Coanda 3 (coanda3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 200,000 Max Cl/Cd: 67.13 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda3-il-200000-n5.txt Download as CSV file: xf-coanda3-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4203 0.08911 0.08586 -0.0253 1.0000 0.0221
-8.250 -0.4281 0.08666 0.08347 -0.0245 1.0000 0.0225
-8.000 -0.4403 0.08456 0.08145 -0.0230 1.0000 0.0227
-7.750 -0.4501 0.08214 0.07908 -0.0219 1.0000 0.0228
-7.500 -0.4568 0.07922 0.07620 -0.0215 1.0000 0.0232
-7.250 -0.4616 0.07613 0.07314 -0.0215 1.0000 0.0236
-7.000 -0.4521 0.07165 0.06860 -0.0253 0.9980 0.0242
-6.750 -0.4306 0.06563 0.06249 -0.0322 0.9937 0.0247
-5.750 -0.3398 0.03445 0.03005 -0.0481 0.9751 0.0091
-5.500 -0.3205 0.02949 0.02448 -0.0484 0.9705 0.0087
-5.250 -0.2952 0.02574 0.02008 -0.0487 0.9677 0.0085
-5.000 -0.2747 0.02348 0.01733 -0.0473 0.9625 0.0086
-4.750 -0.2480 0.02163 0.01506 -0.0471 0.9590 0.0087
-4.500 -0.2191 0.01959 0.01257 -0.0473 0.9566 0.0103
-4.250 -0.1922 0.01819 0.01098 -0.0470 0.9531 0.0106
-4.000 -0.1671 0.01709 0.00971 -0.0462 0.9484 0.0108
-3.750 -0.1371 0.01616 0.00860 -0.0465 0.9452 0.0113
-3.500 -0.1042 0.01539 0.00763 -0.0473 0.9428 0.0120
-3.250 -0.0754 0.01482 0.00688 -0.0472 0.9388 0.0128
-3.000 -0.0475 0.01420 0.00608 -0.0470 0.9339 0.0159
-2.750 -0.0131 0.01367 0.00535 -0.0481 0.9304 0.0173
-2.500 0.0239 0.01302 0.00467 -0.0497 0.9278 0.0268
-2.250 0.0502 0.01282 0.00468 -0.0492 0.9196 0.0768
-2.000 0.0895 0.01288 0.00470 -0.0516 0.9157 0.0935
-1.750 0.1195 0.01290 0.00472 -0.0520 0.9087 0.1052
-1.500 0.1540 0.01262 0.00438 -0.0533 0.9029 0.1085
-1.250 0.1843 0.01239 0.00409 -0.0536 0.8954 0.1116
-1.000 0.2164 0.01204 0.00378 -0.0545 0.8882 0.1157
-0.750 0.2443 0.01182 0.00357 -0.0544 0.8781 0.1194
-0.500 0.2746 0.01160 0.00333 -0.0548 0.8679 0.1234
-0.250 0.3041 0.01138 0.00311 -0.0549 0.8547 0.1278
0.000 0.3322 0.01117 0.00293 -0.0548 0.8396 0.1344
0.250 0.3607 0.01100 0.00278 -0.0548 0.8240 0.1425
0.500 0.3914 0.01078 0.00259 -0.0553 0.8025 0.1574
0.750 0.4148 0.00982 0.00249 -0.0545 0.7754 0.4607
1.250 0.5961 0.00913 0.00270 -0.0818 0.6906 1.0000
1.750 0.6388 0.00955 0.00285 -0.0789 0.6213 1.0000
2.000 0.6585 0.00981 0.00296 -0.0771 0.5794 1.0000
2.250 0.6762 0.01016 0.00313 -0.0750 0.5238 1.0000
2.500 0.6916 0.01064 0.00331 -0.0725 0.4581 1.0000
2.750 0.7079 0.01113 0.00357 -0.0702 0.4073 1.0000
3.000 0.7252 0.01161 0.00387 -0.0682 0.3674 1.0000
3.250 0.7403 0.01226 0.00423 -0.0659 0.3132 1.0000
3.500 0.7578 0.01278 0.00454 -0.0640 0.2624 1.0000
3.750 0.7732 0.01351 0.00486 -0.0619 0.1859 1.0000
4.000 0.7785 0.01540 0.00574 -0.0582 0.0229 1.0000
4.250 0.7976 0.01602 0.00646 -0.0564 0.0167 1.0000
4.500 0.8175 0.01654 0.00715 -0.0548 0.0138 1.0000
4.750 0.8367 0.01717 0.00796 -0.0530 0.0123 1.0000
5.000 0.8549 0.01792 0.00889 -0.0510 0.0113 1.0000
5.250 0.8712 0.01882 0.00996 -0.0488 0.0104 1.0000
5.500 0.8777 0.02056 0.01181 -0.0451 0.0087 1.0000
5.750 0.8938 0.02142 0.01276 -0.0429 0.0083 1.0000
6.000 0.9082 0.02261 0.01400 -0.0405 0.0080 1.0000
6.250 0.9238 0.02391 0.01541 -0.0383 0.0078 1.0000
6.500 0.9413 0.02547 0.01705 -0.0364 0.0076 1.0000
6.750 0.9607 0.02713 0.01882 -0.0349 0.0076 1.0000
7.000 0.9805 0.02902 0.02087 -0.0334 0.0075 1.0000
7.250 0.9988 0.03080 0.02287 -0.0316 0.0071 1.0000
7.500 1.0153 0.03275 0.02506 -0.0297 0.0071 1.0000
7.750 1.0296 0.03418 0.02649 -0.0284 0.0056 1.0000
8.000 1.0427 0.03699 0.02950 -0.0265 0.0054 1.0000
8.500 1.0604 0.04125 0.03437 -0.0208 0.0056 1.0000
8.750 1.0633 0.04429 0.03769 -0.0177 0.0055 1.0000
9.000 1.0636 0.04613 0.03987 -0.0138 0.0056 1.0000
9.250 1.0511 0.04849 0.04272 -0.0080 0.0060 1.0000
9.500 1.0381 0.05117 0.04571 -0.0030 0.0063 1.0000
9.750 1.0251 0.05388 0.04866 0.0009 0.0063 1.0000
10.000 1.0093 0.05714 0.05218 0.0041 0.0067 1.0000
10.250 0.9936 0.06047 0.05572 0.0061 0.0067 1.0000
10.500 0.9765 0.06439 0.05985 0.0070 0.0069 1.0000
10.750 0.9605 0.06857 0.06420 0.0067 0.0069 1.0000
11.000 0.9424 0.07368 0.06949 0.0051 0.0070 1.0000
11.250 0.9243 0.07964 0.07560 0.0021 0.0070 1.0000
11.500 0.9078 0.08621 0.08232 -0.0021 0.0070 1.0000
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Polar data table (+)
Polar graphs
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