S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.67 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9033-il-1000000.txt Download as CSV file: xf-s9033-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9810 0.13549 0.13368 0.0366 1.0000 0.0064
-16.000 -1.0357 0.11786 0.11591 0.0262 1.0000 0.0061
-15.750 -1.0961 0.10091 0.09881 0.0159 1.0000 0.0056
-15.500 -1.1974 0.07765 0.07527 0.0015 1.0000 0.0046
-15.250 -1.2215 0.06909 0.06660 -0.0035 1.0000 0.0043
-15.000 -1.2912 0.05029 0.04751 -0.0173 1.0000 0.0040
-14.750 -1.3184 0.04157 0.03857 -0.0247 1.0000 0.0040
-14.500 -1.3315 0.03738 0.03422 -0.0268 1.0000 0.0041
-14.250 -1.3485 0.03420 0.03088 -0.0258 1.0000 0.0041
-14.000 -1.3529 0.03245 0.02901 -0.0233 1.0000 0.0042
-13.750 -1.3574 0.03001 0.02636 -0.0211 1.0000 0.0043
-13.500 -1.3548 0.02771 0.02388 -0.0195 1.0000 0.0048
-13.250 -1.3410 0.02641 0.02249 -0.0185 1.0000 0.0052
-13.000 -1.3238 0.02541 0.02143 -0.0177 1.0000 0.0056
-12.750 -1.3044 0.02464 0.02057 -0.0170 1.0000 0.0060
-12.500 -1.2843 0.02389 0.01973 -0.0163 1.0000 0.0064
-12.250 -1.2684 0.02250 0.01822 -0.0154 1.0000 0.0072
-12.000 -1.2456 0.02204 0.01776 -0.0149 1.0000 0.0078
-11.750 -1.2220 0.02168 0.01739 -0.0145 1.0000 0.0084
-11.500 -1.1987 0.02125 0.01690 -0.0141 1.0000 0.0090
-11.250 -1.1746 0.02091 0.01651 -0.0137 1.0000 0.0094
-11.000 -1.1494 0.02074 0.01631 -0.0134 1.0000 0.0097
-10.750 -1.1335 0.01898 0.01434 -0.0123 1.0000 0.0106
-10.500 -1.1110 0.01828 0.01359 -0.0118 1.0000 0.0112
-10.250 -1.0868 0.01786 0.01314 -0.0114 1.0000 0.0118
-10.000 -1.0627 0.01739 0.01262 -0.0109 1.0000 0.0123
-9.750 -1.0385 0.01690 0.01207 -0.0105 1.0000 0.0129
-9.500 -1.0141 0.01643 0.01153 -0.0100 1.0000 0.0134
-9.250 -0.9889 0.01609 0.01115 -0.0097 1.0000 0.0138
-9.000 -0.9628 0.01593 0.01094 -0.0094 1.0000 0.0141
-8.750 -0.9432 0.01439 0.00921 -0.0084 1.0000 0.0155
-8.500 -0.9184 0.01392 0.00873 -0.0080 1.0000 0.0167
-8.250 -0.8931 0.01353 0.00832 -0.0076 1.0000 0.0175
-8.000 -0.8679 0.01309 0.00783 -0.0072 1.0000 0.0183
-7.750 -0.8428 0.01261 0.00729 -0.0067 1.0000 0.0189
-7.500 -0.8173 0.01221 0.00682 -0.0062 1.0000 0.0195
-7.250 -0.7917 0.01181 0.00636 -0.0058 1.0000 0.0198
-7.000 -0.7662 0.01140 0.00590 -0.0053 1.0000 0.0201
-6.750 -0.7420 0.01062 0.00499 -0.0046 1.0000 0.0217
-6.500 -0.7167 0.01014 0.00448 -0.0040 1.0000 0.0240
-6.250 -0.6908 0.00980 0.00413 -0.0036 1.0000 0.0262
-6.000 -0.6649 0.00947 0.00377 -0.0031 1.0000 0.0295
-5.750 -0.6393 0.00911 0.00346 -0.0026 1.0000 0.0370
-5.500 -0.6136 0.00878 0.00317 -0.0021 1.0000 0.0458
-5.250 -0.5875 0.00857 0.00296 -0.0016 1.0000 0.0509
-5.000 -0.5618 0.00830 0.00272 -0.0011 1.0000 0.0586
-4.750 -0.5360 0.00809 0.00252 -0.0006 1.0000 0.0654
-4.500 -0.5103 0.00787 0.00233 0.0000 1.0000 0.0738
-4.250 -0.4848 0.00763 0.00215 0.0005 1.0000 0.0857
-4.000 -0.4593 0.00741 0.00199 0.0011 1.0000 0.0989
-3.750 -0.4338 0.00720 0.00183 0.0017 1.0000 0.1134
-3.500 -0.4087 0.00695 0.00169 0.0023 1.0000 0.1355
-3.250 -0.3835 0.00671 0.00156 0.0030 1.0000 0.1605
-3.000 -0.3583 0.00651 0.00145 0.0036 1.0000 0.1839
-2.750 -0.3332 0.00631 0.00134 0.0042 1.0000 0.2065
-2.500 -0.3082 0.00612 0.00126 0.0049 1.0000 0.2311
-2.250 -0.2776 0.00594 0.00118 0.0043 0.9985 0.2599
-2.000 -0.2381 0.00574 0.00112 0.0018 0.9939 0.2963
-1.750 -0.1996 0.00551 0.00106 -0.0005 0.9858 0.3394
-1.500 -0.1630 0.00527 0.00100 -0.0023 0.9723 0.3855
-1.250 -0.1271 0.00504 0.00093 -0.0039 0.9450 0.4391
-1.000 -0.0994 0.00489 0.00086 -0.0035 0.8928 0.4920
-0.750 -0.0754 0.00488 0.00081 -0.0023 0.8374 0.5366
-0.500 -0.0508 0.00493 0.00078 -0.0014 0.7780 0.5769
-0.250 -0.0256 0.00499 0.00076 -0.0006 0.7178 0.6196
0.000 0.0000 0.00500 0.00075 0.0000 0.6678 0.6679
0.250 0.0256 0.00499 0.00076 0.0006 0.6195 0.7176
0.500 0.0507 0.00493 0.00078 0.0014 0.5768 0.7775
0.750 0.0753 0.00488 0.00081 0.0024 0.5365 0.8375
1.000 0.0993 0.00489 0.00086 0.0035 0.4919 0.8929
1.250 0.1271 0.00504 0.00093 0.0039 0.4391 0.9451
1.500 0.1630 0.00527 0.00100 0.0023 0.3854 0.9723
1.750 0.1995 0.00551 0.00106 0.0005 0.3395 0.9857
2.000 0.2379 0.00574 0.00112 -0.0018 0.2963 0.9938
2.250 0.2775 0.00594 0.00118 -0.0043 0.2601 0.9984
2.500 0.3083 0.00612 0.00126 -0.0049 0.2310 1.0000
2.750 0.3334 0.00631 0.00134 -0.0043 0.2066 1.0000
3.000 0.3585 0.00651 0.00145 -0.0036 0.1838 1.0000
3.250 0.3837 0.00671 0.00156 -0.0030 0.1604 1.0000
3.500 0.4088 0.00694 0.00169 -0.0024 0.1356 1.0000
3.750 0.4340 0.00720 0.00183 -0.0018 0.1135 1.0000
4.000 0.4595 0.00741 0.00199 -0.0012 0.0989 1.0000
4.250 0.4850 0.00763 0.00215 -0.0006 0.0857 1.0000
4.500 0.5104 0.00787 0.00233 0.0000 0.0738 1.0000
4.750 0.5361 0.00809 0.00252 0.0006 0.0654 1.0000
5.000 0.5619 0.00830 0.00272 0.0011 0.0587 1.0000
5.250 0.5876 0.00857 0.00296 0.0016 0.0509 1.0000
5.500 0.6137 0.00878 0.00317 0.0021 0.0457 1.0000
5.750 0.6393 0.00911 0.00346 0.0026 0.0370 1.0000
6.000 0.6650 0.00947 0.00377 0.0031 0.0295 1.0000
6.250 0.6908 0.00979 0.00413 0.0036 0.0263 1.0000
6.500 0.7166 0.01014 0.00448 0.0040 0.0240 1.0000
6.750 0.7420 0.01060 0.00498 0.0046 0.0219 1.0000
7.000 0.7661 0.01140 0.00590 0.0053 0.0201 1.0000
7.250 0.7916 0.01181 0.00636 0.0058 0.0198 1.0000
7.500 0.8172 0.01220 0.00680 0.0062 0.0195 1.0000
7.750 0.8427 0.01260 0.00727 0.0067 0.0189 1.0000
8.000 0.8678 0.01308 0.00782 0.0072 0.0183 1.0000
8.250 0.8929 0.01354 0.00833 0.0077 0.0175 1.0000
8.500 0.9183 0.01391 0.00873 0.0080 0.0166 1.0000
8.750 0.9430 0.01438 0.00921 0.0084 0.0155 1.0000
9.000 0.9631 0.01583 0.01083 0.0094 0.0141 1.0000
9.250 0.9888 0.01607 0.01112 0.0097 0.0138 1.0000
9.500 1.0138 0.01644 0.01154 0.0101 0.0134 1.0000
9.750 1.0382 0.01691 0.01208 0.0105 0.0129 1.0000
10.000 1.0623 0.01740 0.01264 0.0110 0.0123 1.0000
10.250 1.0864 0.01787 0.01316 0.0114 0.0118 1.0000
10.500 1.1106 0.01829 0.01360 0.0118 0.0112 1.0000
10.750 1.1330 0.01898 0.01434 0.0124 0.0105 1.0000
11.000 1.1490 0.02072 0.01629 0.0135 0.0097 1.0000
11.250 1.1737 0.02097 0.01658 0.0138 0.0095 1.0000
11.500 1.1981 0.02124 0.01690 0.0142 0.0090 1.0000
11.750 1.2215 0.02166 0.01736 0.0146 0.0084 1.0000
12.000 1.2449 0.02204 0.01777 0.0151 0.0078 1.0000
12.250 1.2677 0.02250 0.01822 0.0155 0.0072 1.0000
12.500 1.2836 0.02388 0.01973 0.0165 0.0064 1.0000
12.750 1.3039 0.02459 0.02052 0.0171 0.0060 1.0000
13.000 1.3230 0.02541 0.02143 0.0178 0.0055 1.0000
13.250 1.3410 0.02631 0.02237 0.0186 0.0051 1.0000
13.500 1.3537 0.02773 0.02389 0.0197 0.0047 1.0000
13.750 1.3582 0.02983 0.02617 0.0212 0.0044 1.0000
14.000 1.3499 0.03256 0.02912 0.0236 0.0042 1.0000
14.250 1.3442 0.03442 0.03111 0.0261 0.0041 1.0000
14.500 1.3353 0.03695 0.03378 0.0270 0.0041 1.0000
14.750 1.3062 0.04329 0.04033 0.0233 0.0042 1.0000
15.000 1.2719 0.05431 0.05159 0.0138 0.0042 1.0000
15.250 1.2267 0.06801 0.06551 0.0042 0.0043 1.0000
15.500 1.1983 0.07740 0.07503 -0.0013 0.0048 1.0000
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Polar data table (+)
Polar graphs
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