S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.02 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9033-il-1000000-n5.txt Download as CSV file: xf-s9033-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1604 0.09247 0.09011 0.0100 1.0000 0.0031
-15.750 -1.2507 0.07112 0.06851 -0.0033 1.0000 0.0026
-15.500 -1.3270 0.05132 0.04838 -0.0177 1.0000 0.0024
-15.250 -1.3568 0.04229 0.03912 -0.0252 1.0000 0.0024
-15.000 -1.3765 0.03730 0.03395 -0.0277 1.0000 0.0024
-14.750 -1.3886 0.03444 0.03095 -0.0270 1.0000 0.0024
-14.500 -1.3971 0.03241 0.02878 -0.0245 1.0000 0.0025
-14.250 -1.3967 0.03070 0.02694 -0.0223 1.0000 0.0025
-14.000 -1.3895 0.02910 0.02520 -0.0209 1.0000 0.0026
-13.750 -1.3807 0.02745 0.02341 -0.0196 1.0000 0.0029
-13.500 -1.3678 0.02608 0.02192 -0.0184 1.0000 0.0031
-13.250 -1.3529 0.02483 0.02056 -0.0174 1.0000 0.0034
-13.000 -1.3362 0.02371 0.01933 -0.0165 1.0000 0.0036
-12.750 -1.3180 0.02270 0.01821 -0.0157 1.0000 0.0040
-12.500 -1.2988 0.02177 0.01717 -0.0150 1.0000 0.0043
-12.250 -1.2787 0.02090 0.01624 -0.0143 1.0000 0.0049
-12.000 -1.2575 0.02014 0.01542 -0.0137 1.0000 0.0055
-11.750 -1.2357 0.01944 0.01465 -0.0131 1.0000 0.0060
-11.500 -1.2133 0.01878 0.01391 -0.0125 1.0000 0.0064
-11.250 -1.1908 0.01811 0.01317 -0.0120 1.0000 0.0069
-11.000 -1.1676 0.01753 0.01256 -0.0115 1.0000 0.0075
-10.750 -1.1440 0.01701 0.01197 -0.0110 1.0000 0.0080
-10.500 -1.1200 0.01651 0.01142 -0.0105 1.0000 0.0085
-10.250 -1.0958 0.01603 0.01088 -0.0101 1.0000 0.0090
-10.000 -1.0713 0.01557 0.01036 -0.0097 1.0000 0.0093
-9.750 -1.0466 0.01515 0.00987 -0.0092 1.0000 0.0096
-9.500 -1.0216 0.01476 0.00942 -0.0088 1.0000 0.0097
-9.250 -0.9977 0.01411 0.00871 -0.0083 1.0000 0.0105
-9.000 -0.9729 0.01364 0.00819 -0.0079 1.0000 0.0113
-8.750 -0.9476 0.01329 0.00784 -0.0076 1.0000 0.0122
-8.500 -0.9220 0.01296 0.00748 -0.0072 1.0000 0.0129
-8.250 -0.8965 0.01258 0.00706 -0.0068 1.0000 0.0134
-8.000 -0.8708 0.01226 0.00669 -0.0064 1.0000 0.0138
-7.750 -0.8450 0.01193 0.00632 -0.0060 1.0000 0.0140
-7.500 -0.8196 0.01149 0.00581 -0.0056 1.0000 0.0145
-7.250 -0.7942 0.01104 0.00530 -0.0051 1.0000 0.0153
-7.000 -0.7684 0.01067 0.00490 -0.0047 1.0000 0.0163
-6.750 -0.7426 0.01034 0.00456 -0.0042 1.0000 0.0174
-6.500 -0.7166 0.01004 0.00424 -0.0038 1.0000 0.0185
-6.250 -0.6905 0.00978 0.00395 -0.0034 1.0000 0.0197
-6.000 -0.6645 0.00949 0.00365 -0.0030 1.0000 0.0226
-5.750 -0.6386 0.00920 0.00339 -0.0025 1.0000 0.0263
-5.500 -0.6127 0.00893 0.00314 -0.0021 1.0000 0.0313
-5.250 -0.5867 0.00869 0.00293 -0.0016 1.0000 0.0366
-5.000 -0.5608 0.00847 0.00271 -0.0011 1.0000 0.0415
-4.750 -0.5350 0.00826 0.00252 -0.0006 1.0000 0.0467
-4.500 -0.5091 0.00808 0.00235 -0.0001 1.0000 0.0511
-4.250 -0.4835 0.00787 0.00218 0.0005 1.0000 0.0575
-4.000 -0.4578 0.00770 0.00202 0.0011 1.0000 0.0635
-3.750 -0.4298 0.00750 0.00187 0.0011 0.9989 0.0728
-3.500 -0.3956 0.00725 0.00172 -0.0003 0.9944 0.0920
-3.250 -0.3626 0.00702 0.00159 -0.0014 0.9875 0.1115
-3.000 -0.3278 0.00684 0.00146 -0.0028 0.9742 0.1272
-2.500 -0.2641 0.00665 0.00122 -0.0040 0.8825 0.1585
-2.250 -0.2394 0.00668 0.00112 -0.0031 0.8284 0.1738
-2.000 -0.2142 0.00674 0.00103 -0.0023 0.7694 0.1906
-1.750 -0.1883 0.00676 0.00096 -0.0018 0.7147 0.2144
-1.250 -0.1350 0.00672 0.00083 -0.0011 0.6273 0.2699
-1.000 -0.1082 0.00666 0.00078 -0.0009 0.5886 0.3081
-0.750 -0.0811 0.00663 0.00074 -0.0007 0.5552 0.3393
-0.500 -0.0540 0.00665 0.00072 -0.0004 0.5142 0.3647
-0.250 -0.0271 0.00670 0.00070 -0.0002 0.4657 0.3919
0.000 0.0000 0.00671 0.00069 0.0000 0.4269 0.4270
0.250 0.0270 0.00671 0.00070 0.0002 0.3918 0.4654
0.500 0.0540 0.00665 0.00072 0.0004 0.3646 0.5135
0.750 0.0811 0.00663 0.00074 0.0007 0.3391 0.5552
1.000 0.1082 0.00666 0.00078 0.0009 0.3080 0.5887
1.250 0.1350 0.00672 0.00083 0.0011 0.2700 0.6275
1.750 0.1882 0.00676 0.00096 0.0018 0.2143 0.7145
2.000 0.2142 0.00674 0.00103 0.0023 0.1905 0.7694
2.250 0.2394 0.00667 0.00112 0.0031 0.1738 0.8290
2.500 0.2641 0.00665 0.00122 0.0040 0.1585 0.8826
2.750 0.2906 0.00668 0.00134 0.0047 0.1436 0.9397
3.000 0.3277 0.00684 0.00146 0.0028 0.1272 0.9742
3.250 0.3624 0.00702 0.00159 0.0014 0.1117 0.9873
3.500 0.3954 0.00725 0.00172 0.0003 0.0922 0.9943
3.750 0.4296 0.00750 0.00187 -0.0010 0.0730 0.9987
4.000 0.4580 0.00770 0.00202 -0.0011 0.0635 1.0000
4.250 0.4837 0.00787 0.00218 -0.0005 0.0576 1.0000
4.500 0.5093 0.00807 0.00235 0.0000 0.0512 1.0000
4.750 0.5351 0.00826 0.00252 0.0006 0.0468 1.0000
5.000 0.5609 0.00847 0.00271 0.0011 0.0416 1.0000
5.250 0.5868 0.00869 0.00293 0.0016 0.0366 1.0000
5.500 0.6127 0.00893 0.00314 0.0021 0.0313 1.0000
5.750 0.6386 0.00920 0.00339 0.0025 0.0263 1.0000
6.000 0.6645 0.00949 0.00365 0.0030 0.0226 1.0000
6.250 0.6905 0.00978 0.00395 0.0034 0.0197 1.0000
6.500 0.7165 0.01004 0.00424 0.0038 0.0186 1.0000
6.750 0.7425 0.01034 0.00456 0.0043 0.0174 1.0000
7.000 0.7684 0.01067 0.00490 0.0047 0.0163 1.0000
7.250 0.7941 0.01104 0.00530 0.0051 0.0154 1.0000
7.500 0.8195 0.01148 0.00580 0.0056 0.0145 1.0000
7.750 0.8449 0.01192 0.00631 0.0061 0.0140 1.0000
8.000 0.8707 0.01225 0.00669 0.0065 0.0138 1.0000
8.250 0.8963 0.01259 0.00707 0.0068 0.0134 1.0000
8.500 0.9218 0.01295 0.00747 0.0072 0.0129 1.0000
8.750 0.9474 0.01328 0.00783 0.0076 0.0122 1.0000
9.000 0.9727 0.01363 0.00818 0.0079 0.0112 1.0000
9.250 0.9974 0.01411 0.00871 0.0084 0.0104 1.0000
9.500 1.0213 0.01476 0.00942 0.0089 0.0097 1.0000
9.750 1.0463 0.01515 0.00987 0.0093 0.0096 1.0000
10.000 1.0710 0.01558 0.01036 0.0097 0.0093 1.0000
10.250 1.0954 0.01603 0.01088 0.0102 0.0090 1.0000
10.500 1.1196 0.01651 0.01142 0.0106 0.0085 1.0000
10.750 1.1436 0.01700 0.01196 0.0111 0.0080 1.0000
11.000 1.1672 0.01753 0.01255 0.0116 0.0075 1.0000
11.250 1.1903 0.01811 0.01318 0.0121 0.0069 1.0000
11.500 1.2129 0.01877 0.01390 0.0126 0.0064 1.0000
11.750 1.2352 0.01943 0.01464 0.0132 0.0060 1.0000
12.000 1.2570 0.02013 0.01542 0.0138 0.0055 1.0000
12.250 1.2781 0.02089 0.01623 0.0144 0.0049 1.0000
12.500 1.2982 0.02176 0.01716 0.0151 0.0043 1.0000
12.750 1.3174 0.02269 0.01820 0.0158 0.0040 1.0000
13.000 1.3355 0.02371 0.01934 0.0167 0.0036 1.0000
13.250 1.3522 0.02484 0.02057 0.0176 0.0033 1.0000
13.500 1.3669 0.02610 0.02194 0.0186 0.0030 1.0000
13.750 1.3801 0.02744 0.02340 0.0197 0.0029 1.0000
14.000 1.3891 0.02908 0.02518 0.0210 0.0026 1.0000
14.250 1.3959 0.03071 0.02695 0.0224 0.0025 1.0000
14.500 1.3966 0.03238 0.02875 0.0246 0.0024 1.0000
14.750 1.3890 0.03437 0.03087 0.0270 0.0025 1.0000
15.000 1.3762 0.03729 0.03395 0.0278 0.0024 1.0000
15.250 1.3567 0.04225 0.03909 0.0252 0.0024 1.0000
15.500 1.3240 0.05192 0.04899 0.0172 0.0025 1.0000
15.750 1.2533 0.07063 0.06802 0.0035 0.0026 1.0000
16.000 1.1588 0.09283 0.09048 -0.0103 0.0031 1.0000
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Polar data table (+)
Polar graphs
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