0371 0.3861 1.0000
4.000 0.6304 0.00653 0.00179 -0.0367 0.3332 1.0000
4.250 0.6557 0.00684 0.00197 -0.0364 0.2973 1.0000
4.500 0.6811 0.00718 0.00216 -0.0361 0.2617 1.0000
4.750 0.7064 0.00754 0.00238 -0.0358 0.2264 1.0000
5.000 0.7314 0.00795 0.00262 -0.0355 0.1879 1.0000
5.250 0.7555 0.00849 0.00294 -0.0351 0.1400 1.0000
5.500 0.7792 0.00910 0.00330 -0.0347 0.0926 1.0000
5.750 0.8016 0.00989 0.00380 -0.0341 0.0391 1.0000
6.000 0.8254 0.01051 0.00427 -0.0335 0.0181 1.0000
6.250 0.8506 0.01093 0.00474 -0.0331 0.0152 1.0000
6.500 0.8761 0.01127 0.00515 -0.0328 0.0147 1.0000
6.750 0.9012 0.01167 0.00560 -0.0324 0.0139 1.0000
7.000 0.9258 0.01211 0.00609 -0.0320 0.0129 1.0000
7.250 0.9499 0.01263 0.00666 -0.0315 0.0122 1.0000
7.500 0.9731 0.01326 0.00736 -0.0308 0.0115 1.0000
7.750 0.9944 0.01411 0.00832 -0.0299 0.0109 1.0000
8.000 1.0121 0.01539 0.00974 -0.0285 0.0103 1.0000
8.250 1.0335 0.01615 0.01058 -0.0276 0.0100 1.0000
8.500 1.0569 0.01661 0.01109 -0.0271 0.0096 1.0000
8.750 1.0786 0.01727 0.01182 -0.0264 0.0092 1.0000
9.000 1.0988 0.01811 0.01273 -0.0254 0.0088 1.0000
9.250 1.1185 0.01898 0.01368 -0.0244 0.0084 1.0000
9.500 1.1379 0.01982 0.01461 -0.0234 0.0079 1.0000
9.750 1.1566 0.02069 0.01554 -0.0224 0.0076 1.0000
10.000 1.1736 0.02168 0.01658 -0.0212 0.0072 1.0000
10.250 1.1736 0.02562 0.02078 -0.0182 0.0065 1.0000
10.500 1.1937 0.02565 0.02088 -0.0173 0.0064 1.0000
10.750 1.2108 0.02620 0.02152 -0.0161 0.0061 1.0000
11.000 1.2226 0.02733 0.02279 -0.0143 0.0059 1.0000
11.250 1.2282 0.02874 0.02433 -0.0116 0.0058 1.0000
11.500 1.2347 0.02978 0.02548 -0.0093 0.0054 1.0000
11.750 1.2386 0.03119 0.02701 -0.0070 0.0053 1.0000
12.000 1.2416 0.03272 0.02867 -0.0050 0.0051 1.0000
12.250 1.2457 0.03415 0.03020 -0.0035 0.0050 1.0000
12.500 1.2441 0.03634 0.03254 -0.0019 0.0049 1.0000
12.750 1.2482 0.03791 0.03418 -0.0011 0.0047 1.0000
13.000 1.2387 0.04134 0.03781 -0.0002 0.0047 1.0000
13.250 1.2403 0.04348 0.04002 -0.0001 0.0046 1.0000
13.500 1.2358 0.04663 0.04329 -0.0004 0.0045 1.0000
13.750 1.2198 0.05166 0.04854 -0.0013 0.0046 1.0000
14.000 1.2236 0.05402 0.05092 -0.0024 0.0044 1.0000
14.250 1.2071 0.05977 0.05687 -0.0046 0.0044 1.0000
14.500 1.1958 0.06504 0.06224 -0.0073 0.0043 1.0000
14.750 1.1768 0.07213 0.06952 -0.0110 0.0044 1.0000
15.000 1.1562 0.08001 0.07754 -0.0157 0.0042 1.0000
15.250 1.1436 0.08705 0.08473 -0.0200 0.0043 1.0000
15.500 1.1235 0.09613 0.09398 -0.0256 0.0044 1.0000
15.750 1.0881 0.10952 0.10760 -0.0337 0.0045 1.0000
16.000 1.0802 0.11651 0.11464 -0.0380 0.0044 1.0000
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Polar data table (+)
Polar graphs
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