Coanda 3 (coanda3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Coanda 3 (coanda3-il) Reynolds number: 50,000 Max Cl/Cd: 37.26 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda3-il-50000-n5.txt Download as CSV file: xf-coanda3-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 3
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4288 0.09361 0.08710 -0.0293 1.0000 0.0348
-8.250 -0.4327 0.09078 0.08436 -0.0287 1.0000 0.0344
-8.000 -0.4347 0.08779 0.08145 -0.0284 1.0000 0.0339
-7.750 -0.4367 0.08463 0.07837 -0.0286 1.0000 0.0336
-7.500 -0.4388 0.08124 0.07504 -0.0290 1.0000 0.0334
-7.250 -0.4397 0.07778 0.07162 -0.0293 1.0000 0.0331
-7.000 -0.4391 0.07432 0.06818 -0.0296 1.0000 0.0328
-6.750 -0.4375 0.07055 0.06441 -0.0300 1.0000 0.0327
-6.500 -0.4342 0.06676 0.06052 -0.0302 1.0000 0.0324
-6.250 -0.4293 0.06277 0.05646 -0.0305 1.0000 0.0322
-6.000 -0.4226 0.05865 0.05222 -0.0306 1.0000 0.0323
-5.750 -0.4141 0.05443 0.04783 -0.0306 1.0000 0.0321
-5.500 -0.4037 0.05032 0.04350 -0.0302 1.0000 0.0318
-5.250 -0.3919 0.04589 0.03877 -0.0297 1.0000 0.0318
-5.000 -0.3784 0.04139 0.03387 -0.0289 1.0000 0.0316
-4.750 -0.3630 0.03677 0.02869 -0.0278 1.0000 0.0313
-4.500 -0.3447 0.03244 0.02366 -0.0265 1.0000 0.0312
-4.250 -0.3238 0.02936 0.01993 -0.0251 1.0000 0.0317
-4.000 -0.3008 0.02708 0.01709 -0.0238 1.0000 0.0328
-3.750 -0.2760 0.02541 0.01493 -0.0228 1.0000 0.0349
-3.500 -0.2523 0.02465 0.01416 -0.0220 1.0000 0.0417
-3.250 -0.2290 0.02433 0.01380 -0.0211 1.0000 0.0525
-3.000 -0.2042 0.02411 0.01317 -0.0200 1.0000 0.0861
-2.750 -0.1839 0.02426 0.01298 -0.0186 1.0000 0.1088
-2.500 -0.1630 0.02429 0.01267 -0.0174 1.0000 0.1248
-2.250 -0.1406 0.02415 0.01235 -0.0167 1.0000 0.1337
-2.000 -0.1236 0.02432 0.01247 -0.0156 1.0000 0.1623
-1.750 -0.1004 0.02418 0.01208 -0.0151 1.0000 0.1707
-1.500 -0.0761 0.02396 0.01168 -0.0147 1.0000 0.1733
-1.250 -0.0442 0.02380 0.01132 -0.0159 0.9967 0.1766
-1.000 -0.0071 0.02373 0.01102 -0.0181 0.9904 0.1810
-0.750 0.0292 0.02365 0.01084 -0.0203 0.9839 0.1867
-0.500 0.0656 0.02363 0.01073 -0.0225 0.9772 0.1957
-0.250 0.1007 0.02356 0.01067 -0.0245 0.9695 0.2085
0.000 0.1364 0.02334 0.01070 -0.0267 0.9606 0.2450
0.250 0.2160 0.02146 0.01072 -0.0376 0.9570 1.0000
0.500 0.2646 0.02164 0.01065 -0.0417 0.9418 1.0000
0.750 0.3082 0.02163 0.01051 -0.0447 0.9236 1.0000
1.000 0.3489 0.02164 0.01044 -0.0471 0.9077 1.0000
1.250 0.3860 0.02168 0.01045 -0.0489 0.8940 1.0000
1.500 0.4220 0.02169 0.01050 -0.0504 0.8800 1.0000
1.750 0.4575 0.02163 0.01050 -0.0517 0.8649 1.0000
2.000 0.4933 0.02150 0.01046 -0.0528 0.8489 1.0000
2.250 0.5305 0.02127 0.01040 -0.0541 0.8318 1.0000
2.500 0.5583 0.02111 0.01038 -0.0534 0.8091 1.0000
2.750 0.5906 0.02079 0.01020 -0.0534 0.7840 1.0000
3.000 0.6247 0.02042 0.01004 -0.0534 0.7539 1.0000
3.250 0.6633 0.02002 0.00976 -0.0541 0.7178 1.0000
3.500 0.6969 0.01986 0.00970 -0.0540 0.6739 1.0000
3.750 0.7246 0.01997 0.00990 -0.0530 0.6227 1.0000
4.000 0.7495 0.02025 0.01016 -0.0516 0.5655 1.0000
4.250 0.7720 0.02072 0.01055 -0.0500 0.5107 1.0000
4.500 0.7930 0.02135 0.01109 -0.0483 0.4651 1.0000
4.750 0.8025 0.02233 0.01155 -0.0447 0.3904 1.0000
5.000 0.8155 0.02327 0.01225 -0.0420 0.3375 1.0000
5.250 0.8282 0.02416 0.01297 -0.0395 0.2843 1.0000
5.500 0.8431 0.02495 0.01369 -0.0373 0.2257 1.0000
5.750 0.8575 0.02609 0.01447 -0.0351 0.1448 1.0000
6.000 0.8681 0.02893 0.01621 -0.0333 0.0396 1.0000
6.250 0.8858 0.03046 0.01795 -0.0316 0.0341 1.0000
6.500 0.9001 0.03219 0.01998 -0.0295 0.0317 1.0000
6.750 0.9138 0.03368 0.02176 -0.0272 0.0304 1.0000
7.000 0.9249 0.03536 0.02372 -0.0247 0.0282 1.0000
7.250 0.9341 0.03719 0.02576 -0.0221 0.0264 1.0000
7.500 0.9413 0.03923 0.02796 -0.0195 0.0250 1.0000
7.750 0.9496 0.04155 0.03045 -0.0169 0.0242 1.0000
8.000 0.9634 0.04392 0.03299 -0.0149 0.0238 1.0000
8.250 0.9806 0.04635 0.03570 -0.0133 0.0236 1.0000
8.500 0.9968 0.04897 0.03863 -0.0118 0.0235 1.0000
8.750 1.0101 0.05198 0.04198 -0.0101 0.0235 1.0000
9.000 1.0184 0.05495 0.04528 -0.0081 0.0235 1.0000
9.250 1.0200 0.05799 0.04867 -0.0054 0.0235 1.0000
9.500 1.0161 0.06099 0.05200 -0.0025 0.0234 1.0000
9.750 1.0076 0.06397 0.05530 0.0003 0.0232 1.0000
10.000 0.9990 0.06733 0.05892 0.0024 0.0233 1.0000
10.250 0.9867 0.07087 0.06272 0.0040 0.0233 1.0000
10.500 0.9725 0.07476 0.06684 0.0046 0.0233 1.0000
10.750 0.9590 0.07901 0.07128 0.0045 0.0235 1.0000
11.000 0.9437 0.08386 0.07630 0.0033 0.0236 1.0000
11.250 0.9271 0.08930 0.08189 0.0010 0.0236 1.0000
11.500 0.9108 0.09529 0.08803 -0.0022 0.0236 1.0000
11.750 0.9006 0.10103 0.09393 -0.0054 0.0242 1.0000
12.000 0.8819 0.10928 0.10235 -0.0114 0.0247 1.0000
12.250 0.8581 0.12096 0.11417 -0.0194 0.0261 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Coanda 3 (coanda3-il)