Coanda 1 (coanda1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 100,000 Max Cl/Cd: 54.27 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda1-il-100000.txt Download as CSV file: xf-coanda1-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4326 0.09271 0.08803 -0.0160 1.0000 0.0690
-7.500 -0.4327 0.08982 0.08519 -0.0155 1.0000 0.0699
-7.250 -0.4310 0.08681 0.08222 -0.0157 1.0000 0.0709
-7.000 -0.4288 0.08385 0.07931 -0.0162 1.0000 0.0718
-6.750 -0.4260 0.08076 0.07624 -0.0169 1.0000 0.0732
-6.500 -0.4218 0.07767 0.07318 -0.0178 1.0000 0.0744
-6.250 -0.4149 0.07501 0.07048 -0.0209 1.0000 0.0775
-6.000 -0.4044 0.07272 0.06804 -0.0245 1.0000 0.0785
-5.750 -0.3942 0.07049 0.06557 -0.0260 1.0000 0.0789
-5.500 -0.3904 0.06450 0.05977 -0.0236 1.0000 0.0800
-5.250 -0.3829 0.06084 0.05613 -0.0219 1.0000 0.0808
-5.000 -0.3735 0.05745 0.05269 -0.0208 1.0000 0.0817
-4.750 -0.3627 0.05415 0.04931 -0.0199 1.0000 0.0826
-4.500 -0.3507 0.05093 0.04597 -0.0189 1.0000 0.0834
-4.250 -0.3306 0.04559 0.04003 -0.0188 1.0000 0.0655
-4.000 -0.3216 0.04198 0.03643 -0.0167 1.0000 0.0624
-3.750 -0.3069 0.03540 0.02905 -0.0143 1.0000 0.0545
-3.500 -0.2925 0.03178 0.02501 -0.0118 1.0000 0.0547
-3.250 -0.2769 0.03112 0.02442 -0.0102 1.0000 0.0586
-3.000 -0.2590 0.02907 0.02190 -0.0079 1.0000 0.0679
-2.750 -0.2403 0.02722 0.01948 -0.0053 1.0000 0.0784
-2.500 -0.2240 0.02549 0.01731 -0.0028 1.0000 0.1049
-2.250 -0.2101 0.02476 0.01670 -0.0015 1.0000 0.1422
-2.000 -0.1945 0.02423 0.01611 -0.0001 1.0000 0.1701
-1.750 -0.1810 0.02358 0.01567 0.0013 1.0000 0.2066
-1.500 -0.1579 0.02275 0.01439 0.0026 1.0000 0.1948
-1.250 -0.1358 0.02239 0.01353 0.0040 1.0000 0.1851
-1.000 -0.1152 0.02160 0.01265 0.0050 1.0000 0.1823
-0.750 -0.0950 0.02110 0.01200 0.0061 1.0000 0.1792
-0.500 -0.0755 0.02078 0.01153 0.0072 1.0000 0.1774
-0.250 -0.0417 0.02061 0.01124 0.0054 0.9954 0.1789
0.000 0.0079 0.02042 0.01089 0.0006 0.9852 0.1775
0.250 0.0619 0.02015 0.01052 -0.0048 0.9728 0.1757
0.500 0.1195 0.01976 0.01013 -0.0108 0.9589 0.1750
0.750 0.1733 0.01925 0.00970 -0.0159 0.9455 0.1765
1.000 0.2263 0.01875 0.00930 -0.0209 0.9326 0.1796
1.250 0.2904 0.01802 0.00865 -0.0275 0.9178 0.1853
1.500 0.3549 0.01703 0.00785 -0.0341 0.9029 0.1977
1.750 0.4117 0.01625 0.00725 -0.0391 0.8884 0.2090
2.000 0.4569 0.01555 0.00689 -0.0419 0.8693 0.2498
2.250 0.6083 0.01345 0.00664 -0.0671 0.8499 1.0000
2.500 0.6454 0.01317 0.00634 -0.0679 0.8125 1.0000
2.750 0.6792 0.01302 0.00611 -0.0680 0.7694 1.0000
3.000 0.7062 0.01306 0.00591 -0.0664 0.6996 1.0000
3.250 0.7267 0.01339 0.00589 -0.0640 0.6266 1.0000
3.500 0.7435 0.01389 0.00594 -0.0611 0.5403 1.0000
3.750 0.7613 0.01444 0.00615 -0.0587 0.4649 1.0000
4.000 0.7777 0.01516 0.00640 -0.0563 0.3797 1.0000
4.250 0.7949 0.01597 0.00687 -0.0543 0.3157 1.0000
4.500 0.8152 0.01659 0.00741 -0.0528 0.2837 1.0000
4.750 0.8355 0.01718 0.00792 -0.0514 0.2462 1.0000
5.000 0.8570 0.01768 0.00844 -0.0500 0.2194 1.0000
5.250 0.8756 0.01850 0.00892 -0.0483 0.1581 1.0000
5.500 0.8887 0.02023 0.00986 -0.0459 0.0509 1.0000
5.750 0.9068 0.02141 0.01109 -0.0438 0.0433 1.0000
6.000 0.9256 0.02245 0.01242 -0.0417 0.0403 1.0000
6.250 0.9429 0.02358 0.01376 -0.0395 0.0389 1.0000
6.500 0.9586 0.02485 0.01522 -0.0371 0.0381 1.0000
6.750 0.9732 0.02632 0.01683 -0.0344 0.0378 1.0000
7.000 0.9891 0.02797 0.01859 -0.0320 0.0379 1.0000
7.250 1.0082 0.02999 0.02073 -0.0299 0.0384 1.0000
7.500 1.0294 0.03229 0.02320 -0.0283 0.0387 1.0000
7.750 1.0487 0.03467 0.02581 -0.0265 0.0378 1.0000
8.000 1.0656 0.03724 0.02865 -0.0246 0.0369 1.0000
8.250 1.0792 0.04053 0.03248 -0.0218 0.0386 1.0000
8.500 1.0867 0.04429 0.03677 -0.0186 0.0408 1.0000
8.750 1.0909 0.04836 0.04123 -0.0156 0.0427 1.0000
9.000 1.0961 0.05441 0.04749 -0.0136 0.0449 1.0000
9.250 1.0857 0.05592 0.04984 -0.0080 0.0483 1.0000
9.500 1.0652 0.06059 0.05501 -0.0036 0.0505 1.0000
9.750 1.0475 0.06470 0.05939 -0.0002 0.0520 1.0000
10.000 1.0250 0.06825 0.06310 0.0035 0.0528 1.0000
10.250 1.0017 0.07218 0.06717 0.0056 0.0534 1.0000
10.500 0.9765 0.07661 0.07175 0.0054 0.0532 1.0000
10.750 0.9471 0.08286 0.07813 0.0020 0.0524 1.0000
11.000 0.9223 0.09037 0.08571 -0.0038 0.0512 1.0000
11.250 0.8949 0.10166 0.09701 -0.0118 0.0509 1.0000
11.500 0.8760 0.11166 0.10694 -0.0171 0.0528 1.0000
11.750 0.8713 0.11723 0.11248 -0.0182 0.0553 1.0000
12.000 0.7335 0.11636 0.11184 -0.0109 0.0550 1.0000
12.250 0.7328 0.12068 0.11617 -0.0112 0.0577 1.0000
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Polar data table (+)
Polar graphs
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