S6063 7.05% (s6063-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 50,000 Max Cl/Cd: 34.67 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6063-il-50000-n5.txt Download as CSV file: xf-s6063-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5418 0.10089 0.09403 -0.0033 1.0000 0.0549
-8.500 -0.5418 0.09595 0.08913 -0.0069 1.0000 0.0481
-8.250 -0.5386 0.09187 0.08510 -0.0084 1.0000 0.0463
-8.000 -0.5377 0.08765 0.08096 -0.0108 1.0000 0.0448
-7.750 -0.5384 0.08307 0.07645 -0.0142 1.0000 0.0434
-7.500 -0.5365 0.07783 0.07125 -0.0188 1.0000 0.0418
-7.250 -0.5347 0.07165 0.06504 -0.0242 1.0000 0.0399
-6.750 -0.5222 0.06025 0.05312 -0.0320 1.0000 0.0365
-6.500 -0.5122 0.05585 0.04855 -0.0332 1.0000 0.0361
-6.250 -0.5002 0.05153 0.04398 -0.0342 1.0000 0.0356
-6.000 -0.4861 0.04732 0.03944 -0.0350 1.0000 0.0353
-5.750 -0.4697 0.04333 0.03497 -0.0354 1.0000 0.0350
-5.500 -0.4513 0.03965 0.03084 -0.0354 1.0000 0.0349
-5.250 -0.4310 0.03625 0.02693 -0.0351 1.0000 0.0349
-5.000 -0.4092 0.03324 0.02342 -0.0346 1.0000 0.0352
-4.750 -0.3862 0.03062 0.02031 -0.0338 1.0000 0.0358
-4.500 -0.3630 0.02832 0.01763 -0.0329 1.0000 0.0377
-4.250 -0.3410 0.02649 0.01568 -0.0321 1.0000 0.0419
-4.000 -0.3176 0.02488 0.01382 -0.0310 1.0000 0.0458
-3.750 -0.2944 0.02338 0.01198 -0.0296 1.0000 0.0491
-3.500 -0.2719 0.02195 0.01045 -0.0284 1.0000 0.0546
-3.250 -0.2485 0.02064 0.00904 -0.0275 1.0000 0.0678
-3.000 -0.2264 0.01885 0.00785 -0.0270 1.0000 0.1504
-2.750 -0.2106 0.01660 0.00729 -0.0257 1.0000 0.4407
-2.500 -0.2002 0.01547 0.00716 -0.0208 1.0000 0.6802
-2.250 -0.1617 0.01494 0.00674 -0.0200 1.0000 0.9081
-2.000 -0.1075 0.01471 0.00597 -0.0253 1.0000 1.0000
-1.750 -0.0908 0.01467 0.00562 -0.0238 1.0000 1.0000
-1.500 -0.0730 0.01468 0.00534 -0.0225 1.0000 1.0000
-1.250 -0.0544 0.01472 0.00509 -0.0213 1.0000 1.0000
-1.000 -0.0353 0.01479 0.00494 -0.0202 1.0000 1.0000
-0.750 -0.0157 0.01489 0.00484 -0.0192 1.0000 1.0000
-0.500 0.0040 0.01502 0.00480 -0.0183 1.0000 1.0000
-0.250 0.0238 0.01518 0.00481 -0.0175 1.0000 1.0000
0.000 0.0438 0.01538 0.00486 -0.0167 1.0000 1.0000
0.250 0.0685 0.01562 0.00500 -0.0170 0.9971 1.0000
0.500 0.1131 0.01598 0.00527 -0.0210 0.9834 1.0000
0.750 0.1570 0.01629 0.00554 -0.0248 0.9688 1.0000
1.000 0.2006 0.01657 0.00581 -0.0283 0.9536 1.0000
1.250 0.2445 0.01682 0.00609 -0.0318 0.9379 1.0000
1.500 0.2880 0.01702 0.00637 -0.0349 0.9216 1.0000
1.750 0.3294 0.01718 0.00664 -0.0375 0.9041 1.0000
2.000 0.3665 0.01730 0.00688 -0.0390 0.8845 1.0000
2.250 0.4011 0.01740 0.00711 -0.0398 0.8632 1.0000
2.500 0.4328 0.01749 0.00737 -0.0400 0.8402 1.0000
2.750 0.4635 0.01755 0.00756 -0.0397 0.8164 1.0000
3.000 0.4916 0.01761 0.00776 -0.0388 0.7901 1.0000
3.250 0.5177 0.01768 0.00796 -0.0376 0.7611 1.0000
3.500 0.5426 0.01778 0.00825 -0.0361 0.7287 1.0000
3.750 0.5673 0.01788 0.00846 -0.0344 0.6941 1.0000
4.000 0.5911 0.01804 0.00872 -0.0326 0.6551 1.0000
4.250 0.6144 0.01825 0.00899 -0.0307 0.6121 1.0000
4.500 0.6368 0.01856 0.00940 -0.0287 0.5637 1.0000
4.750 0.6584 0.01899 0.00982 -0.0268 0.5087 1.0000
5.000 0.6782 0.01958 0.01029 -0.0247 0.4355 1.0000
5.250 0.6903 0.02093 0.01064 -0.0222 0.2767 1.0000
5.500 0.7041 0.02333 0.01181 -0.0213 0.1098 1.0000
5.750 0.7228 0.02553 0.01369 -0.0203 0.0655 1.0000
6.000 0.7428 0.02731 0.01556 -0.0192 0.0545 1.0000
6.250 0.7622 0.02914 0.01751 -0.0181 0.0493 1.0000
6.500 0.7841 0.03089 0.01957 -0.0167 0.0461 1.0000
6.750 0.8067 0.03279 0.02174 -0.0156 0.0430 1.0000
7.000 0.8282 0.03478 0.02389 -0.0147 0.0394 1.0000
7.250 0.8488 0.03738 0.02662 -0.0140 0.0368 1.0000
7.500 0.8704 0.04000 0.02972 -0.0130 0.0355 1.0000
7.750 0.8894 0.04313 0.03334 -0.0120 0.0350 1.0000
8.000 0.9048 0.04664 0.03735 -0.0110 0.0346 1.0000
8.250 0.9162 0.05046 0.04168 -0.0100 0.0344 1.0000
8.500 0.9232 0.05451 0.04622 -0.0090 0.0344 1.0000
8.750 0.9255 0.05878 0.05091 -0.0083 0.0344 1.0000
9.000 0.9230 0.06319 0.05568 -0.0077 0.0346 1.0000
9.250 0.9158 0.06764 0.06043 -0.0075 0.0347 1.0000
9.500 0.9036 0.07206 0.06506 -0.0076 0.0349 1.0000
9.750 0.8874 0.07662 0.06976 -0.0085 0.0351 1.0000
10.000 0.8709 0.08193 0.07517 -0.0112 0.0354 1.0000
10.250 0.8555 0.08815 0.08145 -0.0155 0.0357 1.0000
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Polar data table (+)
Polar graphs
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