S6063 7.05% (s6063-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 100,000 Max Cl/Cd: 48.6 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6063-il-100000.txt Download as CSV file: xf-s6063-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5449 0.10606 0.10120 0.0006 1.0000 0.0855
-8.750 -0.5598 0.10357 0.09884 -0.0064 1.0000 0.0871
-8.500 -0.5731 0.10038 0.09575 -0.0133 1.0000 0.0874
-8.250 -0.5350 0.09449 0.08975 -0.0036 1.0000 0.0922
-8.000 -0.5320 0.09110 0.08641 -0.0051 1.0000 0.0958
-7.750 -0.5426 0.08773 0.08315 -0.0107 1.0000 0.0995
-7.500 -0.5544 0.08239 0.07780 -0.0229 1.0000 0.1014
-7.250 -0.5330 0.07918 0.07464 -0.0145 1.0000 0.1049
-7.000 -0.5263 0.07539 0.07085 -0.0171 1.0000 0.1102
-6.750 -0.5264 0.06989 0.06528 -0.0250 1.0000 0.1163
-6.500 -0.5125 0.06690 0.06234 -0.0229 1.0000 0.1213
-6.250 -0.5059 0.06210 0.05740 -0.0281 1.0000 0.1305
-6.000 -0.4918 0.05892 0.05422 -0.0279 1.0000 0.1381
-5.750 -0.4797 0.05503 0.05026 -0.0292 1.0000 0.1473
-5.500 -0.4661 0.05154 0.04668 -0.0302 1.0000 0.1606
-5.250 -0.4514 0.04866 0.04375 -0.0300 1.0000 0.1774
-5.000 -0.4127 0.03389 0.02681 -0.0358 1.0000 0.0598
-4.750 -0.3925 0.03046 0.02305 -0.0351 1.0000 0.0585
-4.500 -0.3709 0.02745 0.01963 -0.0341 1.0000 0.0568
-4.250 -0.3477 0.02456 0.01625 -0.0328 1.0000 0.0537
-4.000 -0.3236 0.02219 0.01340 -0.0314 1.0000 0.0521
-3.750 -0.2997 0.02032 0.01127 -0.0301 1.0000 0.0524
-3.500 -0.2765 0.01878 0.00962 -0.0288 1.0000 0.0542
-3.250 -0.2538 0.01748 0.00825 -0.0275 1.0000 0.0577
-3.000 -0.2322 0.01624 0.00705 -0.0262 1.0000 0.0657
-2.750 -0.2105 0.01503 0.00595 -0.0249 1.0000 0.0910
-2.500 -0.1954 0.01181 0.00508 -0.0232 1.0000 0.5252
-2.250 -0.1847 0.01083 0.00532 -0.0167 1.0000 0.8794
-2.000 -0.1137 0.01068 0.00472 -0.0246 1.0000 1.0000
-1.750 -0.0986 0.01068 0.00448 -0.0229 1.0000 1.0000
-1.500 -0.0812 0.01073 0.00430 -0.0215 1.0000 1.0000
-1.250 -0.0625 0.01081 0.00418 -0.0203 1.0000 1.0000
-1.000 -0.0431 0.01092 0.00408 -0.0193 1.0000 1.0000
-0.750 -0.0233 0.01106 0.00407 -0.0184 1.0000 1.0000
-0.500 -0.0034 0.01123 0.00411 -0.0176 1.0000 1.0000
-0.250 0.0166 0.01143 0.00420 -0.0169 1.0000 1.0000
0.000 0.0365 0.01168 0.00434 -0.0162 1.0000 1.0000
0.250 0.0562 0.01196 0.00454 -0.0156 1.0000 1.0000
0.500 0.0925 0.01236 0.00488 -0.0183 0.9940 1.0000
0.750 0.1458 0.01278 0.00527 -0.0241 0.9809 1.0000
1.000 0.1988 0.01310 0.00560 -0.0295 0.9670 1.0000
1.250 0.2514 0.01331 0.00585 -0.0347 0.9525 1.0000
1.500 0.3050 0.01340 0.00603 -0.0398 0.9376 1.0000
1.750 0.3563 0.01337 0.00612 -0.0441 0.9218 1.0000
2.000 0.4021 0.01328 0.00614 -0.0470 0.9044 1.0000
2.250 0.4390 0.01318 0.00614 -0.0478 0.8843 1.0000
2.500 0.4695 0.01306 0.00616 -0.0472 0.8618 1.0000
2.750 0.4950 0.01299 0.00616 -0.0455 0.8368 1.0000
3.000 0.5189 0.01291 0.00615 -0.0435 0.8103 1.0000
3.250 0.5419 0.01286 0.00614 -0.0412 0.7813 1.0000
3.500 0.5646 0.01282 0.00618 -0.0389 0.7496 1.0000
3.750 0.5871 0.01285 0.00624 -0.0368 0.7126 1.0000
4.000 0.6097 0.01293 0.00633 -0.0347 0.6718 1.0000
4.250 0.6304 0.01304 0.00629 -0.0321 0.6113 1.0000
4.500 0.6493 0.01336 0.00626 -0.0294 0.5234 1.0000
4.750 0.6684 0.01400 0.00653 -0.0274 0.4197 1.0000
5.000 0.6853 0.01527 0.00704 -0.0257 0.2630 1.0000
5.250 0.6961 0.01868 0.00901 -0.0235 0.0747 1.0000
5.500 0.7162 0.02027 0.01051 -0.0223 0.0598 1.0000
5.750 0.7382 0.02170 0.01204 -0.0210 0.0543 1.0000
6.000 0.7612 0.02335 0.01375 -0.0199 0.0509 1.0000
6.250 0.7854 0.02534 0.01575 -0.0190 0.0490 1.0000
6.500 0.8109 0.02789 0.01841 -0.0182 0.0481 1.0000
6.750 0.8363 0.03054 0.02133 -0.0174 0.0481 1.0000
7.000 0.8607 0.03314 0.02441 -0.0162 0.0491 1.0000
7.250 0.8815 0.03651 0.02842 -0.0147 0.0504 1.0000
7.500 0.8985 0.04018 0.03270 -0.0133 0.0510 1.0000
7.750 0.9110 0.04460 0.03775 -0.0118 0.0525 1.0000
8.000 0.9205 0.04982 0.04343 -0.0107 0.0562 1.0000
8.250 0.8659 0.04638 0.04125 -0.0064 0.0662 1.0000
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Polar data table (+)
Polar graphs
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