S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 200,000 Max Cl/Cd: 42.95 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9033-il-200000-n5.txt Download as CSV file: xf-s9033-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9033 (7.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.9095 0.06715 0.06356 -0.0042 1.0000 0.0181
-11.250 -0.9551 0.05388 0.05003 -0.0167 1.0000 0.0171
-11.000 -0.9783 0.04870 0.04461 -0.0192 1.0000 0.0171
-10.750 -0.9930 0.04487 0.04051 -0.0186 1.0000 0.0173
-10.500 -0.9953 0.04164 0.03697 -0.0181 1.0000 0.0180
-10.250 -0.9931 0.03842 0.03339 -0.0173 1.0000 0.0186
-10.000 -0.9858 0.03551 0.03008 -0.0165 1.0000 0.0192
-9.750 -0.9742 0.03299 0.02716 -0.0156 1.0000 0.0197
-9.500 -0.9611 0.03045 0.02425 -0.0147 1.0000 0.0204
-9.250 -0.9450 0.02852 0.02214 -0.0140 1.0000 0.0215
-9.000 -0.9253 0.02732 0.02082 -0.0134 1.0000 0.0226
-8.750 -0.9053 0.02590 0.01920 -0.0126 1.0000 0.0235
-8.500 -0.8846 0.02446 0.01756 -0.0119 1.0000 0.0244
-8.250 -0.8632 0.02312 0.01601 -0.0111 1.0000 0.0253
-8.000 -0.8411 0.02191 0.01461 -0.0104 1.0000 0.0264
-7.750 -0.8180 0.02098 0.01345 -0.0097 1.0000 0.0277
-7.500 -0.7964 0.01969 0.01209 -0.0090 1.0000 0.0295
-7.250 -0.7732 0.01880 0.01113 -0.0084 1.0000 0.0313
-7.000 -0.7495 0.01799 0.01022 -0.0078 1.0000 0.0334
-6.750 -0.7255 0.01723 0.00935 -0.0071 1.0000 0.0359
-6.500 -0.7016 0.01645 0.00847 -0.0065 1.0000 0.0390
-6.250 -0.6773 0.01577 0.00775 -0.0059 1.0000 0.0436
-6.000 -0.6522 0.01528 0.00716 -0.0054 1.0000 0.0492
-5.750 -0.6276 0.01468 0.00658 -0.0049 1.0000 0.0570
-5.500 -0.6026 0.01418 0.00606 -0.0043 1.0000 0.0646
-5.250 -0.5772 0.01376 0.00560 -0.0038 1.0000 0.0736
-5.000 -0.5521 0.01332 0.00517 -0.0034 1.0000 0.0848
-4.750 -0.5268 0.01290 0.00479 -0.0029 1.0000 0.0979
-4.500 -0.5016 0.01250 0.00443 -0.0024 1.0000 0.1127
-4.250 -0.4763 0.01212 0.00410 -0.0019 1.0000 0.1295
-4.000 -0.4510 0.01175 0.00379 -0.0013 1.0000 0.1474
-3.750 -0.4257 0.01143 0.00350 -0.0008 1.0000 0.1665
-3.500 -0.4005 0.01110 0.00326 -0.0003 1.0000 0.1895
-3.250 -0.3754 0.01077 0.00304 0.0003 1.0000 0.2166
-3.000 -0.3503 0.01047 0.00284 0.0009 1.0000 0.2449
-2.750 -0.3255 0.01017 0.00266 0.0015 1.0000 0.2774
-2.500 -0.3009 0.00986 0.00251 0.0021 1.0000 0.3155
-2.250 -0.2765 0.00955 0.00239 0.0028 1.0000 0.3588
-2.000 -0.2523 0.00926 0.00229 0.0036 1.0000 0.4044
-1.750 -0.2282 0.00899 0.00220 0.0044 1.0000 0.4486
-1.500 -0.2044 0.00874 0.00215 0.0052 1.0000 0.4949
-1.250 -0.1809 0.00848 0.00212 0.0062 1.0000 0.5450
-1.000 -0.1508 0.00822 0.00212 0.0058 0.9934 0.6043
-0.750 -0.1142 0.00796 0.00215 0.0042 0.9749 0.6709
-0.500 -0.0787 0.00773 0.00217 0.0030 0.9492 0.7327
-0.250 -0.0395 0.00755 0.00219 0.0014 0.9109 0.7951
0.000 0.0000 0.00747 0.00220 0.0000 0.8572 0.8573
0.250 0.0395 0.00755 0.00219 -0.0014 0.7950 0.9109
0.500 0.0786 0.00773 0.00217 -0.0030 0.7328 0.9490
0.750 0.1142 0.00796 0.00215 -0.0042 0.6710 0.9749
1.000 0.1507 0.00823 0.00212 -0.0058 0.6040 0.9933
1.250 0.1810 0.00848 0.00212 -0.0062 0.5450 1.0000
1.500 0.2044 0.00874 0.00215 -0.0052 0.4950 1.0000
1.750 0.2283 0.00899 0.00220 -0.0044 0.4486 1.0000
2.000 0.2524 0.00926 0.00229 -0.0036 0.4041 1.0000
2.250 0.2766 0.00955 0.00239 -0.0028 0.3585 1.0000
2.500 0.3010 0.00986 0.00251 -0.0021 0.3154 1.0000
2.750 0.3256 0.01017 0.00266 -0.0015 0.2772 1.0000
3.000 0.3504 0.01047 0.00284 -0.0009 0.2448 1.0000
3.250 0.3755 0.01077 0.00304 -0.0003 0.2163 1.0000
3.500 0.4005 0.01110 0.00326 0.0003 0.1895 1.0000
3.750 0.4257 0.01143 0.00350 0.0008 0.1665 1.0000
4.000 0.4511 0.01175 0.00380 0.0013 0.1474 1.0000
4.250 0.4763 0.01212 0.00410 0.0018 0.1294 1.0000
4.500 0.5016 0.01250 0.00443 0.0024 0.1126 1.0000
4.750 0.5269 0.01290 0.00479 0.0029 0.0978 1.0000
5.000 0.5521 0.01332 0.00517 0.0033 0.0848 1.0000
5.250 0.5772 0.01376 0.00560 0.0038 0.0737 1.0000
5.500 0.6025 0.01418 0.00606 0.0043 0.0646 1.0000
5.750 0.6276 0.01468 0.00658 0.0049 0.0571 1.0000
6.000 0.6521 0.01528 0.00716 0.0054 0.0492 1.0000
6.250 0.6773 0.01577 0.00774 0.0059 0.0436 1.0000
6.500 0.7015 0.01645 0.00847 0.0065 0.0390 1.0000
6.750 0.7254 0.01724 0.00935 0.0071 0.0360 1.0000
7.000 0.7494 0.01799 0.01022 0.0078 0.0334 1.0000
7.250 0.7731 0.01880 0.01112 0.0084 0.0313 1.0000
7.500 0.7963 0.01968 0.01208 0.0090 0.0295 1.0000
7.750 0.8178 0.02097 0.01344 0.0098 0.0277 1.0000
8.000 0.8410 0.02191 0.01460 0.0104 0.0264 1.0000
8.250 0.8630 0.02312 0.01600 0.0112 0.0253 1.0000
8.500 0.8844 0.02445 0.01755 0.0119 0.0244 1.0000
8.750 0.9050 0.02589 0.01919 0.0127 0.0235 1.0000
9.000 0.9250 0.02731 0.02081 0.0134 0.0226 1.0000
9.250 0.9447 0.02854 0.02217 0.0140 0.0216 1.0000
9.500 0.9609 0.03045 0.02425 0.0148 0.0204 1.0000
9.750 0.9739 0.03298 0.02716 0.0156 0.0197 1.0000
10.000 0.9854 0.03552 0.03009 0.0165 0.0193 1.0000
10.250 0.9927 0.03842 0.03338 0.0174 0.0186 1.0000
10.500 0.9959 0.04147 0.03679 0.0181 0.0179 1.0000
10.750 0.9934 0.04476 0.04040 0.0186 0.0173 1.0000
11.000 0.9801 0.04844 0.04435 0.0192 0.0170 1.0000
11.250 0.9548 0.05391 0.05005 0.0167 0.0172 1.0000
11.500 0.9114 0.06674 0.06315 0.0045 0.0181 1.0000
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Polar data table (+)
Polar graphs
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