S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1010 HPV airfoil (s1010-il) Reynolds number: 500,000 Max Cl/Cd: 53.06 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1010-il-500000.txt Download as CSV file: xf-s1010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S1010 HPV airfoil
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6617 0.07508 0.07305 0.0041 1.0000 0.0128
-9.750 -0.7442 0.07832 0.07617 0.0021 1.0000 0.0127
-9.500 -0.7672 0.06932 0.06725 -0.0052 1.0000 0.0123
-9.000 -0.8620 0.03887 0.03589 -0.0170 1.0000 0.0107
-8.750 -0.8662 0.03272 0.02915 -0.0157 1.0000 0.0106
-8.500 -0.8588 0.02847 0.02440 -0.0143 1.0000 0.0108
-8.250 -0.8463 0.02496 0.02042 -0.0128 1.0000 0.0109
-8.000 -0.8288 0.02255 0.01765 -0.0116 1.0000 0.0113
-7.750 -0.8088 0.02067 0.01548 -0.0106 1.0000 0.0121
-7.500 -0.7868 0.01928 0.01384 -0.0097 1.0000 0.0127
-7.250 -0.7670 0.01714 0.01137 -0.0084 1.0000 0.0137
-7.000 -0.7459 0.01559 0.00966 -0.0074 1.0000 0.0153
-6.750 -0.7216 0.01500 0.00901 -0.0069 1.0000 0.0172
-6.500 -0.6966 0.01459 0.00852 -0.0063 1.0000 0.0192
-6.250 -0.6751 0.01319 0.00695 -0.0051 1.0000 0.0216
-6.000 -0.6511 0.01256 0.00629 -0.0044 1.0000 0.0244
-5.750 -0.6262 0.01217 0.00582 -0.0038 1.0000 0.0274
-5.500 -0.6031 0.01138 0.00497 -0.0028 1.0000 0.0318
-5.250 -0.5786 0.01098 0.00455 -0.0021 1.0000 0.0377
-5.000 -0.5549 0.01046 0.00405 -0.0012 1.0000 0.0484
-4.750 -0.5310 0.01007 0.00368 -0.0004 1.0000 0.0598
-4.500 -0.5068 0.00975 0.00338 0.0003 1.0000 0.0698
-4.250 -0.4826 0.00948 0.00310 0.0011 1.0000 0.0800
-4.000 -0.4585 0.00924 0.00288 0.0019 1.0000 0.0913
-3.750 -0.4346 0.00900 0.00267 0.0027 1.0000 0.1035
-3.500 -0.4110 0.00874 0.00248 0.0035 1.0000 0.1192
-3.250 -0.3876 0.00849 0.00229 0.0044 1.0000 0.1364
-3.000 -0.3643 0.00827 0.00212 0.0053 1.0000 0.1546
-2.750 -0.3413 0.00803 0.00198 0.0063 1.0000 0.1774
-2.500 -0.3185 0.00780 0.00186 0.0072 1.0000 0.2051
-2.250 -0.2960 0.00755 0.00175 0.0082 1.0000 0.2425
-2.000 -0.2738 0.00725 0.00166 0.0092 1.0000 0.2965
-1.750 -0.2522 0.00684 0.00160 0.0102 1.0000 0.3852
-1.500 -0.2304 0.00627 0.00156 0.0110 0.9997 0.5230
-1.250 -0.1876 0.00532 0.00161 0.0079 0.9907 0.7771
-1.000 -0.1487 0.00513 0.00165 0.0060 0.9843 0.8533
-0.750 -0.1126 0.00504 0.00168 0.0048 0.9778 0.8952
-0.500 -0.0744 0.00501 0.00170 0.0031 0.9720 0.9222
-0.250 -0.0384 0.00501 0.00171 0.0018 0.9641 0.9416
0.000 0.0000 0.00501 0.00171 0.0000 0.9552 0.9552
0.250 0.0384 0.00501 0.00171 -0.0018 0.9416 0.9643
0.500 0.0743 0.00501 0.00170 -0.0030 0.9221 0.9720
0.750 0.1128 0.00504 0.00168 -0.0048 0.8950 0.9779
1.000 0.1488 0.00513 0.00165 -0.0061 0.8539 0.9843
1.250 0.1877 0.00532 0.00161 -0.0079 0.7761 0.9907
1.500 0.2306 0.00627 0.00156 -0.0111 0.5233 0.9997
1.750 0.2522 0.00684 0.00160 -0.0102 0.3857 1.0000
2.000 0.2738 0.00725 0.00166 -0.0092 0.2966 1.0000
2.250 0.2961 0.00755 0.00175 -0.0082 0.2424 1.0000
2.500 0.3186 0.00780 0.00185 -0.0072 0.2052 1.0000
2.750 0.3414 0.00803 0.00198 -0.0063 0.1773 1.0000
3.000 0.3643 0.00827 0.00212 -0.0053 0.1545 1.0000
3.250 0.3876 0.00849 0.00229 -0.0044 0.1363 1.0000
3.500 0.4110 0.00874 0.00247 -0.0036 0.1190 1.0000
3.750 0.4346 0.00900 0.00267 -0.0027 0.1034 1.0000
4.000 0.4585 0.00924 0.00288 -0.0019 0.0913 1.0000
4.250 0.4827 0.00948 0.00310 -0.0011 0.0800 1.0000
4.500 0.5069 0.00975 0.00338 -0.0003 0.0699 1.0000
4.750 0.5310 0.01007 0.00368 0.0004 0.0599 1.0000
5.000 0.5550 0.01046 0.00405 0.0012 0.0484 1.0000
5.250 0.5787 0.01099 0.00456 0.0021 0.0376 1.0000
5.500 0.6032 0.01138 0.00497 0.0028 0.0318 1.0000
5.750 0.6263 0.01218 0.00583 0.0038 0.0274 1.0000
6.000 0.6512 0.01255 0.00628 0.0044 0.0244 1.0000
6.250 0.6751 0.01319 0.00695 0.0051 0.0216 1.0000
6.500 0.6967 0.01457 0.00850 0.0063 0.0191 1.0000
6.750 0.7216 0.01501 0.00902 0.0069 0.0172 1.0000
7.000 0.7460 0.01557 0.00964 0.0074 0.0153 1.0000
7.250 0.7670 0.01715 0.01137 0.0084 0.0137 1.0000
7.500 0.7865 0.01938 0.01396 0.0097 0.0128 1.0000
7.750 0.8088 0.02063 0.01544 0.0106 0.0120 1.0000
8.000 0.8286 0.02259 0.01770 0.0117 0.0114 1.0000
8.250 0.8461 0.02499 0.02045 0.0129 0.0109 1.0000
8.500 0.8587 0.02846 0.02439 0.0143 0.0108 1.0000
8.750 0.8659 0.03276 0.02920 0.0157 0.0106 1.0000
9.000 0.8638 0.03846 0.03545 0.0170 0.0106 1.0000
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Polar data table (+)
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