S4053 (s4053-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.98 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4053-il-1000000.txt Download as CSV file: xf-s4053-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S4053
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3079 0.08238 0.08086 -0.0340 1.0000 0.0098
-9.000 -0.3094 0.07871 0.07720 -0.0344 1.0000 0.0099
-8.750 -0.3120 0.07499 0.07350 -0.0348 1.0000 0.0100
-8.500 -0.3158 0.07129 0.06982 -0.0352 1.0000 0.0103
-8.250 -0.3211 0.06762 0.06617 -0.0353 1.0000 0.0104
-8.000 -0.3286 0.06411 0.06270 -0.0352 1.0000 0.0105
-6.000 -0.2718 0.02380 0.02067 -0.0817 0.9578 0.0132
-5.750 -0.2459 0.02234 0.01909 -0.0823 0.9455 0.0137
-5.500 -0.2192 0.02091 0.01747 -0.0828 0.9311 0.0146
-5.250 -0.1941 0.01943 0.01572 -0.0824 0.9135 0.0159
-5.000 -0.1699 0.00722 0.00340 -0.0762 0.8577 0.0172
-4.500 -0.1262 0.01258 0.00756 -0.0785 0.8618 0.0128
-4.250 -0.1005 0.01202 0.00684 -0.0779 0.8476 0.0126
-4.000 -0.0769 0.01052 0.00516 -0.0769 0.8344 0.0129
-3.750 -0.0523 0.00974 0.00428 -0.0762 0.8220 0.0133
-3.500 -0.0269 0.00927 0.00372 -0.0757 0.8104 0.0138
-3.250 -0.0012 0.00890 0.00327 -0.0752 0.7994 0.0142
-3.000 0.0248 0.00856 0.00285 -0.0747 0.7888 0.0146
-2.750 0.0512 0.00830 0.00253 -0.0744 0.7790 0.0153
-2.500 0.0777 0.00806 0.00221 -0.0740 0.7698 0.0161
-2.250 0.1044 0.00784 0.00191 -0.0736 0.7607 0.0168
-2.000 0.1313 0.00762 0.00162 -0.0733 0.7521 0.0179
-1.500 0.1852 0.00726 0.00119 -0.0728 0.7356 0.0349
-1.250 0.2096 0.00662 0.00107 -0.0724 0.7278 0.2037
-1.000 0.2343 0.00608 0.00102 -0.0720 0.7196 0.3706
-0.750 0.2591 0.00568 0.00100 -0.0716 0.7120 0.5091
-0.500 0.2839 0.00536 0.00100 -0.0710 0.7037 0.6280
-0.250 0.3066 0.00498 0.00103 -0.0699 0.6957 0.7689
0.000 0.3277 0.00463 0.00109 -0.0679 0.6877 0.9165
0.250 0.3709 0.00466 0.00112 -0.0711 0.6798 0.9722
0.750 0.4636 0.00477 0.00111 -0.0793 0.6620 0.9976
1.000 0.4977 0.00481 0.00110 -0.0807 0.6528 1.0000
1.250 0.5223 0.00488 0.00110 -0.0800 0.6432 1.0000
1.500 0.5473 0.00493 0.00112 -0.0794 0.6332 1.0000
1.750 0.5723 0.00499 0.00115 -0.0787 0.6235 1.0000
2.000 0.5970 0.00507 0.00118 -0.0780 0.6131 1.0000
2.250 0.6220 0.00515 0.00122 -0.0774 0.6010 1.0000
2.500 0.6468 0.00524 0.00127 -0.0767 0.5871 1.0000
2.750 0.6713 0.00535 0.00132 -0.0760 0.5715 1.0000
3.000 0.6959 0.00546 0.00138 -0.0753 0.5534 1.0000
3.250 0.7204 0.00560 0.00146 -0.0746 0.5341 1.0000
3.500 0.7442 0.00577 0.00156 -0.0738 0.5108 1.0000
3.750 0.7678 0.00598 0.00166 -0.0729 0.4839 1.0000
4.000 0.7910 0.00623 0.00180 -0.0720 0.4533 1.0000
4.250 0.8129 0.00658 0.00197 -0.0709 0.4107 1.0000
4.500 0.8352 0.00694 0.00216 -0.0699 0.3716 1.0000
4.750 0.8578 0.00729 0.00237 -0.0690 0.3352 1.0000
5.000 0.8800 0.00768 0.00260 -0.0680 0.2978 1.0000
5.250 0.9017 0.00813 0.00287 -0.0670 0.2570 1.0000
5.500 0.9241 0.00853 0.00313 -0.0661 0.2229 1.0000
5.750 0.9463 0.00896 0.00341 -0.0652 0.1914 1.0000
6.000 0.9685 0.00939 0.00371 -0.0643 0.1623 1.0000
6.250 0.9904 0.00984 0.00403 -0.0633 0.1345 1.0000
6.500 1.0126 0.01027 0.00436 -0.0624 0.1110 1.0000
6.750 1.0347 0.01071 0.00471 -0.0615 0.0910 1.0000
7.000 1.0565 0.01116 0.00507 -0.0606 0.0734 1.0000
7.250 1.0785 0.01159 0.00543 -0.0597 0.0605 1.0000
7.500 1.1010 0.01198 0.00579 -0.0589 0.0513 1.0000
7.750 1.1232 0.01238 0.00619 -0.0580 0.0443 1.0000
8.000 1.1455 0.01276 0.00656 -0.0572 0.0395 1.0000
8.250 1.1673 0.01319 0.00699 -0.0563 0.0346 1.0000
8.500 1.1898 0.01352 0.00734 -0.0555 0.0315 1.0000
8.750 1.2098 0.01406 0.00786 -0.0543 0.0263 1.0000
9.000 1.2324 0.01436 0.00821 -0.0536 0.0239 1.0000
9.250 1.2516 0.01493 0.00875 -0.0523 0.0189 1.0000
9.500 1.2709 0.01546 0.00927 -0.0511 0.0148 1.0000
9.750 1.2894 0.01605 0.00988 -0.0497 0.0122 1.0000
10.000 1.3059 0.01675 0.01060 -0.0480 0.0102 1.0000
10.250 1.3224 0.01742 0.01134 -0.0463 0.0092 1.0000
10.500 1.3389 0.01802 0.01200 -0.0446 0.0085 1.0000
10.750 1.3525 0.01866 0.01271 -0.0424 0.0078 1.0000
11.000 1.3623 0.01948 0.01360 -0.0397 0.0072 1.0000
11.250 1.3653 0.02075 0.01499 -0.0360 0.0066 1.0000
11.500 1.3774 0.02145 0.01577 -0.0339 0.0064 1.0000
11.750 1.3879 0.02228 0.01668 -0.0317 0.0062 1.0000
12.000 1.3958 0.02330 0.01780 -0.0293 0.0060 1.0000
12.250 1.4050 0.02427 0.01885 -0.0272 0.0057 1.0000
12.500 1.4129 0.02537 0.02003 -0.0251 0.0054 1.0000
12.750 1.4175 0.02675 0.02152 -0.0229 0.0054 1.0000
13.000 1.4232 0.02812 0.02297 -0.0211 0.0051 1.0000
13.250 1.4256 0.02982 0.02479 -0.0192 0.0050 1.0000
13.500 1.4234 0.03201 0.02709 -0.0174 0.0047 1.0000
13.750 1.4139 0.03504 0.03028 -0.0155 0.0045 1.0000
14.000 1.4033 0.03839 0.03380 -0.0141 0.0044 1.0000
14.250 1.4025 0.04095 0.03650 -0.0133 0.0043 1.0000
14.500 1.4095 0.04275 0.03839 -0.0130 0.0042 1.0000
14.750 1.4060 0.04581 0.04157 -0.0128 0.0042 1.0000
15.000 1.3986 0.04946 0.04536 -0.0128 0.0042 1.0000
15.250 1.3971 0.05256 0.04858 -0.0131 0.0041 1.0000
15.500 1.3890 0.05669 0.05286 -0.0139 0.0040 1.0000
15.750 1.3780 0.06147 0.05779 -0.0151 0.0040 1.0000
16.000 1.3720 0.06577 0.06221 -0.0165 0.0039 1.0000
16.250 1.3619 0.07093 0.06750 -0.0185 0.0039 1.0000
16.500 1.3496 0.07674 0.07346 -0.0209 0.0039 1.0000
16.750 1.3338 0.08349 0.08036 -0.0241 0.0038 1.0000
17.000 1.3170 0.09074 0.08777 -0.0277 0.0039 1.0000
17.250 1.3033 0.09774 0.09489 -0.0314 0.0038 1.0000
17.500 1.2873 0.10546 0.10276 -0.0356 0.0038 1.0000
17.750 1.2654 0.11467 0.11212 -0.0407 0.0038 1.0000
18.000 1.2464 0.12348 0.12107 -0.0457 0.0039 1.0000
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Polar data table (+)
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