Coanda 1 (coanda1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 50,000 Max Cl/Cd: 37.68 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda1-il-50000-n5.txt Download as CSV file: xf-coanda1-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4221 0.10007 0.09329 -0.0169 1.0000 0.0432
-8.000 -0.4224 0.09683 0.09014 -0.0173 1.0000 0.0419
-7.500 -0.4316 0.09038 0.08389 -0.0208 1.0000 0.0369
-7.250 -0.4285 0.08706 0.08062 -0.0212 1.0000 0.0367
-7.000 -0.4256 0.08356 0.07716 -0.0222 1.0000 0.0367
-6.750 -0.4210 0.08019 0.07382 -0.0227 1.0000 0.0364
-6.500 -0.4160 0.07660 0.07026 -0.0235 1.0000 0.0364
-6.250 -0.4099 0.07303 0.06669 -0.0242 1.0000 0.0362
-6.000 -0.4029 0.06926 0.06291 -0.0248 1.0000 0.0360
-5.750 -0.3944 0.06576 0.05937 -0.0251 1.0000 0.0357
-5.500 -0.3852 0.06197 0.05551 -0.0253 1.0000 0.0354
-5.250 -0.3747 0.05821 0.05165 -0.0253 1.0000 0.0351
-5.000 -0.3632 0.05441 0.04772 -0.0252 1.0000 0.0349
-4.750 -0.3508 0.05058 0.04371 -0.0246 1.0000 0.0348
-4.500 -0.3374 0.04693 0.03983 -0.0238 1.0000 0.0349
-4.250 -0.3232 0.04315 0.03577 -0.0226 1.0000 0.0353
-4.000 -0.3080 0.03935 0.03159 -0.0212 1.0000 0.0362
-3.750 -0.2915 0.03727 0.02928 -0.0196 1.0000 0.0397
-3.500 -0.2736 0.03465 0.02623 -0.0179 1.0000 0.0440
-3.250 -0.2545 0.03188 0.02303 -0.0161 1.0000 0.0477
-3.000 -0.2338 0.02988 0.02061 -0.0143 1.0000 0.0558
-2.750 -0.2122 0.02846 0.01864 -0.0125 1.0000 0.0787
-2.500 -0.1939 0.02797 0.01750 -0.0106 1.0000 0.1130
-2.250 -0.1768 0.02737 0.01675 -0.0094 1.0000 0.1408
-2.000 -0.1538 0.02632 0.01533 -0.0085 1.0000 0.1435
-1.750 -0.1310 0.02556 0.01431 -0.0077 1.0000 0.1464
-1.500 -0.1079 0.02498 0.01345 -0.0070 1.0000 0.1489
-1.250 -0.0844 0.02447 0.01267 -0.0063 1.0000 0.1490
-1.000 -0.0578 0.02403 0.01193 -0.0062 1.0000 0.1487
-0.750 -0.0289 0.02371 0.01135 -0.0067 1.0000 0.1486
-0.500 -0.0008 0.02345 0.01089 -0.0071 1.0000 0.1490
-0.250 0.0432 0.02323 0.01046 -0.0108 0.9927 0.1499
0.000 0.0888 0.02304 0.01014 -0.0148 0.9835 0.1517
0.250 0.1324 0.02289 0.00990 -0.0184 0.9732 0.1540
0.500 0.1748 0.02272 0.00971 -0.0218 0.9619 0.1574
0.750 0.2166 0.02254 0.00961 -0.0251 0.9496 0.1665
1.000 0.2610 0.02231 0.00949 -0.0287 0.9344 0.1746
1.250 0.3086 0.02199 0.00927 -0.0326 0.9168 0.1811
1.500 0.3563 0.02156 0.00903 -0.0363 0.8985 0.1907
2.000 0.5088 0.01904 0.00877 -0.0553 0.8597 1.0000
2.250 0.5469 0.01875 0.00855 -0.0563 0.8240 1.0000
2.500 0.5853 0.01851 0.00832 -0.0573 0.7860 1.0000
2.750 0.6208 0.01839 0.00822 -0.0578 0.7476 1.0000
3.000 0.6523 0.01843 0.00829 -0.0576 0.7073 1.0000
3.250 0.6798 0.01861 0.00847 -0.0567 0.6650 1.0000
3.500 0.7042 0.01889 0.00874 -0.0553 0.6203 1.0000
3.750 0.7260 0.01927 0.00903 -0.0533 0.5679 1.0000
4.000 0.7384 0.02000 0.00916 -0.0495 0.4558 1.0000
4.250 0.7533 0.02091 0.00951 -0.0469 0.3613 1.0000
4.500 0.7706 0.02188 0.01012 -0.0451 0.2976 1.0000
4.750 0.7909 0.02266 0.01086 -0.0438 0.2590 1.0000
5.000 0.8109 0.02349 0.01162 -0.0424 0.2148 1.0000
5.250 0.8308 0.02439 0.01248 -0.0411 0.1658 1.0000
5.750 0.8651 0.02789 0.01521 -0.0380 0.0328 1.0000
6.000 0.8838 0.02925 0.01678 -0.0363 0.0296 1.0000
6.250 0.9008 0.03075 0.01851 -0.0344 0.0268 1.0000
6.500 0.9143 0.03259 0.02058 -0.0323 0.0250 1.0000
6.750 0.9277 0.03424 0.02249 -0.0299 0.0244 1.0000
7.000 0.9398 0.03599 0.02451 -0.0274 0.0241 1.0000
7.250 0.9519 0.03772 0.02648 -0.0250 0.0240 1.0000
7.500 0.9642 0.03965 0.02878 -0.0225 0.0238 1.0000
7.750 0.9777 0.04178 0.03116 -0.0202 0.0238 1.0000
8.000 0.9923 0.04415 0.03381 -0.0180 0.0237 1.0000
8.250 1.0061 0.04663 0.03661 -0.0160 0.0235 1.0000
8.500 1.0172 0.04942 0.03977 -0.0138 0.0233 1.0000
8.750 1.0244 0.05235 0.04308 -0.0114 0.0230 1.0000
9.000 1.0277 0.05539 0.04648 -0.0089 0.0229 1.0000
9.250 1.0250 0.05872 0.05019 -0.0061 0.0227 1.0000
9.500 1.0195 0.06185 0.05363 -0.0034 0.0227 1.0000
9.750 1.0076 0.06500 0.05705 -0.0003 0.0228 1.0000
10.000 0.9932 0.06843 0.06070 0.0019 0.0228 1.0000
10.250 0.9782 0.07215 0.06463 0.0029 0.0229 1.0000
10.500 0.9620 0.07656 0.06923 0.0026 0.0230 1.0000
10.750 0.9475 0.08128 0.07410 0.0011 0.0233 1.0000
11.000 0.9306 0.08708 0.08003 -0.0017 0.0234 1.0000
11.250 0.9147 0.09353 0.08658 -0.0054 0.0236 1.0000
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Polar data table (+)
Polar graphs
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