Coanda 1 (coanda1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 100,000 Max Cl/Cd: 47.75 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda1-il-100000-n5.txt Download as CSV file: xf-coanda1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4333 0.10402 0.09925 -0.0192 1.0000 0.0460
-8.250 -0.4329 0.10080 0.09609 -0.0195 1.0000 0.0459
-8.000 -0.4388 0.09865 0.09402 -0.0208 1.0000 0.0461
-7.500 -0.4299 0.08728 0.08268 -0.0173 1.0000 0.0272
-7.250 -0.4288 0.08414 0.07959 -0.0175 1.0000 0.0257
-7.000 -0.4281 0.08069 0.07619 -0.0183 1.0000 0.0246
-6.750 -0.4259 0.07718 0.07271 -0.0194 1.0000 0.0234
-6.500 -0.4233 0.07300 0.06855 -0.0210 1.0000 0.0220
-6.250 -0.4180 0.06759 0.06313 -0.0239 1.0000 0.0202
-6.000 -0.4086 0.06394 0.05941 -0.0242 1.0000 0.0193
-5.750 -0.4016 0.06043 0.05585 -0.0241 1.0000 0.0190
-5.500 -0.3935 0.05653 0.05188 -0.0240 1.0000 0.0186
-5.250 -0.3840 0.05262 0.04787 -0.0237 1.0000 0.0183
-5.000 -0.3735 0.04864 0.04374 -0.0231 1.0000 0.0181
-4.750 -0.3623 0.04439 0.03930 -0.0222 1.0000 0.0179
-4.500 -0.3503 0.04024 0.03491 -0.0208 1.0000 0.0176
-4.250 -0.3382 0.03544 0.02973 -0.0189 1.0000 0.0174
-4.000 -0.3252 0.03038 0.02413 -0.0165 1.0000 0.0172
-3.750 -0.3093 0.02598 0.01902 -0.0140 1.0000 0.0172
-3.500 -0.2900 0.02324 0.01564 -0.0120 1.0000 0.0176
-3.250 -0.2686 0.02151 0.01339 -0.0104 1.0000 0.0192
-3.000 -0.2465 0.02014 0.01166 -0.0089 1.0000 0.0217
-2.750 -0.2127 0.01926 0.01052 -0.0099 0.9962 0.0247
-2.500 -0.1752 0.02027 0.01196 -0.0121 0.9890 0.0463
-2.250 -0.1376 0.02057 0.01161 -0.0136 0.9823 0.0791
-2.000 -0.1031 0.02124 0.01201 -0.0153 0.9749 0.0973
-1.750 -0.0684 0.02097 0.01160 -0.0172 0.9683 0.1095
-1.500 -0.0351 0.02037 0.01076 -0.0183 0.9608 0.1098
-1.250 0.0027 0.01993 0.01005 -0.0203 0.9550 0.1118
-1.000 0.0348 0.01947 0.00943 -0.0211 0.9460 0.1128
-0.750 0.0723 0.01892 0.00877 -0.0231 0.9397 0.1128
-0.500 0.1063 0.01845 0.00820 -0.0243 0.9308 0.1131
-0.250 0.1414 0.01796 0.00769 -0.0258 0.9223 0.1135
0.000 0.1820 0.01728 0.00707 -0.0284 0.9146 0.1148
0.250 0.2199 0.01666 0.00652 -0.0302 0.9018 0.1165
0.500 0.2593 0.01611 0.00603 -0.0323 0.8869 0.1181
0.750 0.2961 0.01567 0.00564 -0.0338 0.8687 0.1202
1.000 0.3360 0.01529 0.00526 -0.0359 0.8468 0.1225
1.250 0.3761 0.01495 0.00489 -0.0380 0.8175 0.1266
1.500 0.4167 0.01460 0.00455 -0.0402 0.7821 0.1322
1.750 0.4547 0.01443 0.00434 -0.0420 0.7496 0.1361
2.000 0.4891 0.01439 0.00422 -0.0430 0.7173 0.1390
2.250 0.5196 0.01443 0.00425 -0.0433 0.6827 0.1425
2.500 0.5482 0.01450 0.00432 -0.0432 0.6483 0.1479
2.750 0.5752 0.01460 0.00445 -0.0428 0.6129 0.1593
3.250 0.7058 0.01478 0.00529 -0.0599 0.3531 1.0000
3.500 0.7218 0.01587 0.00564 -0.0580 0.2447 1.0000
3.750 0.7418 0.01659 0.00607 -0.0567 0.1885 1.0000
4.000 0.7620 0.01732 0.00656 -0.0553 0.1399 1.0000
4.500 0.7974 0.01962 0.00828 -0.0516 0.0210 1.0000
4.750 0.8176 0.02048 0.00934 -0.0500 0.0180 1.0000
5.000 0.8376 0.02142 0.01051 -0.0483 0.0169 1.0000
5.250 0.8573 0.02236 0.01175 -0.0465 0.0166 1.0000
5.500 0.8757 0.02341 0.01304 -0.0446 0.0162 1.0000
5.750 0.8928 0.02455 0.01440 -0.0426 0.0157 1.0000
6.000 0.9085 0.02576 0.01581 -0.0403 0.0149 1.0000
6.250 0.9233 0.02709 0.01730 -0.0380 0.0140 1.0000
6.500 0.9379 0.02861 0.01895 -0.0356 0.0137 1.0000
6.750 0.9537 0.03024 0.02070 -0.0334 0.0138 1.0000
7.000 0.9711 0.03212 0.02272 -0.0314 0.0138 1.0000
7.250 0.9890 0.03406 0.02494 -0.0296 0.0140 1.0000
7.500 1.0064 0.03637 0.02750 -0.0276 0.0144 1.0000
7.750 1.0218 0.03897 0.03041 -0.0255 0.0148 1.0000
8.000 1.0340 0.04190 0.03368 -0.0230 0.0152 1.0000
8.250 1.0432 0.04484 0.03694 -0.0205 0.0158 1.0000
8.500 1.0485 0.04887 0.04126 -0.0179 0.0165 1.0000
8.750 1.0657 0.04985 0.04250 -0.0156 0.0183 1.0000
9.000 1.0636 0.05239 0.04564 -0.0114 0.0198 1.0000
9.250 1.0563 0.05587 0.04956 -0.0075 0.0209 1.0000
9.500 1.0485 0.05909 0.05307 -0.0041 0.0219 1.0000
9.750 1.0321 0.06196 0.05617 0.0000 0.0217 1.0000
10.000 1.0151 0.06512 0.05952 0.0033 0.0223 1.0000
10.250 0.9979 0.06849 0.06307 0.0052 0.0225 1.0000
10.500 0.9789 0.07259 0.06734 0.0055 0.0227 1.0000
10.750 0.9631 0.07701 0.07190 0.0044 0.0230 1.0000
11.000 0.9406 0.08302 0.07806 0.0009 0.0227 1.0000
11.250 0.9206 0.09007 0.08524 -0.0039 0.0226 1.0000
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Polar data table (+)
Polar graphs
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