(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 200,000 Max Cl/Cd: 56.92 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e171-il-200000.txt Download as CSV file: xf-e171-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6716 0.11236 0.10883 -0.0066 1.0000 0.0351
-12.500 -0.6810 0.10563 0.10214 -0.0092 1.0000 0.0330
-11.750 -0.8152 0.06753 0.06337 -0.0347 1.0000 0.0264
-11.500 -0.8337 0.06221 0.05793 -0.0361 1.0000 0.0258
-11.250 -0.8546 0.05790 0.05343 -0.0364 1.0000 0.0257
-11.000 -0.8701 0.05409 0.04947 -0.0357 1.0000 0.0251
-10.750 -0.8878 0.05067 0.04582 -0.0336 1.0000 0.0250
-10.500 -0.9019 0.04752 0.04244 -0.0305 1.0000 0.0246
-10.250 -0.9103 0.04415 0.03878 -0.0276 1.0000 0.0242
-10.000 -0.9130 0.04076 0.03504 -0.0250 1.0000 0.0241
-9.750 -0.9097 0.03764 0.03157 -0.0226 1.0000 0.0239
-9.500 -0.9015 0.03479 0.02836 -0.0205 1.0000 0.0241
-9.250 -0.8889 0.03302 0.02631 -0.0187 1.0000 0.0255
-9.000 -0.8741 0.03156 0.02452 -0.0170 1.0000 0.0265
-8.750 -0.8575 0.02873 0.02140 -0.0156 1.0000 0.0274
-8.500 -0.8375 0.02597 0.01853 -0.0147 1.0000 0.0287
-8.250 -0.8186 0.02442 0.01695 -0.0135 1.0000 0.0304
-8.000 -0.8001 0.02313 0.01558 -0.0121 1.0000 0.0328
-7.750 -0.7806 0.02236 0.01467 -0.0107 1.0000 0.0360
-7.500 -0.7677 0.02051 0.01288 -0.0086 1.0000 0.0398
-7.250 -0.7516 0.01952 0.01184 -0.0068 1.0000 0.0443
-7.000 -0.7383 0.01836 0.01068 -0.0045 1.0000 0.0506
-6.750 -0.7226 0.01750 0.00978 -0.0025 1.0000 0.0593
-6.500 -0.7119 0.01626 0.00869 0.0002 1.0000 0.0762
-6.250 -0.7015 0.01500 0.00771 0.0029 1.0000 0.1165
-6.000 -0.6905 0.01390 0.00699 0.0053 1.0000 0.1777
-5.750 -0.6796 0.01296 0.00643 0.0077 1.0000 0.2465
-5.500 -0.6700 0.01218 0.00599 0.0104 1.0000 0.3178
-5.250 -0.6621 0.01163 0.00580 0.0135 1.0000 0.3879
-5.000 -0.6302 0.01130 0.00578 0.0120 0.9934 0.4737
-4.750 -0.5875 0.01127 0.00582 0.0088 0.9837 0.5278
-4.500 -0.5462 0.01127 0.00576 0.0060 0.9730 0.5581
-4.250 -0.5052 0.01128 0.00570 0.0034 0.9627 0.5823
-4.000 -0.4635 0.01129 0.00567 0.0007 0.9536 0.6034
-3.750 -0.4244 0.01127 0.00556 -0.0014 0.9425 0.6206
-3.500 -0.3877 0.01124 0.00547 -0.0030 0.9298 0.6352
-3.250 -0.3530 0.01121 0.00540 -0.0041 0.9166 0.6480
-3.000 -0.3210 0.01118 0.00531 -0.0047 0.9026 0.6595
-2.750 -0.2918 0.01117 0.00523 -0.0047 0.8883 0.6705
-2.500 -0.2647 0.01118 0.00514 -0.0043 0.8743 0.6817
-2.250 -0.2379 0.01118 0.00511 -0.0038 0.8612 0.6913
-2.000 -0.2114 0.01118 0.00505 -0.0033 0.8490 0.7003
-1.750 -0.1854 0.01119 0.00496 -0.0027 0.8377 0.7102
-1.500 -0.1588 0.01119 0.00495 -0.0022 0.8268 0.7187
-1.250 -0.1327 0.01118 0.00490 -0.0018 0.8158 0.7276
-1.000 -0.1065 0.01119 0.00486 -0.0014 0.8061 0.7370
-0.750 -0.0796 0.01119 0.00484 -0.0010 0.7972 0.7447
-0.500 -0.0534 0.01118 0.00481 -0.0007 0.7873 0.7538
-0.250 -0.0266 0.01118 0.00481 -0.0003 0.7790 0.7615
0.000 0.0000 0.01117 0.00478 0.0000 0.7702 0.7702
0.250 0.0266 0.01118 0.00481 0.0003 0.7615 0.7789
0.500 0.0534 0.01118 0.00481 0.0007 0.7538 0.7873
0.750 0.0796 0.01119 0.00484 0.0010 0.7447 0.7972
1.000 0.1064 0.01119 0.00486 0.0014 0.7370 0.8061
1.250 0.1327 0.01118 0.00490 0.0018 0.7276 0.8158
1.500 0.1588 0.01119 0.00495 0.0022 0.7187 0.8268
1.750 0.1853 0.01119 0.00496 0.0027 0.7103 0.8377
2.000 0.2114 0.01118 0.00505 0.0033 0.7003 0.8490
2.250 0.2378 0.01118 0.00511 0.0038 0.6913 0.8612
2.500 0.2646 0.01118 0.00514 0.0043 0.6817 0.8743
2.750 0.2918 0.01117 0.00523 0.0047 0.6705 0.8884
3.000 0.3209 0.01118 0.00531 0.0047 0.6595 0.9026
3.250 0.3530 0.01121 0.00540 0.0041 0.6480 0.9165
3.500 0.3877 0.01124 0.00547 0.0030 0.6351 0.9298
3.750 0.4244 0.01127 0.00556 0.0014 0.6206 0.9425
4.000 0.4635 0.01129 0.00567 -0.0007 0.6034 0.9536
4.250 0.5052 0.01128 0.00571 -0.0034 0.5824 0.9627
4.500 0.5462 0.01127 0.00576 -0.0060 0.5581 0.9730
4.750 0.5876 0.01127 0.00582 -0.0088 0.5280 0.9837
5.000 0.6303 0.01130 0.00578 -0.0120 0.4738 0.9934
5.250 0.6620 0.01163 0.00580 -0.0135 0.3888 1.0000
5.500 0.6699 0.01217 0.00599 -0.0104 0.3183 1.0000
5.750 0.6795 0.01296 0.00643 -0.0077 0.2469 1.0000
6.000 0.6905 0.01390 0.00699 -0.0053 0.1781 1.0000
6.250 0.7015 0.01499 0.00771 -0.0029 0.1167 1.0000
6.500 0.7119 0.01626 0.00867 -0.0002 0.0760 1.0000
6.750 0.7224 0.01752 0.00980 0.0025 0.0591 1.0000
7.000 0.7383 0.01836 0.01067 0.0045 0.0504 1.0000
7.250 0.7517 0.01951 0.01183 0.0068 0.0443 1.0000
7.500 0.7677 0.02052 0.01289 0.0086 0.0399 1.0000
7.750 0.7807 0.02235 0.01467 0.0107 0.0359 1.0000
8.000 0.8001 0.02313 0.01558 0.0121 0.0328 1.0000
8.250 0.8189 0.02443 0.01696 0.0135 0.0306 1.0000
8.500 0.8376 0.02596 0.01852 0.0147 0.0287 1.0000
8.750 0.8576 0.02872 0.02138 0.0156 0.0274 1.0000
9.000 0.8744 0.03168 0.02464 0.0169 0.0266 1.0000
9.250 0.8890 0.03292 0.02620 0.0187 0.0254 1.0000
9.500 0.9016 0.03479 0.02836 0.0205 0.0241 1.0000
9.750 0.9100 0.03764 0.03156 0.0226 0.0240 1.0000
10.000 0.9132 0.04072 0.03500 0.0250 0.0239 1.0000
10.250 0.9111 0.04408 0.03869 0.0275 0.0242 1.0000
10.500 0.9014 0.04753 0.04246 0.0306 0.0244 1.0000
10.750 0.8878 0.05071 0.04587 0.0336 0.0249 1.0000
11.000 0.8704 0.05416 0.04954 0.0357 0.0252 1.0000
11.250 0.8526 0.05796 0.05353 0.0364 0.0255 1.0000
11.500 0.8349 0.06228 0.05799 0.0360 0.0259 1.0000
11.750 0.8136 0.06744 0.06331 0.0345 0.0262 1.0000
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Polar data table (+)
Polar graphs
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