Coanda 1 (coanda1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 200,000 Max Cl/Cd: 45.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda1-il-200000-n5.txt Download as CSV file: xf-coanda1-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4260 0.09061 0.08728 -0.0166 1.0000 0.0218
-7.750 -0.4283 0.08802 0.08474 -0.0165 1.0000 0.0223
-7.500 -0.4323 0.08560 0.08237 -0.0159 1.0000 0.0227
-7.250 -0.4331 0.08266 0.07947 -0.0162 1.0000 0.0228
-7.000 -0.4338 0.07850 0.07532 -0.0170 1.0000 0.0158
-6.750 -0.4325 0.07498 0.07183 -0.0179 1.0000 0.0145
-6.500 -0.4325 0.06941 0.06627 -0.0201 1.0000 0.0120
-6.250 -0.4236 0.06534 0.06218 -0.0212 1.0000 0.0108
-6.000 -0.4177 0.06223 0.05902 -0.0207 1.0000 0.0099
-5.750 -0.4116 0.05849 0.05523 -0.0209 1.0000 0.0097
-5.500 -0.4046 0.05431 0.05099 -0.0209 1.0000 0.0094
-5.250 -0.3961 0.05012 0.04668 -0.0205 1.0000 0.0091
-5.000 -0.3787 0.04494 0.04132 -0.0218 0.9984 0.0088
-4.750 -0.3483 0.03752 0.03350 -0.0253 0.9930 0.0086
-4.500 -0.3213 0.02965 0.02499 -0.0268 0.9877 0.0082
-4.250 -0.2984 0.02356 0.01811 -0.0260 0.9824 0.0080
-4.000 -0.2691 0.02108 0.01513 -0.0263 0.9789 0.0092
-3.750 -0.2409 0.01945 0.01309 -0.0261 0.9746 0.0102
-3.250 -0.1788 0.01651 0.00939 -0.0267 0.9674 0.0112
-3.000 -0.1510 0.01578 0.00841 -0.0263 0.9612 0.0124
-2.750 -0.1177 0.01492 0.00729 -0.0271 0.9574 0.0161
-2.500 -0.0834 0.01407 0.00625 -0.0281 0.9539 0.0213
-2.250 -0.0535 0.01487 0.00716 -0.0282 0.9461 0.0689
-2.000 -0.0184 0.01549 0.00770 -0.0298 0.9417 0.0781
-1.750 0.0094 0.01596 0.00799 -0.0296 0.9334 0.0869
-1.500 0.0440 0.01523 0.00717 -0.0310 0.9291 0.0880
-1.250 0.0747 0.01472 0.00659 -0.0316 0.9219 0.0887
-1.000 0.1117 0.01422 0.00605 -0.0334 0.9152 0.0903
-0.750 0.1456 0.01376 0.00553 -0.0346 0.9041 0.0912
-0.500 0.1830 0.01326 0.00499 -0.0364 0.8903 0.0919
-0.250 0.2235 0.01276 0.00443 -0.0389 0.8718 0.0927
0.000 0.2611 0.01235 0.00398 -0.0407 0.8447 0.0940
0.250 0.2972 0.01203 0.00359 -0.0423 0.8094 0.0956
0.500 0.3312 0.01184 0.00326 -0.0433 0.7672 0.0968
0.750 0.3596 0.01179 0.00304 -0.0432 0.7286 0.0981
1.000 0.3852 0.01178 0.00293 -0.0426 0.6977 0.0991
1.500 0.4332 0.01174 0.00279 -0.0408 0.6397 0.1011
1.750 0.4559 0.01176 0.00275 -0.0397 0.6074 0.1023
2.000 0.4783 0.01184 0.00275 -0.0385 0.5757 0.1040
2.250 0.5005 0.01196 0.00282 -0.0373 0.5447 0.1064
2.500 0.5230 0.01209 0.00290 -0.0362 0.5154 0.1092
2.750 0.5456 0.01224 0.00300 -0.0352 0.4845 0.1112
3.000 0.5649 0.01259 0.00310 -0.0335 0.4146 0.1124
3.250 0.5799 0.01333 0.00332 -0.0312 0.3097 0.1133
3.500 0.5985 0.01391 0.00355 -0.0297 0.2352 0.1157
3.750 0.6164 0.01465 0.00382 -0.0281 0.1585 0.1182
4.250 0.6529 0.01630 0.00482 -0.0248 0.0167 0.1285
4.750 0.8313 0.01832 0.00949 -0.0531 0.0092 1.0000
5.000 0.8507 0.01908 0.01033 -0.0514 0.0087 1.0000
5.250 0.8678 0.02013 0.01148 -0.0494 0.0085 1.0000
5.500 0.8848 0.02131 0.01270 -0.0473 0.0083 1.0000
5.750 0.9022 0.02266 0.01410 -0.0453 0.0083 1.0000
6.000 0.9207 0.02419 0.01569 -0.0434 0.0083 1.0000
6.250 0.9403 0.02595 0.01752 -0.0418 0.0085 1.0000
6.500 0.9602 0.02767 0.01940 -0.0401 0.0083 1.0000
6.750 0.9791 0.02933 0.02127 -0.0383 0.0081 1.0000
7.000 0.9967 0.03053 0.02277 -0.0363 0.0072 1.0000
7.250 1.0127 0.03223 0.02468 -0.0344 0.0067 1.0000
7.500 1.0266 0.03456 0.02735 -0.0318 0.0069 1.0000
7.750 1.0370 0.03736 0.03053 -0.0289 0.0074 1.0000
8.000 1.0429 0.04075 0.03428 -0.0256 0.0080 1.0000
8.250 1.0606 0.04201 0.03599 -0.0225 0.0125 1.0000
8.500 1.0633 0.04485 0.03917 -0.0190 0.0127 1.0000
8.750 1.0626 0.04766 0.04231 -0.0154 0.0128 1.0000
9.000 1.0585 0.05043 0.04536 -0.0117 0.0127 1.0000
9.250 1.0492 0.05343 0.04862 -0.0077 0.0125 1.0000
9.500 1.0375 0.05594 0.05134 -0.0035 0.0126 1.0000
9.750 1.0195 0.05844 0.05402 0.0010 0.0125 1.0000
10.000 1.0008 0.06146 0.05721 0.0040 0.0124 1.0000
10.250 0.9834 0.06493 0.06086 0.0052 0.0125 1.0000
10.500 0.9642 0.06934 0.06543 0.0047 0.0125 1.0000
10.750 0.9474 0.07434 0.07059 0.0025 0.0128 1.0000
11.000 0.9277 0.08100 0.07739 -0.0017 0.0130 1.0000
11.250 0.9089 0.08888 0.08539 -0.0073 0.0132 1.0000
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Polar data table (+)
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