Coanda 2 (coanda2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 500,000 Max Cl/Cd: 62.7 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda2-il-500000.txt Download as CSV file: xf-coanda2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4375 0.09931 0.09707 -0.0141 1.0000 0.0160
-9.250 -0.4360 0.09620 0.09398 -0.0148 1.0000 0.0165
-9.000 -0.4356 0.09303 0.09084 -0.0155 1.0000 0.0176
-8.750 -0.3653 0.07548 0.07348 -0.0225 1.0000 0.0216
-8.500 -0.3591 0.07373 0.07175 -0.0210 1.0000 0.0229
-8.250 -0.3602 0.07108 0.06912 -0.0206 1.0000 0.0236
-8.000 -0.3647 0.06836 0.06644 -0.0199 1.0000 0.0243
-7.750 -0.3746 0.06578 0.06390 -0.0188 1.0000 0.0247
-7.500 -0.3887 0.06370 0.06185 -0.0166 1.0000 0.0251
-7.250 -0.3970 0.06098 0.05917 -0.0159 1.0000 0.0259
-7.000 -0.4043 0.05797 0.05618 -0.0157 1.0000 0.0265
-6.750 -0.4097 0.05463 0.05284 -0.0161 1.0000 0.0275
-5.750 -0.4304 0.02190 0.01804 -0.0294 0.9909 0.0141
-5.500 -0.4002 0.01980 0.01551 -0.0298 0.9876 0.0131
-5.250 -0.3646 0.01849 0.01394 -0.0313 0.9846 0.0126
-5.000 -0.3315 0.01622 0.01121 -0.0322 0.9825 0.0126
-4.750 -0.3079 0.01426 0.00885 -0.0310 0.9771 0.0129
-4.500 -0.2753 0.01278 0.00705 -0.0315 0.9735 0.0144
-4.250 -0.2380 0.01217 0.00629 -0.0332 0.9712 0.0159
-4.000 -0.2005 0.01161 0.00556 -0.0350 0.9696 0.0184
-3.750 -0.1748 0.01114 0.00493 -0.0342 0.9646 0.0202
-3.500 -0.1419 0.01084 0.00483 -0.0349 0.9613 0.0578
-3.250 -0.1005 0.01257 0.00666 -0.0374 0.9584 0.0690
-3.000 -0.0604 0.01354 0.00761 -0.0398 0.9565 0.0731
-2.750 -0.0344 0.01294 0.00701 -0.0395 0.9508 0.0765
-2.500 0.0004 0.01344 0.00760 -0.0410 0.9470 0.0823
-2.250 0.0369 0.01362 0.00789 -0.0431 0.9446 0.0928
-2.000 0.0753 0.01255 0.00661 -0.0450 0.9427 0.0901
-1.750 0.1027 0.01208 0.00613 -0.0447 0.9353 0.0917
-1.500 0.1410 0.01141 0.00539 -0.0468 0.9309 0.0919
-1.250 0.1735 0.01091 0.00485 -0.0475 0.9233 0.0927
-1.000 0.2114 0.01044 0.00436 -0.0495 0.9158 0.0938
-0.750 0.2438 0.01007 0.00397 -0.0503 0.9039 0.0945
-0.500 0.2778 0.00973 0.00359 -0.0514 0.8891 0.0950
-0.250 0.3084 0.00945 0.00327 -0.0518 0.8688 0.0954
0.000 0.3376 0.00923 0.00299 -0.0518 0.8389 0.0957
0.250 0.3640 0.00910 0.00272 -0.0512 0.7945 0.0959
0.500 0.3855 0.00916 0.00252 -0.0495 0.7248 0.0962
0.750 0.4029 0.00940 0.00243 -0.0470 0.6512 0.0967
1.000 0.4229 0.00958 0.00241 -0.0453 0.6041 0.0977
1.250 0.4443 0.00972 0.00240 -0.0438 0.5653 0.0985
1.500 0.4663 0.00980 0.00237 -0.0425 0.5291 0.0989
1.750 0.4888 0.00989 0.00237 -0.0414 0.4985 0.0995
2.000 0.5084 0.00995 0.00223 -0.0397 0.4468 0.1016
2.250 0.5293 0.01015 0.00224 -0.0383 0.4018 0.1036
2.500 0.5523 0.01028 0.00227 -0.0374 0.3700 0.1056
2.750 0.5747 0.01049 0.00231 -0.0363 0.3262 0.1080
3.000 0.5954 0.01089 0.00242 -0.0350 0.2585 0.1097
3.250 0.6137 0.01158 0.00266 -0.0334 0.1670 0.1112
3.500 0.6344 0.01210 0.00293 -0.0321 0.1120 0.1127
3.750 0.6519 0.01296 0.00341 -0.0303 0.0222 0.1160
4.000 0.6758 0.01318 0.00373 -0.0294 0.0183 0.1205
4.250 0.6993 0.01348 0.00416 -0.0284 0.0157 0.1272
4.500 0.8810 0.01405 0.00690 -0.0645 0.0140 1.0000
4.750 0.9033 0.01459 0.00749 -0.0633 0.0148 1.0000
5.000 0.9265 0.01505 0.00806 -0.0621 0.0163 1.0000
5.250 0.9458 0.01595 0.00904 -0.0603 0.0159 1.0000
5.500 0.9660 0.01683 0.01004 -0.0585 0.0169 1.0000
5.750 0.9851 0.01804 0.01138 -0.0563 0.0192 1.0000
6.000 1.0034 0.01966 0.01308 -0.0541 0.0197 1.0000
6.250 1.0236 0.02101 0.01453 -0.0525 0.0184 1.0000
6.500 1.0429 0.02256 0.01619 -0.0509 0.0167 1.0000
6.750 1.0619 0.02438 0.01806 -0.0494 0.0155 1.0000
7.000 1.0798 0.02674 0.02051 -0.0479 0.0144 1.0000
7.250 1.0871 0.03374 0.02794 -0.0452 0.0130 1.0000
7.500 1.0995 0.03573 0.03021 -0.0427 0.0129 1.0000
7.750 1.1115 0.03704 0.03179 -0.0401 0.0128 1.0000
8.000 1.1272 0.03683 0.03180 -0.0379 0.0120 1.0000
8.250 1.1391 0.03832 0.03350 -0.0354 0.0112 1.0000
8.500 1.1466 0.04046 0.03589 -0.0326 0.0106 1.0000
8.750 1.1506 0.04290 0.03856 -0.0296 0.0102 1.0000
9.000 1.1511 0.04550 0.04140 -0.0264 0.0099 1.0000
9.250 1.1486 0.04815 0.04427 -0.0231 0.0098 1.0000
9.500 1.1418 0.05095 0.04727 -0.0196 0.0096 1.0000
9.750 1.1271 0.05319 0.04968 -0.0148 0.0095 1.0000
10.000 1.1110 0.05582 0.05247 -0.0112 0.0095 1.0000
10.250 1.0938 0.05907 0.05589 -0.0090 0.0095 1.0000
10.500 1.0769 0.06288 0.05986 -0.0085 0.0095 1.0000
10.750 1.0580 0.06773 0.06487 -0.0098 0.0094 1.0000
11.000 1.0388 0.07381 0.07111 -0.0133 0.0095 1.0000
11.250 1.0196 0.08118 0.07863 -0.0184 0.0096 1.0000
11.500 0.9999 0.08976 0.08736 -0.0246 0.0099 1.0000
11.750 0.9779 0.09981 0.09753 -0.0314 0.0101 1.0000
12.000 0.9533 0.11141 0.10922 -0.0384 0.0105 1.0000
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Polar data table (+)
Polar graphs
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