S6063 7.05% (s6063-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.13 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6063-il-1000000-n5.txt Download as CSV file: xf-s6063-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5655 0.08455 0.08297 -0.0042 1.0000 0.0032
-8.500 -0.5703 0.07882 0.07727 -0.0072 1.0000 0.0036
-8.250 -0.5770 0.07390 0.07238 -0.0103 1.0000 0.0036
-8.000 -0.5836 0.06824 0.06675 -0.0162 1.0000 0.0035
-7.750 -0.5838 0.06060 0.05906 -0.0240 1.0000 0.0035
-7.500 -0.5800 0.05263 0.05096 -0.0296 1.0000 0.0035
-7.250 -0.5741 0.04410 0.04222 -0.0333 1.0000 0.0036
-7.000 -0.5662 0.03578 0.03358 -0.0349 1.0000 0.0037
-6.750 -0.5557 0.02869 0.02604 -0.0352 1.0000 0.0037
-6.500 -0.5390 0.02458 0.02153 -0.0349 1.0000 0.0037
-6.250 -0.5131 0.02237 0.01902 -0.0355 0.9939 0.0038
-6.000 -0.4832 0.02003 0.01630 -0.0368 0.9851 0.0040
-5.750 -0.4554 0.01726 0.01314 -0.0377 0.9751 0.0040
-5.500 -0.4270 0.01600 0.01166 -0.0381 0.9652 0.0040
-5.250 -0.4005 0.01478 0.01024 -0.0380 0.9545 0.0040
-5.000 -0.3754 0.01365 0.00890 -0.0374 0.9433 0.0039
-4.750 -0.3509 0.01248 0.00754 -0.0367 0.9315 0.0039
-4.500 -0.3265 0.01126 0.00614 -0.0360 0.9199 0.0040
-4.250 -0.3019 0.01014 0.00486 -0.0353 0.9082 0.0041
-4.000 -0.2768 0.00928 0.00386 -0.0347 0.8970 0.0043
-3.750 -0.2507 0.00878 0.00325 -0.0343 0.8860 0.0046
-3.500 -0.2242 0.00844 0.00284 -0.0340 0.8747 0.0050
-3.250 -0.1972 0.00815 0.00248 -0.0338 0.8631 0.0055
-3.000 -0.1702 0.00791 0.00217 -0.0335 0.8510 0.0060
-2.750 -0.1430 0.00771 0.00188 -0.0333 0.8379 0.0064
-2.500 -0.1158 0.00757 0.00168 -0.0331 0.8243 0.0070
-2.250 -0.0884 0.00743 0.00146 -0.0329 0.8103 0.0073
-2.000 -0.0609 0.00729 0.00121 -0.0327 0.7958 0.0080
-1.750 -0.0333 0.00719 0.00103 -0.0325 0.7804 0.0104
-1.500 -0.0060 0.00702 0.00088 -0.0324 0.7637 0.0340
-1.250 0.0210 0.00673 0.00076 -0.0323 0.7460 0.1013
-1.000 0.0476 0.00633 0.00066 -0.0323 0.7267 0.2085
-0.750 0.0741 0.00594 0.00060 -0.0323 0.7069 0.3301
-0.500 0.1004 0.00554 0.00055 -0.0323 0.6859 0.4684
-0.250 0.1274 0.00542 0.00053 -0.0322 0.6632 0.5302
0.000 0.1542 0.00529 0.00053 -0.0320 0.6384 0.6009
0.250 0.1810 0.00520 0.00054 -0.0318 0.6119 0.6636
0.500 0.2075 0.00514 0.00056 -0.0316 0.5849 0.7212
0.750 0.2337 0.00510 0.00060 -0.0312 0.5585 0.7777
1.000 0.2594 0.00507 0.00065 -0.0306 0.5317 0.8319
1.250 0.2844 0.00507 0.00071 -0.0299 0.5049 0.8774
1.500 0.3082 0.00524 0.00079 -0.0290 0.4513 0.9174
1.750 0.3337 0.00562 0.00088 -0.0285 0.3635 0.9559
2.000 0.3685 0.00597 0.00098 -0.0303 0.2984 0.9856
2.250 0.4000 0.00637 0.00111 -0.0314 0.2311 1.0000
2.500 0.4253 0.00688 0.00129 -0.0311 0.1543 1.0000
3.000 0.4758 0.00802 0.00182 -0.0306 0.0121 1.0000
3.250 0.5028 0.00820 0.00198 -0.0305 0.0106 1.0000
3.500 0.5299 0.00838 0.00217 -0.0303 0.0095 1.0000
3.750 0.5569 0.00858 0.00240 -0.0302 0.0085 1.0000
4.000 0.5838 0.00885 0.00272 -0.0299 0.0075 1.0000
4.250 0.6104 0.00917 0.00309 -0.0297 0.0072 1.0000
4.500 0.6369 0.00949 0.00346 -0.0295 0.0071 1.0000
4.750 0.6634 0.00983 0.00383 -0.0293 0.0070 1.0000
5.000 0.6898 0.01015 0.00418 -0.0291 0.0068 1.0000
5.250 0.7160 0.01051 0.00458 -0.0288 0.0065 1.0000
5.500 0.7418 0.01095 0.00507 -0.0285 0.0064 1.0000
5.750 0.7674 0.01144 0.00564 -0.0282 0.0062 1.0000
6.000 0.7927 0.01196 0.00622 -0.0278 0.0060 1.0000
6.250 0.8177 0.01253 0.00685 -0.0274 0.0058 1.0000
6.500 0.8424 0.01315 0.00754 -0.0270 0.0056 1.0000
6.750 0.8669 0.01378 0.00823 -0.0266 0.0053 1.0000
7.000 0.8910 0.01450 0.00903 -0.0261 0.0051 1.0000
7.250 0.9149 0.01521 0.00981 -0.0256 0.0049 1.0000
7.500 0.9385 0.01599 0.01069 -0.0251 0.0047 1.0000
7.750 0.9614 0.01690 0.01168 -0.0245 0.0046 1.0000
8.000 0.9837 0.01792 0.01280 -0.0238 0.0045 1.0000
8.250 1.0048 0.01920 0.01420 -0.0231 0.0043 1.0000
8.500 1.0251 0.02067 0.01583 -0.0222 0.0043 1.0000
8.750 1.0441 0.02239 0.01774 -0.0213 0.0042 1.0000
9.000 1.0606 0.02457 0.02015 -0.0201 0.0042 1.0000
9.250 1.0661 0.02904 0.02505 -0.0181 0.0040 1.0000
9.500 1.0812 0.03071 0.02695 -0.0171 0.0040 1.0000
9.750 1.0938 0.03262 0.02909 -0.0158 0.0039 1.0000
10.000 1.1033 0.03477 0.03146 -0.0144 0.0039 1.0000
10.250 1.1077 0.03732 0.03425 -0.0127 0.0039 1.0000
10.500 1.1060 0.04019 0.03736 -0.0108 0.0039 1.0000
10.750 1.0945 0.04292 0.04028 -0.0077 0.0039 1.0000
11.000 1.0821 0.04562 0.04315 -0.0057 0.0038 1.0000
11.250 1.0675 0.04919 0.04689 -0.0054 0.0038 1.0000
11.500 1.0501 0.05398 0.05184 -0.0072 0.0038 1.0000
11.750 1.0334 0.05994 0.05795 -0.0111 0.0038 1.0000
12.000 1.0027 0.07049 0.06867 -0.0193 0.0039 1.0000
12.250 0.9784 0.08222 0.08054 -0.0282 0.0039 1.0000
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Polar data table (+)
Polar graphs
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