Coanda 1 (coanda1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 500,000 Max Cl/Cd: 63.77 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda1-il-500000.txt Download as CSV file: xf-coanda1-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4371 0.08778 0.08563 -0.0165 1.0000 0.0141
-7.750 -0.4547 0.08319 0.08111 -0.0161 1.0000 0.0144
-7.500 -0.4615 0.07876 0.07671 -0.0170 1.0000 0.0149
-7.250 -0.4610 0.07610 0.07406 -0.0167 1.0000 0.0156
-7.000 -0.4551 0.07465 0.07262 -0.0157 1.0000 0.0169
-6.750 -0.4520 0.07186 0.06983 -0.0159 1.0000 0.0178
-6.500 -0.4487 0.06877 0.06673 -0.0163 1.0000 0.0185
-6.250 -0.4445 0.06548 0.06342 -0.0166 1.0000 0.0194
-6.000 -0.4393 0.06197 0.05988 -0.0169 1.0000 0.0203
-5.750 -0.4321 0.05822 0.05607 -0.0172 1.0000 0.0214
-4.500 -0.3336 0.02051 0.01636 -0.0239 0.9851 0.0148
-4.250 -0.3062 0.01705 0.01232 -0.0236 0.9830 0.0129
-4.000 -0.2803 0.01488 0.00969 -0.0228 0.9797 0.0126
-3.750 -0.2514 0.01348 0.00796 -0.0226 0.9763 0.0128
-3.500 -0.2184 0.01258 0.00687 -0.0233 0.9736 0.0138
-3.250 -0.1837 0.01172 0.00579 -0.0245 0.9714 0.0151
-3.000 -0.1466 0.01114 0.00505 -0.0261 0.9698 0.0186
-2.750 -0.1180 0.01062 0.00441 -0.0259 0.9650 0.0217
-2.500 -0.0843 0.01034 0.00429 -0.0269 0.9612 0.0573
-2.250 -0.0412 0.01198 0.00600 -0.0299 0.9577 0.0711
-2.000 -0.0054 0.01240 0.00638 -0.0315 0.9529 0.0764
-1.750 0.0291 0.01230 0.00627 -0.0328 0.9471 0.0819
-1.500 0.0728 0.01287 0.00688 -0.0361 0.9431 0.0910
-1.250 0.1053 0.01218 0.00606 -0.0369 0.9333 0.0929
-1.000 0.1425 0.01176 0.00559 -0.0387 0.9235 0.0925
-0.750 0.1802 0.01136 0.00516 -0.0406 0.9113 0.0921
-0.500 0.2161 0.01083 0.00458 -0.0422 0.8962 0.0921
-0.250 0.2514 0.00991 0.00363 -0.0439 0.8762 0.0936
0.000 0.2819 0.00956 0.00322 -0.0443 0.8510 0.0940
0.250 0.3103 0.00928 0.00288 -0.0443 0.8188 0.0955
0.500 0.3359 0.00917 0.00265 -0.0436 0.7818 0.0964
0.750 0.3596 0.00913 0.00249 -0.0425 0.7456 0.0977
1.000 0.3825 0.00915 0.00239 -0.0413 0.7122 0.0991
1.250 0.4051 0.00919 0.00231 -0.0401 0.6802 0.1000
1.500 0.4277 0.00922 0.00225 -0.0389 0.6479 0.1009
1.750 0.4502 0.00926 0.00221 -0.0377 0.6165 0.1016
2.000 0.4708 0.00941 0.00218 -0.0361 0.5718 0.1022
2.250 0.4893 0.00969 0.00220 -0.0341 0.5044 0.1027
2.500 0.5108 0.00987 0.00223 -0.0328 0.4554 0.1033
2.750 0.5298 0.01027 0.00229 -0.0312 0.3717 0.1040
3.000 0.5494 0.01067 0.00240 -0.0296 0.3048 0.1053
3.250 0.5679 0.01114 0.00250 -0.0281 0.2212 0.1078
3.750 0.6037 0.01249 0.00298 -0.0247 0.0522 0.1123
4.000 0.6251 0.01292 0.00321 -0.0234 0.0212 0.1155
4.250 0.6494 0.01305 0.00348 -0.0226 0.0171 0.1181
4.500 0.6731 0.01322 0.00378 -0.0217 0.0159 0.1244
4.750 0.8666 0.01359 0.00649 -0.0595 0.0149 1.0000
5.000 0.8868 0.01429 0.00729 -0.0579 0.0147 1.0000
5.250 0.9057 0.01512 0.00819 -0.0560 0.0133 1.0000
5.500 0.9242 0.01604 0.00921 -0.0540 0.0139 1.0000
5.750 0.9405 0.01741 0.01069 -0.0513 0.0147 1.0000
6.750 1.0144 0.02573 0.01947 -0.0435 0.0160 1.0000
7.000 1.0338 0.02503 0.01895 -0.0416 0.0144 1.0000
7.250 1.0511 0.02649 0.02059 -0.0396 0.0134 1.0000
7.500 1.0666 0.02818 0.02248 -0.0375 0.0126 1.0000
7.750 1.0802 0.03010 0.02460 -0.0351 0.0121 1.0000
8.000 1.0919 0.03216 0.02686 -0.0326 0.0115 1.0000
8.250 1.1017 0.03444 0.02933 -0.0299 0.0111 1.0000
8.500 1.1100 0.03687 0.03198 -0.0272 0.0107 1.0000
8.750 1.1171 0.03944 0.03471 -0.0245 0.0104 1.0000
9.000 1.1203 0.04244 0.03789 -0.0215 0.0101 1.0000
9.250 1.1192 0.04569 0.04134 -0.0181 0.0099 1.0000
9.500 1.1138 0.04935 0.04521 -0.0145 0.0097 1.0000
9.750 1.1043 0.05316 0.04923 -0.0107 0.0095 1.0000
10.000 1.0824 0.05851 0.05482 -0.0063 0.0093 1.0000
10.250 1.0583 0.06174 0.05822 -0.0009 0.0092 1.0000
10.500 1.0282 0.06570 0.06236 0.0036 0.0091 1.0000
10.750 1.0112 0.06831 0.06510 0.0059 0.0091 1.0000
11.000 1.0020 0.07020 0.06708 0.0069 0.0092 1.0000
11.250 0.9827 0.07432 0.07134 0.0063 0.0092 1.0000
11.500 0.9691 0.07813 0.07526 0.0048 0.0093 1.0000
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Polar data table (+)
Polar graphs
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