Coanda 1 (coanda1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 200,000 Max Cl/Cd: 60.94 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda1-il-200000.txt Download as CSV file: xf-coanda1-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3487 0.07964 0.07647 -0.0198 1.0000 0.0465
-7.750 -0.3491 0.07648 0.07335 -0.0195 1.0000 0.0475
-7.500 -0.4444 0.08629 0.08304 -0.0186 1.0000 0.0451
-7.250 -0.4393 0.08311 0.07988 -0.0169 1.0000 0.0460
-7.000 -0.4358 0.08029 0.07708 -0.0165 1.0000 0.0470
-6.750 -0.4325 0.07737 0.07418 -0.0166 1.0000 0.0482
-6.500 -0.4283 0.07442 0.07124 -0.0171 1.0000 0.0495
-6.250 -0.4229 0.07131 0.06812 -0.0180 1.0000 0.0515
-6.000 -0.4071 0.06890 0.06552 -0.0243 1.0000 0.0544
-5.750 -0.3970 0.06586 0.06233 -0.0248 1.0000 0.0546
-5.500 -0.3879 0.06238 0.05874 -0.0240 1.0000 0.0547
-5.250 -0.3786 0.05888 0.05514 -0.0228 1.0000 0.0547
-5.000 -0.3694 0.05513 0.05129 -0.0214 1.0000 0.0547
-4.750 -0.3768 0.04349 0.03958 -0.0190 1.0000 0.0346
-4.500 -0.3664 0.04052 0.03649 -0.0168 1.0000 0.0314
-4.250 -0.3566 0.03602 0.03173 -0.0145 1.0000 0.0292
-4.000 -0.3567 0.02275 0.01711 -0.0089 1.0000 0.0243
-3.750 -0.3397 0.01942 0.01310 -0.0063 1.0000 0.0242
-3.500 -0.3197 0.01729 0.01048 -0.0044 1.0000 0.0257
-3.250 -0.2988 0.01641 0.00941 -0.0029 1.0000 0.0298
-3.000 -0.2765 0.01538 0.00809 -0.0013 1.0000 0.0317
-2.750 -0.2547 0.01482 0.00739 0.0003 1.0000 0.0362
-2.500 -0.2343 0.01587 0.00873 0.0018 0.9997 0.0491
-2.250 -0.1878 0.01867 0.01149 -0.0023 0.9915 0.0824
-2.000 -0.1478 0.01923 0.01205 -0.0056 0.9848 0.0972
-1.750 -0.1117 0.01954 0.01243 -0.0085 0.9778 0.1252
-1.250 -0.0351 0.01884 0.01136 -0.0131 0.9647 0.1433
-1.000 0.0056 0.01753 0.00999 -0.0157 0.9590 0.1383
-0.750 0.0482 0.01693 0.00910 -0.0182 0.9513 0.1322
-0.500 0.0948 0.01650 0.00856 -0.0217 0.9440 0.1308
-0.250 0.1369 0.01552 0.00757 -0.0243 0.9342 0.1318
0.000 0.1848 0.01492 0.00694 -0.0279 0.9260 0.1306
0.250 0.2313 0.01407 0.00610 -0.0313 0.9172 0.1306
0.500 0.2746 0.01330 0.00538 -0.0340 0.9048 0.1308
1.000 0.3533 0.01201 0.00430 -0.0382 0.8757 0.1339
1.250 0.3879 0.01161 0.00397 -0.0393 0.8541 0.1356
1.500 0.4218 0.01129 0.00368 -0.0402 0.8282 0.1375
1.750 0.4533 0.01108 0.00347 -0.0406 0.7975 0.1406
2.000 0.4830 0.01099 0.00331 -0.0406 0.7654 0.1440
2.250 0.5092 0.01094 0.00323 -0.0399 0.7319 0.1473
2.500 0.5341 0.01102 0.00321 -0.0390 0.6980 0.1507
2.750 0.5559 0.01119 0.00321 -0.0374 0.6505 0.1558
3.000 0.5736 0.01147 0.00320 -0.0349 0.5789 0.1638
3.250 0.7215 0.01184 0.00407 -0.0630 0.3156 1.0000
3.500 0.7410 0.01246 0.00431 -0.0616 0.2530 1.0000
3.750 0.7622 0.01296 0.00459 -0.0603 0.2086 1.0000
4.250 0.8050 0.01396 0.00533 -0.0578 0.1394 1.0000
4.500 0.8199 0.01531 0.00601 -0.0557 0.0318 1.0000
4.750 0.8415 0.01588 0.00658 -0.0543 0.0265 1.0000
5.000 0.8633 0.01645 0.00729 -0.0528 0.0246 1.0000
5.250 0.8845 0.01710 0.00814 -0.0512 0.0242 1.0000
5.500 0.9048 0.01784 0.00908 -0.0495 0.0242 1.0000
5.750 0.9232 0.01877 0.01020 -0.0475 0.0243 1.0000
6.000 0.9393 0.01992 0.01153 -0.0451 0.0241 1.0000
6.250 0.9555 0.02111 0.01281 -0.0428 0.0235 1.0000
6.500 0.9718 0.02253 0.01431 -0.0405 0.0230 1.0000
6.750 0.9894 0.02443 0.01626 -0.0383 0.0239 1.0000
7.000 1.0103 0.02658 0.01847 -0.0367 0.0250 1.0000
7.250 1.0346 0.02752 0.01969 -0.0349 0.0280 1.0000
7.500 1.0562 0.03131 0.02385 -0.0330 0.0326 1.0000
7.750 1.0777 0.03418 0.02736 -0.0299 0.0409 1.0000
10.500 0.7594 0.09388 0.09083 -0.0079 0.0869 1.0000
10.750 0.7392 0.10160 0.09850 -0.0109 0.0870 1.0000
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Polar data table (+)
Polar graphs
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