Coanda 3 (coanda3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 50,000 Max Cl/Cd: 37.07 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda3-il-50000.txt Download as CSV file: xf-coanda3-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4252 0.10230 0.09560 -0.0209 1.0000 0.1490
-8.500 -0.4356 0.10053 0.09395 -0.0214 1.0000 0.1529
-8.250 -0.4553 0.09964 0.09323 -0.0223 1.0000 0.1543
-8.000 -0.4478 0.09502 0.08867 -0.0208 1.0000 0.1569
-7.750 -0.4425 0.09150 0.08519 -0.0193 1.0000 0.1618
-7.500 -0.4530 0.08958 0.08336 -0.0206 1.0000 0.1670
-7.250 -0.4565 0.08637 0.08024 -0.0209 1.0000 0.1700
-7.000 -0.4498 0.08274 0.07665 -0.0186 1.0000 0.1765
-6.750 -0.4601 0.08100 0.07493 -0.0215 1.0000 0.1827
-6.500 -0.4507 0.07687 0.07086 -0.0177 1.0000 0.1918
-6.250 -0.4498 0.07378 0.06781 -0.0170 1.0000 0.2010
-6.000 -0.4476 0.07087 0.06493 -0.0154 1.0000 0.2170
-4.500 -0.3611 0.04453 0.03680 -0.0229 1.0000 0.1114
-4.250 -0.3444 0.04086 0.03278 -0.0217 1.0000 0.1089
-4.000 -0.3259 0.03746 0.02887 -0.0203 1.0000 0.1090
-3.750 -0.3052 0.03419 0.02480 -0.0186 1.0000 0.1132
-3.500 -0.2853 0.03150 0.02169 -0.0170 1.0000 0.1255
-3.250 -0.2665 0.02901 0.01897 -0.0152 1.0000 0.1616
-3.000 -0.2492 0.02781 0.01763 -0.0136 1.0000 0.2026
-2.750 -0.2279 0.02694 0.01645 -0.0124 1.0000 0.2197
-2.500 -0.2081 0.02643 0.01575 -0.0113 1.0000 0.2396
-2.250 -0.1890 0.02596 0.01524 -0.0101 1.0000 0.2624
-2.000 -0.1655 0.02539 0.01437 -0.0095 1.0000 0.2669
-1.750 -0.1410 0.02483 0.01351 -0.0089 1.0000 0.2675
-1.500 -0.1136 0.02436 0.01282 -0.0089 1.0000 0.2695
-1.250 -0.0846 0.02399 0.01225 -0.0093 1.0000 0.2731
-1.000 -0.0571 0.02372 0.01178 -0.0094 1.0000 0.2786
-0.750 -0.0306 0.02338 0.01138 -0.0095 1.0000 0.2866
-0.500 -0.0068 0.02313 0.01116 -0.0092 1.0000 0.3017
-0.250 0.0158 0.02288 0.01102 -0.0087 1.0000 0.3232
0.000 0.0885 0.02057 0.01093 -0.0177 1.0000 1.0000
0.250 0.1079 0.02102 0.01088 -0.0164 1.0000 1.0000
0.500 0.1256 0.02147 0.01099 -0.0151 1.0000 1.0000
0.750 0.1426 0.02196 0.01126 -0.0139 1.0000 1.0000
1.000 0.1593 0.02249 0.01165 -0.0128 1.0000 1.0000
1.250 0.1757 0.02306 0.01211 -0.0118 1.0000 1.0000
1.500 0.1918 0.02369 0.01266 -0.0109 1.0000 1.0000
1.750 0.2076 0.02437 0.01331 -0.0101 1.0000 1.0000
2.000 0.2229 0.02512 0.01404 -0.0094 1.0000 1.0000
2.250 0.2840 0.02659 0.01556 -0.0178 0.9794 1.0000
2.500 0.3535 0.02772 0.01682 -0.0271 0.9500 1.0000
2.750 0.4279 0.02831 0.01767 -0.0363 0.9178 1.0000
3.000 0.4988 0.02812 0.01777 -0.0436 0.8801 1.0000
3.250 0.5770 0.02695 0.01707 -0.0505 0.8390 1.0000
3.500 0.6653 0.02458 0.01522 -0.0575 0.7943 1.0000
3.750 0.7345 0.02244 0.01349 -0.0605 0.7363 1.0000
4.000 0.7834 0.02169 0.01273 -0.0610 0.6663 1.0000
4.250 0.8134 0.02206 0.01298 -0.0596 0.6066 1.0000
4.500 0.8404 0.02267 0.01349 -0.0583 0.5597 1.0000
4.750 0.8546 0.02307 0.01369 -0.0545 0.5088 1.0000
5.000 0.8644 0.02346 0.01386 -0.0501 0.4569 1.0000
5.250 0.8846 0.02425 0.01462 -0.0482 0.4231 1.0000
5.500 0.8976 0.02490 0.01526 -0.0451 0.3859 1.0000
5.750 0.9073 0.02546 0.01583 -0.0414 0.3482 1.0000
6.000 0.9078 0.02590 0.01621 -0.0363 0.3003 1.0000
6.250 0.9061 0.02645 0.01666 -0.0311 0.2320 1.0000
6.500 0.9083 0.02849 0.01793 -0.0269 0.1290 1.0000
6.750 0.9214 0.03070 0.01980 -0.0243 0.0991 1.0000
7.000 0.9378 0.03272 0.02180 -0.0221 0.0879 1.0000
7.250 0.9584 0.03499 0.02406 -0.0205 0.0813 1.0000
7.500 0.9827 0.03730 0.02668 -0.0193 0.0745 1.0000
7.750 1.0075 0.04027 0.02967 -0.0187 0.0695 1.0000
8.000 1.0311 0.04345 0.03333 -0.0175 0.0681 1.0000
8.250 1.0486 0.04710 0.03745 -0.0158 0.0679 1.0000
8.500 1.0594 0.05095 0.04176 -0.0135 0.0682 1.0000
8.750 1.0654 0.05498 0.04621 -0.0110 0.0690 1.0000
9.000 1.0671 0.05926 0.05084 -0.0083 0.0697 1.0000
9.250 1.0690 0.06385 0.05568 -0.0061 0.0705 1.0000
9.500 1.0532 0.06708 0.05946 -0.0021 0.0717 1.0000
9.750 1.0228 0.07069 0.06348 0.0022 0.0730 1.0000
10.000 0.9914 0.07484 0.06787 0.0051 0.0738 1.0000
10.250 0.9615 0.07958 0.07279 0.0057 0.0747 1.0000
10.500 0.9302 0.08565 0.07898 0.0038 0.0757 1.0000
10.750 0.8995 0.09337 0.08675 -0.0007 0.0770 1.0000
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Polar data table (+)
Polar graphs
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