S9027 (8%) (s9027-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 500,000 Max Cl/Cd: 59.48 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9027-il-500000-n5.txt Download as CSV file: xf-s9027-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9273 0.12751 0.12508 0.0277 1.0000 0.0085
-15.250 -0.9866 0.10905 0.10648 0.0172 1.0000 0.0081
-15.000 -1.0390 0.09385 0.09115 0.0083 1.0000 0.0077
-14.750 -1.1033 0.07712 0.07424 -0.0019 1.0000 0.0072
-14.500 -1.1592 0.06188 0.05876 -0.0120 1.0000 0.0068
-14.250 -1.1919 0.05097 0.04760 -0.0204 1.0000 0.0067
-14.000 -1.2138 0.04361 0.04002 -0.0261 1.0000 0.0067
-13.750 -1.2276 0.03916 0.03540 -0.0283 1.0000 0.0067
-13.500 -1.2322 0.03658 0.03269 -0.0283 1.0000 0.0069
-13.250 -1.2358 0.03452 0.03050 -0.0269 1.0000 0.0071
-13.000 -1.2382 0.03276 0.02860 -0.0246 1.0000 0.0073
-12.750 -1.2317 0.03136 0.02707 -0.0229 1.0000 0.0076
-12.500 -1.2217 0.03000 0.02556 -0.0216 1.0000 0.0080
-12.250 -1.2098 0.02866 0.02405 -0.0204 1.0000 0.0083
-12.000 -1.1955 0.02746 0.02269 -0.0193 1.0000 0.0087
-11.750 -1.1797 0.02633 0.02139 -0.0182 1.0000 0.0090
-11.500 -1.1662 0.02484 0.01977 -0.0170 1.0000 0.0095
-11.250 -1.1478 0.02389 0.01874 -0.0162 1.0000 0.0100
-11.000 -1.1278 0.02310 0.01785 -0.0155 1.0000 0.0105
-10.750 -1.1066 0.02243 0.01710 -0.0148 1.0000 0.0112
-10.500 -1.0855 0.02168 0.01624 -0.0141 1.0000 0.0118
-10.250 -1.0641 0.02094 0.01535 -0.0134 1.0000 0.0124
-10.000 -1.0421 0.02026 0.01454 -0.0127 1.0000 0.0128
-9.750 -1.0227 0.01912 0.01329 -0.0118 1.0000 0.0135
-9.500 -1.0010 0.01832 0.01242 -0.0111 1.0000 0.0142
-9.250 -0.9779 0.01774 0.01178 -0.0105 1.0000 0.0151
-9.000 -0.9546 0.01716 0.01112 -0.0099 1.0000 0.0159
-8.750 -0.9311 0.01658 0.01046 -0.0093 1.0000 0.0166
-8.500 -0.9074 0.01603 0.00980 -0.0087 1.0000 0.0173
-8.250 -0.8832 0.01556 0.00925 -0.0081 1.0000 0.0179
-8.000 -0.8606 0.01477 0.00837 -0.0073 1.0000 0.0191
-7.750 -0.8369 0.01419 0.00775 -0.0067 1.0000 0.0203
-7.500 -0.8126 0.01371 0.00723 -0.0061 1.0000 0.0215
-7.250 -0.7879 0.01328 0.00675 -0.0055 1.0000 0.0230
-7.000 -0.7632 0.01289 0.00628 -0.0049 1.0000 0.0243
-6.750 -0.7387 0.01242 0.00577 -0.0043 1.0000 0.0266
-6.500 -0.7141 0.01201 0.00536 -0.0037 1.0000 0.0296
-6.250 -0.6891 0.01168 0.00500 -0.0031 1.0000 0.0327
-6.000 -0.6644 0.01131 0.00464 -0.0025 1.0000 0.0376
-5.750 -0.6394 0.01101 0.00432 -0.0019 1.0000 0.0425
-5.500 -0.6147 0.01070 0.00402 -0.0012 1.0000 0.0483
-5.250 -0.5898 0.01043 0.00375 -0.0006 1.0000 0.0545
-5.000 -0.5651 0.01013 0.00349 0.0001 1.0000 0.0616
-4.750 -0.5403 0.00989 0.00324 0.0008 1.0000 0.0684
-4.500 -0.5156 0.00963 0.00302 0.0015 1.0000 0.0783
-4.250 -0.4910 0.00936 0.00281 0.0022 1.0000 0.0905
-4.000 -0.4665 0.00911 0.00262 0.0029 1.0000 0.1057
-3.750 -0.4421 0.00886 0.00244 0.0036 1.0000 0.1221
-3.500 -0.4175 0.00864 0.00227 0.0043 1.0000 0.1369
-3.250 -0.3903 0.00842 0.00213 0.0044 0.9989 0.1540
-2.750 -0.3192 0.00797 0.00187 0.0011 0.9870 0.2017
-2.500 -0.2845 0.00777 0.00175 -0.0004 0.9793 0.2253
-2.250 -0.2501 0.00754 0.00165 -0.0018 0.9671 0.2547
-2.000 -0.2157 0.00729 0.00153 -0.0031 0.9487 0.2936
-1.750 -0.1801 0.00702 0.00143 -0.0047 0.9223 0.3408
-1.500 -0.1502 0.00688 0.00133 -0.0048 0.8850 0.3745
-1.250 -0.1247 0.00680 0.00124 -0.0040 0.8443 0.4092
-1.000 -0.1000 0.00676 0.00117 -0.0031 0.7993 0.4469
-0.750 -0.0752 0.00675 0.00112 -0.0022 0.7532 0.4835
0.000 0.0000 0.00664 0.00105 0.0000 0.6235 0.6239
0.750 0.0752 0.00675 0.00112 0.0022 0.4833 0.7532
1.000 0.1001 0.00676 0.00117 0.0031 0.4468 0.7991
1.250 0.1247 0.00680 0.00124 0.0040 0.4094 0.8442
1.500 0.1502 0.00688 0.00133 0.0048 0.3746 0.8851
1.750 0.1801 0.00702 0.00143 0.0047 0.3409 0.9225
2.000 0.2157 0.00729 0.00153 0.0031 0.2937 0.9487
2.250 0.2501 0.00754 0.00164 0.0018 0.2544 0.9673
2.500 0.2845 0.00776 0.00175 0.0004 0.2254 0.9795
2.750 0.3193 0.00797 0.00186 -0.0011 0.2015 0.9872
3.000 0.3536 0.00820 0.00200 -0.0025 0.1780 0.9939
3.250 0.3905 0.00842 0.00213 -0.0045 0.1539 0.9992
3.500 0.4171 0.00863 0.00227 -0.0042 0.1371 1.0000
3.750 0.4416 0.00885 0.00243 -0.0035 0.1222 1.0000
4.000 0.4661 0.00910 0.00261 -0.0028 0.1058 1.0000
4.250 0.4906 0.00936 0.00281 -0.0021 0.0906 1.0000
4.500 0.5152 0.00962 0.00301 -0.0014 0.0785 1.0000
4.750 0.5399 0.00989 0.00324 -0.0007 0.0685 1.0000
5.000 0.5647 0.01013 0.00348 0.0000 0.0617 1.0000
5.250 0.5894 0.01043 0.00375 0.0007 0.0545 1.0000
5.500 0.6144 0.01070 0.00401 0.0013 0.0484 1.0000
5.750 0.6392 0.01101 0.00432 0.0019 0.0425 1.0000
6.000 0.6642 0.01131 0.00464 0.0025 0.0376 1.0000
6.250 0.6890 0.01168 0.00500 0.0031 0.0327 1.0000
6.500 0.7140 0.01201 0.00536 0.0037 0.0296 1.0000
6.750 0.7387 0.01242 0.00577 0.0043 0.0265 1.0000
7.000 0.7632 0.01289 0.00628 0.0049 0.0243 1.0000
7.250 0.7880 0.01329 0.00675 0.0055 0.0230 1.0000
7.500 0.8127 0.01371 0.00722 0.0061 0.0215 1.0000
7.750 0.8371 0.01419 0.00775 0.0066 0.0203 1.0000
8.000 0.8610 0.01477 0.00838 0.0073 0.0191 1.0000
8.250 0.8835 0.01558 0.00926 0.0080 0.0179 1.0000
8.500 0.9078 0.01605 0.00982 0.0086 0.0174 1.0000
8.750 0.9316 0.01659 0.01046 0.0092 0.0166 1.0000
9.000 0.9551 0.01717 0.01114 0.0098 0.0159 1.0000
9.250 0.9785 0.01775 0.01178 0.0104 0.0151 1.0000
9.500 1.0017 0.01832 0.01242 0.0110 0.0142 1.0000
9.750 1.0234 0.01913 0.01329 0.0117 0.0135 1.0000
10.000 1.0428 0.02027 0.01455 0.0126 0.0128 1.0000
10.250 1.0650 0.02093 0.01534 0.0132 0.0124 1.0000
10.500 1.0867 0.02165 0.01621 0.0139 0.0118 1.0000
10.750 1.1078 0.02239 0.01706 0.0146 0.0111 1.0000
11.000 1.1286 0.02314 0.01790 0.0153 0.0105 1.0000
11.250 1.1488 0.02392 0.01876 0.0160 0.0100 1.0000
11.500 1.1672 0.02488 0.01981 0.0168 0.0095 1.0000
11.750 1.1811 0.02633 0.02139 0.0180 0.0090 1.0000
12.000 1.1971 0.02745 0.02267 0.0190 0.0087 1.0000
12.250 1.2105 0.02876 0.02415 0.0202 0.0084 1.0000
12.500 1.2230 0.03004 0.02562 0.0213 0.0080 1.0000
12.750 1.2326 0.03148 0.02720 0.0227 0.0076 1.0000
13.000 1.2392 0.03288 0.02873 0.0243 0.0073 1.0000
13.250 1.2406 0.03438 0.03034 0.0264 0.0070 1.0000
13.500 1.2361 0.03647 0.03258 0.0279 0.0069 1.0000
13.750 1.2325 0.03892 0.03514 0.0280 0.0067 1.0000
14.000 1.2214 0.04292 0.03929 0.0262 0.0066 1.0000
14.250 1.1984 0.05026 0.04687 0.0206 0.0066 1.0000
14.500 1.1538 0.06343 0.06034 0.0105 0.0069 1.0000
14.750 1.0992 0.07836 0.07551 0.0007 0.0073 1.0000
15.000 1.0369 0.09481 0.09212 -0.0092 0.0078 1.0000
15.250 0.9845 0.11007 0.10751 -0.0182 0.0082 1.0000
15.500 0.9253 0.12872 0.12629 -0.0287 0.0085 1.0000
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Polar data table (+)
Polar graphs
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