Coanda 2 (coanda2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 50,000 Max Cl/Cd: 37.05 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda2-il-50000-n5.txt Download as CSV file: xf-coanda2-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4231 0.09627 0.08955 -0.0184 1.0000 0.0387
-8.250 -0.4259 0.09323 0.08661 -0.0190 1.0000 0.0378
-8.000 -0.4309 0.08996 0.08345 -0.0196 1.0000 0.0370
-7.750 -0.4356 0.08577 0.07940 -0.0229 1.0000 0.0355
-7.500 -0.4329 0.08230 0.07592 -0.0236 1.0000 0.0353
-7.250 -0.4296 0.07871 0.07238 -0.0245 1.0000 0.0351
-7.000 -0.4253 0.07506 0.06876 -0.0255 1.0000 0.0349
-6.750 -0.4204 0.07111 0.06481 -0.0266 1.0000 0.0347
-6.500 -0.4140 0.06714 0.06082 -0.0277 1.0000 0.0346
-6.250 -0.4063 0.06304 0.05668 -0.0286 1.0000 0.0346
-6.000 -0.3974 0.05875 0.05229 -0.0294 1.0000 0.0346
-5.750 -0.3872 0.05442 0.04783 -0.0298 1.0000 0.0348
-5.500 -0.3760 0.04975 0.04294 -0.0301 1.0000 0.0354
-5.250 -0.3618 0.04813 0.04125 -0.0290 1.0000 0.0387
-5.000 -0.3478 0.04451 0.03736 -0.0283 1.0000 0.0412
-4.750 -0.3335 0.04006 0.03250 -0.0274 1.0000 0.0435
-4.500 -0.3174 0.03789 0.03012 -0.0259 1.0000 0.0470
-4.250 -0.3002 0.03464 0.02639 -0.0242 1.0000 0.0534
-4.000 -0.2808 0.03182 0.02285 -0.0223 1.0000 0.0703
-3.750 -0.2629 0.03124 0.02169 -0.0203 1.0000 0.0962
-3.500 -0.2487 0.03138 0.02192 -0.0189 1.0000 0.1294
-3.250 -0.2294 0.03031 0.02038 -0.0174 1.0000 0.1401
-3.000 -0.2085 0.02917 0.01890 -0.0161 1.0000 0.1419
-2.750 -0.1874 0.02825 0.01767 -0.0149 1.0000 0.1448
-2.500 -0.1651 0.02734 0.01638 -0.0138 1.0000 0.1450
-2.250 -0.1422 0.02653 0.01525 -0.0129 1.0000 0.1442
-2.000 -0.1187 0.02581 0.01423 -0.0121 1.0000 0.1437
-1.750 -0.0948 0.02518 0.01334 -0.0114 1.0000 0.1434
-1.500 -0.0710 0.02465 0.01255 -0.0108 1.0000 0.1434
-1.250 -0.0462 0.02417 0.01190 -0.0104 1.0000 0.1439
-1.000 -0.0188 0.02380 0.01134 -0.0105 1.0000 0.1447
-0.750 0.0110 0.02350 0.01087 -0.0112 0.9997 0.1457
-0.500 0.0625 0.02331 0.01048 -0.0164 0.9886 0.1505
-0.250 0.1130 0.02302 0.01019 -0.0214 0.9771 0.1565
0.000 0.1604 0.02272 0.00986 -0.0256 0.9633 0.1597
0.250 0.2063 0.02243 0.00958 -0.0294 0.9479 0.1621
0.500 0.2520 0.02213 0.00932 -0.0331 0.9314 0.1651
0.750 0.2989 0.02177 0.00906 -0.0368 0.9143 0.1693
1.000 0.3422 0.02138 0.00882 -0.0397 0.8942 0.1757
1.250 0.3878 0.02093 0.00859 -0.0429 0.8731 0.1861
1.500 0.4308 0.02045 0.00841 -0.0455 0.8475 0.2080
1.750 0.5239 0.01836 0.00834 -0.0589 0.8183 1.0000
2.000 0.5622 0.01820 0.00816 -0.0600 0.7772 1.0000
2.250 0.6014 0.01808 0.00796 -0.0611 0.7304 1.0000
2.500 0.6366 0.01813 0.00792 -0.0615 0.6815 1.0000
2.750 0.6666 0.01842 0.00802 -0.0611 0.6368 1.0000
3.000 0.6927 0.01886 0.00833 -0.0602 0.5981 1.0000
3.250 0.7168 0.01935 0.00883 -0.0591 0.5634 1.0000
3.500 0.7370 0.01989 0.00919 -0.0571 0.5157 1.0000
3.750 0.7492 0.02059 0.00933 -0.0537 0.4317 1.0000
4.000 0.7702 0.02117 0.00986 -0.0523 0.3928 1.0000
4.250 0.7900 0.02180 0.01040 -0.0507 0.3451 1.0000
4.500 0.8117 0.02238 0.01110 -0.0494 0.3062 1.0000
4.750 0.8312 0.02318 0.01169 -0.0480 0.2424 1.0000
5.000 0.8519 0.02412 0.01244 -0.0467 0.1806 1.0000
5.500 0.8870 0.02815 0.01548 -0.0443 0.0331 1.0000
5.750 0.9060 0.02962 0.01715 -0.0427 0.0306 1.0000
6.000 0.9238 0.03108 0.01888 -0.0411 0.0285 1.0000
6.250 0.9390 0.03274 0.02078 -0.0392 0.0264 1.0000
6.500 0.9508 0.03469 0.02307 -0.0370 0.0249 1.0000
6.750 0.9613 0.03670 0.02526 -0.0346 0.0242 1.0000
7.000 0.9730 0.03857 0.02738 -0.0322 0.0240 1.0000
7.250 0.9852 0.04053 0.02957 -0.0299 0.0239 1.0000
7.500 0.9988 0.04261 0.03187 -0.0278 0.0238 1.0000
7.750 1.0139 0.04491 0.03442 -0.0258 0.0238 1.0000
8.000 1.0298 0.04757 0.03736 -0.0241 0.0238 1.0000
8.250 1.0439 0.05036 0.04044 -0.0223 0.0238 1.0000
8.500 1.0542 0.05344 0.04388 -0.0204 0.0238 1.0000
8.750 1.0602 0.05658 0.04738 -0.0183 0.0237 1.0000
9.000 1.0607 0.05993 0.05111 -0.0160 0.0236 1.0000
9.250 1.0582 0.06325 0.05474 -0.0138 0.0237 1.0000
9.500 1.0470 0.06662 0.05842 -0.0111 0.0235 1.0000
9.750 1.0363 0.07016 0.06218 -0.0092 0.0237 1.0000
10.000 1.0223 0.07396 0.06622 -0.0083 0.0237 1.0000
10.250 1.0075 0.07834 0.07080 -0.0087 0.0237 1.0000
10.500 0.9941 0.08319 0.07581 -0.0101 0.0239 1.0000
10.750 0.9793 0.08876 0.08152 -0.0127 0.0240 1.0000
11.000 0.9665 0.09467 0.08754 -0.0158 0.0242 1.0000
11.250 0.9497 0.10193 0.09501 -0.0208 0.0246 1.0000
11.500 0.9233 0.11330 0.10661 -0.0295 0.0258 1.0000
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Polar data table (+)
Polar graphs
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