Coanda 3 (coanda3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Coanda 3 (coanda3-il) Reynolds number: 100,000 Max Cl/Cd: 55.48 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda3-il-100000.txt Download as CSV file: xf-coanda3-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4251 0.09479 0.09009 -0.0243 1.0000 0.0838
-8.250 -0.4374 0.09290 0.08831 -0.0246 1.0000 0.0848
-8.000 -0.4508 0.09116 0.08665 -0.0261 1.0000 0.0856
-7.750 -0.3794 0.07554 0.07142 -0.0249 1.0000 0.0888
-7.500 -0.3828 0.07253 0.06846 -0.0228 1.0000 0.0903
-7.250 -0.3902 0.06964 0.06562 -0.0217 1.0000 0.0912
-7.000 -0.4549 0.07729 0.07293 -0.0242 1.0000 0.0890
-6.750 -0.4521 0.07432 0.06998 -0.0228 1.0000 0.0905
-6.500 -0.4498 0.07112 0.06678 -0.0223 1.0000 0.0919
-6.250 -0.4460 0.06794 0.06356 -0.0222 1.0000 0.0934
-6.000 -0.4407 0.06443 0.05999 -0.0223 1.0000 0.0945
-5.750 -0.4335 0.06079 0.05626 -0.0224 1.0000 0.0950
-5.500 -0.4222 0.04975 0.04446 -0.0264 1.0000 0.0612
-5.250 -0.4125 0.04692 0.04169 -0.0244 1.0000 0.0579
-5.000 -0.4020 0.03769 0.03162 -0.0233 1.0000 0.0491
-4.750 -0.3888 0.03410 0.02773 -0.0216 1.0000 0.0480
-4.500 -0.3735 0.03005 0.02317 -0.0196 1.0000 0.0469
-4.250 -0.3549 0.02576 0.01814 -0.0176 1.0000 0.0463
-4.000 -0.3329 0.02265 0.01438 -0.0159 1.0000 0.0470
-3.750 -0.3100 0.02063 0.01191 -0.0143 1.0000 0.0492
-3.500 -0.2889 0.02004 0.01133 -0.0129 1.0000 0.0537
-3.250 -0.2679 0.02003 0.01123 -0.0113 1.0000 0.0680
-3.000 -0.2480 0.02019 0.01125 -0.0096 1.0000 0.0936
-2.750 -0.2292 0.02058 0.01131 -0.0080 1.0000 0.1135
-2.500 -0.2103 0.02054 0.01122 -0.0067 1.0000 0.1235
-2.250 -0.1910 0.02049 0.01101 -0.0055 1.0000 0.1306
-2.000 -0.1736 0.02066 0.01115 -0.0042 1.0000 0.1442
-1.750 -0.1559 0.02074 0.01115 -0.0031 1.0000 0.1571
-1.500 -0.1365 0.02055 0.01091 -0.0020 1.0000 0.1613
-1.250 -0.1181 0.02050 0.01082 -0.0010 1.0000 0.1718
-1.000 -0.0999 0.02048 0.01077 0.0000 1.0000 0.1839
-0.750 -0.0666 0.02039 0.01068 -0.0017 0.9959 0.1877
-0.500 -0.0145 0.02045 0.01067 -0.0068 0.9849 0.1927
-0.250 0.0363 0.02032 0.01060 -0.0116 0.9730 0.1995
0.000 0.0857 0.02017 0.01050 -0.0160 0.9608 0.2105
0.250 0.1336 0.01997 0.01043 -0.0202 0.9505 0.2308
0.500 0.2532 0.01795 0.01053 -0.0393 0.9550 1.0000
0.750 0.2991 0.01808 0.01050 -0.0430 0.9440 1.0000
1.000 0.3425 0.01810 0.01045 -0.0461 0.9320 1.0000
1.250 0.3876 0.01802 0.01036 -0.0494 0.9195 1.0000
1.500 0.4375 0.01771 0.01009 -0.0534 0.9061 1.0000
1.750 0.4927 0.01710 0.00958 -0.0579 0.8917 1.0000
2.000 0.5478 0.01637 0.00897 -0.0622 0.8774 1.0000
2.250 0.5976 0.01562 0.00835 -0.0654 0.8615 1.0000
2.500 0.6309 0.01511 0.00801 -0.0654 0.8382 1.0000
2.750 0.6667 0.01452 0.00755 -0.0657 0.8103 1.0000
3.000 0.7030 0.01398 0.00709 -0.0659 0.7714 1.0000
3.250 0.7420 0.01362 0.00666 -0.0666 0.7127 1.0000
3.500 0.7679 0.01384 0.00667 -0.0650 0.6334 1.0000
3.750 0.7830 0.01439 0.00675 -0.0617 0.5379 1.0000
4.000 0.7945 0.01516 0.00695 -0.0581 0.4536 1.0000
4.250 0.8098 0.01591 0.00739 -0.0556 0.4028 1.0000
4.500 0.8270 0.01659 0.00791 -0.0535 0.3671 1.0000
4.750 0.8414 0.01722 0.00837 -0.0510 0.3194 1.0000
5.000 0.8583 0.01773 0.00888 -0.0489 0.2810 1.0000
5.250 0.8755 0.01822 0.00929 -0.0467 0.2292 1.0000
5.500 0.8881 0.01941 0.00983 -0.0440 0.1172 1.0000
5.750 0.8983 0.02133 0.01112 -0.0410 0.0537 1.0000
6.000 0.9133 0.02261 0.01241 -0.0386 0.0457 1.0000
6.250 0.9286 0.02372 0.01372 -0.0360 0.0429 1.0000
6.500 0.9416 0.02496 0.01514 -0.0332 0.0411 1.0000
6.750 0.9535 0.02634 0.01665 -0.0302 0.0400 1.0000
7.000 0.9669 0.02785 0.01825 -0.0276 0.0395 1.0000
7.250 0.9848 0.02969 0.02024 -0.0256 0.0393 1.0000
7.500 1.0092 0.03201 0.02271 -0.0245 0.0396 1.0000
7.750 1.0323 0.03459 0.02544 -0.0236 0.0386 1.0000
8.000 1.0535 0.03750 0.02856 -0.0224 0.0378 1.0000
8.250 1.0705 0.04045 0.03185 -0.0206 0.0377 1.0000
8.500 1.0811 0.04335 0.03539 -0.0172 0.0399 1.0000
8.750 1.0834 0.04711 0.03977 -0.0134 0.0424 1.0000
9.000 1.0837 0.05125 0.04431 -0.0100 0.0446 1.0000
9.250 1.0849 0.05631 0.04959 -0.0076 0.0465 1.0000
9.500 1.0755 0.05860 0.05247 -0.0026 0.0497 1.0000
9.750 1.0485 0.06226 0.05658 0.0027 0.0515 1.0000
10.000 1.0219 0.06612 0.06070 0.0069 0.0528 1.0000
10.250 0.9995 0.06996 0.06473 0.0091 0.0536 1.0000
10.500 0.9752 0.07436 0.06930 0.0098 0.0540 1.0000
10.750 0.9498 0.07946 0.07454 0.0085 0.0539 1.0000
11.000 0.9220 0.08598 0.08118 0.0048 0.0533 1.0000
11.250 0.8957 0.09418 0.08945 -0.0012 0.0526 1.0000
11.500 0.8671 0.10603 0.10129 -0.0096 0.0526 1.0000
11.750 0.8481 0.11639 0.11158 -0.0151 0.0552 1.0000
12.000 0.7145 0.11606 0.11153 -0.0095 0.0558 1.0000
12.250 0.7124 0.12023 0.11570 -0.0100 0.0576 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Coanda 3 (coanda3-il)