Coanda 2 (coanda2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 100,000 Max Cl/Cd: 47.95 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda2-il-100000-n5.txt Download as CSV file: xf-coanda2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 2
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 -0.4279 0.09123 0.08653 -0.0183 1.0000 0.0211
-8.250 -0.4330 0.08797 0.08336 -0.0190 1.0000 0.0203
-8.000 -0.4419 0.08425 0.07974 -0.0195 1.0000 0.0196
-7.750 -0.4429 0.08019 0.07575 -0.0213 1.0000 0.0188
-7.250 -0.4386 0.07294 0.06853 -0.0235 1.0000 0.0181
-7.000 -0.4356 0.06919 0.06480 -0.0246 1.0000 0.0179
-6.750 -0.4320 0.06494 0.06055 -0.0258 1.0000 0.0178
-6.500 -0.4267 0.06059 0.05616 -0.0269 1.0000 0.0176
-6.250 -0.4198 0.05618 0.05168 -0.0277 1.0000 0.0175
-6.000 -0.4122 0.05118 0.04654 -0.0284 1.0000 0.0173
-5.750 -0.4040 0.04577 0.04089 -0.0286 1.0000 0.0172
-5.500 -0.3952 0.04018 0.03497 -0.0280 1.0000 0.0170
-5.250 -0.3862 0.03434 0.02869 -0.0266 1.0000 0.0169
-5.000 -0.3750 0.02935 0.02301 -0.0243 1.0000 0.0169
-4.750 -0.3600 0.02617 0.01923 -0.0221 1.0000 0.0173
-4.500 -0.3422 0.02410 0.01666 -0.0201 1.0000 0.0182
-4.250 -0.3237 0.02240 0.01459 -0.0182 1.0000 0.0205
-4.000 -0.3030 0.02135 0.01324 -0.0165 1.0000 0.0226
-3.750 -0.2812 0.02054 0.01220 -0.0150 1.0000 0.0253
-3.500 -0.2616 0.02205 0.01433 -0.0136 1.0000 0.0407
-3.250 -0.2366 0.02106 0.01243 -0.0120 1.0000 0.0702
-3.000 -0.2071 0.02255 0.01389 -0.0128 0.9962 0.0866
-2.750 -0.1639 0.02292 0.01416 -0.0167 0.9872 0.1020
-2.500 -0.1244 0.02243 0.01331 -0.0191 0.9790 0.1074
-2.250 -0.0889 0.02179 0.01236 -0.0206 0.9716 0.1088
-2.000 -0.0521 0.02114 0.01145 -0.0224 0.9653 0.1094
-1.750 -0.0179 0.02045 0.01055 -0.0236 0.9576 0.1094
-1.500 0.0173 0.01984 0.00979 -0.0251 0.9499 0.1096
-1.250 0.0548 0.01927 0.00908 -0.0269 0.9422 0.1103
-1.000 0.0887 0.01870 0.00843 -0.0280 0.9328 0.1109
-0.750 0.1272 0.01800 0.00775 -0.0301 0.9247 0.1121
-0.500 0.1636 0.01743 0.00721 -0.0317 0.9147 0.1134
-0.250 0.1982 0.01693 0.00675 -0.0329 0.9031 0.1147
0.000 0.2339 0.01647 0.00637 -0.0343 0.8906 0.1177
0.250 0.2697 0.01608 0.00603 -0.0357 0.8760 0.1216
0.500 0.3060 0.01569 0.00568 -0.0371 0.8588 0.1235
0.750 0.3406 0.01536 0.00538 -0.0381 0.8363 0.1243
1.000 0.3810 0.01497 0.00506 -0.0404 0.8087 0.1258
1.250 0.4234 0.01465 0.00473 -0.0430 0.7715 0.1281
1.500 0.4658 0.01445 0.00442 -0.0455 0.7193 0.1311
1.750 0.5036 0.01447 0.00424 -0.0470 0.6619 0.1350
2.000 0.5348 0.01466 0.00424 -0.0474 0.6144 0.1394
2.250 0.5632 0.01487 0.00438 -0.0475 0.5745 0.1470
2.500 0.5915 0.01502 0.00462 -0.0475 0.5396 0.1723
3.000 0.7140 0.01489 0.00535 -0.0635 0.3660 1.0000
3.250 0.7342 0.01553 0.00561 -0.0621 0.2887 1.0000
3.500 0.7557 0.01617 0.00596 -0.0609 0.2290 1.0000
3.750 0.7752 0.01717 0.00649 -0.0596 0.1474 1.0000
4.250 0.8126 0.01963 0.00827 -0.0565 0.0220 1.0000
4.500 0.8339 0.02048 0.00936 -0.0551 0.0193 1.0000
4.750 0.8542 0.02151 0.01063 -0.0535 0.0172 1.0000
5.000 0.8739 0.02260 0.01199 -0.0518 0.0165 1.0000
5.250 0.8920 0.02379 0.01343 -0.0500 0.0162 1.0000
5.500 0.9091 0.02502 0.01484 -0.0480 0.0160 1.0000
5.750 0.9251 0.02634 0.01633 -0.0459 0.0158 1.0000
6.000 0.9417 0.02761 0.01775 -0.0439 0.0151 1.0000
6.250 0.9582 0.02904 0.01938 -0.0420 0.0144 1.0000
6.500 0.9751 0.03071 0.02117 -0.0400 0.0138 1.0000
6.750 0.9933 0.03259 0.02318 -0.0383 0.0139 1.0000
7.000 1.0122 0.03469 0.02546 -0.0367 0.0140 1.0000
7.250 1.0304 0.03699 0.02800 -0.0350 0.0142 1.0000
7.500 1.0468 0.03949 0.03078 -0.0332 0.0145 1.0000
7.750 1.0605 0.04238 0.03400 -0.0311 0.0148 1.0000
8.000 1.0704 0.04569 0.03766 -0.0288 0.0152 1.0000
8.250 1.0772 0.04958 0.04184 -0.0265 0.0158 1.0000
8.500 1.0931 0.05139 0.04387 -0.0247 0.0170 1.0000
8.750 1.0985 0.05321 0.04617 -0.0216 0.0182 1.0000
9.000 1.0914 0.05665 0.05019 -0.0176 0.0196 1.0000
9.250 1.0840 0.06000 0.05387 -0.0146 0.0203 1.0000
9.500 1.0688 0.06347 0.05760 -0.0109 0.0212 1.0000
9.750 1.0531 0.06681 0.06115 -0.0084 0.0215 1.0000
10.000 1.0359 0.07059 0.06512 -0.0073 0.0217 1.0000
10.250 1.0176 0.07503 0.06975 -0.0078 0.0218 1.0000
10.500 0.9987 0.08030 0.07520 -0.0103 0.0216 1.0000
10.750 0.9783 0.08699 0.08205 -0.0148 0.0214 1.0000
11.000 0.9586 0.09479 0.08998 -0.0207 0.0209 1.0000
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Polar data table (+)
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