S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 500,000 Max Cl/Cd: 56.88 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9033-il-500000.txt Download as CSV file: xf-s9033-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -1.0921 0.04558 0.04252 -0.0216 1.0000 0.0108
-12.250 -1.1056 0.04163 0.03840 -0.0233 1.0000 0.0108
-12.000 -1.1076 0.03981 0.03651 -0.0225 1.0000 0.0112
-11.750 -1.1064 0.03830 0.03491 -0.0209 1.0000 0.0115
-11.500 -1.0995 0.03668 0.03314 -0.0200 1.0000 0.0121
-11.250 -1.0884 0.03534 0.03166 -0.0192 1.0000 0.0128
-11.000 -1.0723 0.03451 0.03069 -0.0185 1.0000 0.0136
-10.750 -1.0529 0.03413 0.03018 -0.0179 1.0000 0.0142
-10.500 -1.0610 0.02866 0.02422 -0.0162 1.0000 0.0152
-10.250 -1.0413 0.02795 0.02349 -0.0157 1.0000 0.0161
-10.000 -1.0212 0.02717 0.02262 -0.0151 1.0000 0.0169
-9.750 -1.0001 0.02644 0.02179 -0.0145 1.0000 0.0180
-9.500 -0.9792 0.02551 0.02071 -0.0138 1.0000 0.0190
-9.250 -0.9567 0.02489 0.01992 -0.0133 1.0000 0.0197
-9.000 -0.9398 0.02260 0.01732 -0.0123 1.0000 0.0206
-8.750 -0.9222 0.02035 0.01486 -0.0113 1.0000 0.0219
-8.500 -0.8998 0.01934 0.01375 -0.0107 1.0000 0.0228
-8.250 -0.8768 0.01841 0.01272 -0.0100 1.0000 0.0237
-8.000 -0.8531 0.01763 0.01184 -0.0094 1.0000 0.0248
-7.750 -0.8291 0.01687 0.01098 -0.0088 1.0000 0.0259
-7.500 -0.8052 0.01603 0.01000 -0.0081 1.0000 0.0267
-7.250 -0.7809 0.01530 0.00917 -0.0075 1.0000 0.0274
-7.000 -0.7566 0.01457 0.00834 -0.0068 1.0000 0.0281
-6.750 -0.7348 0.01325 0.00692 -0.0059 1.0000 0.0305
-6.500 -0.7098 0.01272 0.00637 -0.0053 1.0000 0.0333
-6.250 -0.6843 0.01231 0.00589 -0.0048 1.0000 0.0364
-6.000 -0.6599 0.01160 0.00515 -0.0041 1.0000 0.0418
-5.750 -0.6341 0.01124 0.00477 -0.0036 1.0000 0.0484
-5.500 -0.6091 0.01073 0.00429 -0.0031 1.0000 0.0581
-5.250 -0.5835 0.01036 0.00392 -0.0026 1.0000 0.0664
-5.000 -0.5576 0.01009 0.00364 -0.0021 1.0000 0.0743
-4.750 -0.5322 0.00973 0.00333 -0.0016 1.0000 0.0857
-4.500 -0.5066 0.00942 0.00306 -0.0010 1.0000 0.0992
-4.250 -0.4812 0.00910 0.00282 -0.0005 1.0000 0.1161
-4.000 -0.4560 0.00878 0.00261 0.0001 1.0000 0.1386
-3.750 -0.4308 0.00847 0.00240 0.0006 1.0000 0.1632
-3.500 -0.4056 0.00819 0.00222 0.0012 1.0000 0.1894
-3.250 -0.3805 0.00792 0.00206 0.0018 1.0000 0.2168
-3.000 -0.3555 0.00766 0.00191 0.0024 1.0000 0.2462
-2.750 -0.3304 0.00741 0.00178 0.0031 1.0000 0.2786
-2.500 -0.3055 0.00716 0.00167 0.0037 1.0000 0.3148
-2.250 -0.2809 0.00690 0.00158 0.0044 1.0000 0.3576
-2.000 -0.2563 0.00664 0.00151 0.0051 1.0000 0.4033
-1.750 -0.2320 0.00640 0.00145 0.0059 1.0000 0.4514
-1.500 -0.2081 0.00615 0.00142 0.0067 1.0000 0.5070
-1.250 -0.1846 0.00590 0.00142 0.0076 1.0000 0.5674
-1.000 -0.1446 0.00565 0.00143 0.0051 0.9927 0.6319
-0.750 -0.1028 0.00541 0.00143 0.0022 0.9820 0.6923
-0.500 -0.0669 0.00516 0.00142 0.0008 0.9631 0.7537
-0.250 -0.0307 0.00490 0.00141 -0.0004 0.9346 0.8197
0.000 0.0000 0.00477 0.00141 0.0000 0.8872 0.8871
0.250 0.0307 0.00490 0.00141 0.0004 0.8198 0.9347
0.500 0.0669 0.00516 0.00142 -0.0008 0.7534 0.9632
0.750 0.1028 0.00541 0.00143 -0.0022 0.6926 0.9820
1.000 0.1446 0.00565 0.00143 -0.0051 0.6320 0.9927
1.250 0.1846 0.00590 0.00142 -0.0076 0.5671 1.0000
1.500 0.2082 0.00614 0.00143 -0.0067 0.5076 1.0000
1.750 0.2321 0.00640 0.00145 -0.0059 0.4510 1.0000
2.000 0.2565 0.00664 0.00151 -0.0051 0.4031 1.0000
2.250 0.2810 0.00689 0.00158 -0.0044 0.3579 1.0000
2.500 0.3057 0.00716 0.00167 -0.0037 0.3148 1.0000
2.750 0.3306 0.00741 0.00178 -0.0031 0.2787 1.0000
3.000 0.3556 0.00766 0.00191 -0.0025 0.2462 1.0000
3.250 0.3807 0.00792 0.00206 -0.0019 0.2167 1.0000
3.500 0.4058 0.00819 0.00222 -0.0012 0.1893 1.0000
3.750 0.4309 0.00847 0.00240 -0.0007 0.1631 1.0000
4.000 0.4561 0.00878 0.00261 -0.0001 0.1384 1.0000
4.250 0.4813 0.00910 0.00282 0.0005 0.1162 1.0000
4.500 0.5067 0.00942 0.00307 0.0010 0.0992 1.0000
4.750 0.5322 0.00973 0.00333 0.0015 0.0857 1.0000
5.000 0.5577 0.01009 0.00364 0.0021 0.0743 1.0000
5.250 0.5836 0.01036 0.00392 0.0026 0.0664 1.0000
5.500 0.6091 0.01073 0.00429 0.0031 0.0581 1.0000
5.750 0.6341 0.01124 0.00477 0.0036 0.0484 1.0000
6.000 0.6598 0.01160 0.00515 0.0041 0.0418 1.0000
6.250 0.6842 0.01230 0.00589 0.0048 0.0364 1.0000
6.500 0.7098 0.01271 0.00636 0.0053 0.0333 1.0000
6.750 0.7347 0.01325 0.00692 0.0059 0.0306 1.0000
7.000 0.7565 0.01456 0.00833 0.0069 0.0281 1.0000
7.250 0.7808 0.01530 0.00917 0.0075 0.0274 1.0000
7.500 0.8051 0.01603 0.01000 0.0082 0.0267 1.0000
7.750 0.8289 0.01686 0.01096 0.0088 0.0259 1.0000
8.000 0.8529 0.01763 0.01184 0.0095 0.0248 1.0000
8.250 0.8766 0.01841 0.01272 0.0101 0.0237 1.0000
8.500 0.8996 0.01934 0.01375 0.0107 0.0228 1.0000
8.750 0.9220 0.02034 0.01484 0.0114 0.0219 1.0000
9.000 0.9396 0.02258 0.01730 0.0123 0.0206 1.0000
9.250 0.9564 0.02489 0.01992 0.0133 0.0197 1.0000
9.500 0.9790 0.02551 0.02071 0.0139 0.0190 1.0000
9.750 0.9999 0.02641 0.02176 0.0145 0.0180 1.0000
10.000 1.0207 0.02720 0.02265 0.0151 0.0170 1.0000
10.250 1.0408 0.02799 0.02353 0.0157 0.0161 1.0000
10.500 1.0605 0.02869 0.02426 0.0163 0.0152 1.0000
10.750 1.0513 0.03432 0.03040 0.0180 0.0142 1.0000
11.000 1.0712 0.03461 0.03080 0.0186 0.0136 1.0000
11.250 1.0847 0.03580 0.03216 0.0194 0.0129 1.0000
11.500 1.0987 0.03671 0.03318 0.0201 0.0121 1.0000
11.750 1.1070 0.03814 0.03474 0.0210 0.0115 1.0000
12.000 1.1055 0.03994 0.03665 0.0227 0.0112 1.0000
12.250 1.1036 0.04177 0.03856 0.0234 0.0109 1.0000
12.500 1.0918 0.04556 0.04249 0.0216 0.0108 1.0000
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Polar data table (+)
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