Coanda 2 (coanda2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 500,000 Max Cl/Cd: 52.92 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda2-il-500000-n5.txt Download as CSV file: xf-coanda2-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4394 0.08842 0.08629 -0.0161 1.0000 0.0036
-8.500 -0.4452 0.08491 0.08283 -0.0164 1.0000 0.0033
-8.250 -0.4527 0.08220 0.08016 -0.0159 1.0000 0.0035
-8.000 -0.4598 0.07974 0.07774 -0.0150 1.0000 0.0038
-7.750 -0.4640 0.07598 0.07402 -0.0159 1.0000 0.0037
-7.500 -0.4653 0.07257 0.07062 -0.0167 1.0000 0.0040
-7.250 -0.4628 0.06808 0.06613 -0.0192 0.9995 0.0040
-7.000 -0.4393 0.05982 0.05780 -0.0289 0.9959 0.0039
-6.750 -0.4150 0.05242 0.05028 -0.0363 0.9919 0.0048
-6.500 -0.3915 0.04045 0.03796 -0.0455 0.9868 0.0046
-6.250 -0.3801 0.02744 0.02418 -0.0483 0.9793 0.0042
-6.000 -0.3562 0.02219 0.01837 -0.0489 0.9766 0.0045
-5.750 -0.3382 0.01918 0.01487 -0.0472 0.9706 0.0044
-5.500 -0.3114 0.01694 0.01219 -0.0470 0.9671 0.0044
-5.250 -0.2853 0.01534 0.01029 -0.0465 0.9629 0.0044
-5.000 -0.2605 0.01391 0.00858 -0.0455 0.9575 0.0045
-4.750 -0.2304 0.01289 0.00733 -0.0457 0.9544 0.0044
-4.500 -0.2031 0.01219 0.00647 -0.0452 0.9491 0.0046
-4.250 -0.1730 0.01177 0.00588 -0.0452 0.9431 0.0050
-4.000 -0.1388 0.01102 0.00492 -0.0463 0.9399 0.0058
-3.750 -0.1106 0.01042 0.00421 -0.0462 0.9331 0.0115
-3.500 -0.0773 0.00977 0.00344 -0.0474 0.9286 0.0176
-3.250 -0.0445 0.00938 0.00293 -0.0484 0.9235 0.0212
-3.000 -0.0120 0.00913 0.00262 -0.0493 0.9166 0.0244
-2.750 0.0210 0.00875 0.00231 -0.0504 0.9096 0.0471
-2.500 0.0557 0.00872 0.00229 -0.0518 0.9004 0.0577
-2.250 0.0874 0.00867 0.00218 -0.0525 0.8893 0.0613
-2.000 0.1189 0.00865 0.00215 -0.0532 0.8761 0.0636
-1.750 0.1494 0.00865 0.00212 -0.0536 0.8597 0.0655
-1.500 0.1778 0.00865 0.00202 -0.0535 0.8379 0.0673
-1.250 0.2047 0.00865 0.00192 -0.0532 0.8083 0.0688
-1.000 0.2292 0.00874 0.00184 -0.0522 0.7641 0.0704
-0.750 0.2494 0.00907 0.00187 -0.0503 0.6932 0.0722
-0.500 0.2693 0.00939 0.00195 -0.0485 0.6373 0.0740
-0.250 0.2904 0.00947 0.00188 -0.0470 0.5986 0.0760
0.000 0.3127 0.00958 0.00187 -0.0458 0.5613 0.0772
0.250 0.3351 0.00970 0.00186 -0.0446 0.5228 0.0784
0.500 0.3575 0.00981 0.00183 -0.0435 0.4860 0.0794
0.750 0.3804 0.00991 0.00182 -0.0424 0.4537 0.0801
1.000 0.4032 0.01005 0.00183 -0.0414 0.4205 0.0813
1.500 0.4494 0.01036 0.00189 -0.0395 0.3530 0.0836
1.750 0.4737 0.01045 0.00193 -0.0388 0.3323 0.0847
2.000 0.4976 0.01059 0.00198 -0.0381 0.3048 0.0857
2.250 0.5209 0.01080 0.00206 -0.0373 0.2696 0.0864
2.500 0.5441 0.01099 0.00214 -0.0364 0.2359 0.0876
2.750 0.5668 0.01125 0.00232 -0.0355 0.1974 0.0892
3.000 0.5873 0.01177 0.00256 -0.0343 0.1347 0.0906
3.250 0.6068 0.01242 0.00290 -0.0329 0.0628 0.0924
3.500 0.6281 0.01292 0.00328 -0.0317 0.0176 0.0944
3.750 0.6515 0.01322 0.00370 -0.0308 0.0114 0.0963
4.000 0.6737 0.01369 0.00434 -0.0295 0.0075 0.0984
4.250 0.6980 0.01386 0.00454 -0.0289 0.0055 0.1022
4.500 0.7215 0.01412 0.00488 -0.0281 0.0039 0.1085
4.750 0.7403 0.01497 0.00589 -0.0262 0.0027 0.1174
5.000 0.9108 0.01721 0.01028 -0.0604 0.0022 1.0000
5.250 0.9294 0.01838 0.01151 -0.0586 0.0022 1.0000
5.500 0.9482 0.01982 0.01301 -0.0567 0.0022 1.0000
5.750 0.9680 0.02119 0.01447 -0.0551 0.0023 1.0000
6.000 0.9879 0.02292 0.01632 -0.0535 0.0023 1.0000
6.250 1.0074 0.02465 0.01820 -0.0519 0.0023 1.0000
6.500 1.0258 0.02674 0.02048 -0.0501 0.0024 1.0000
6.750 1.0425 0.02895 0.02291 -0.0481 0.0024 1.0000
7.000 1.0570 0.03135 0.02556 -0.0459 0.0025 1.0000
8.500 1.1175 0.04475 0.04032 -0.0309 0.0032 1.0000
8.750 1.1165 0.04740 0.04326 -0.0273 0.0033 1.0000
9.000 1.1124 0.05019 0.04627 -0.0240 0.0033 1.0000
9.250 1.1031 0.05307 0.04935 -0.0201 0.0033 1.0000
9.500 1.0884 0.05518 0.05163 -0.0155 0.0033 1.0000
9.750 1.0722 0.05789 0.05450 -0.0122 0.0033 1.0000
10.000 1.0542 0.06139 0.05816 -0.0104 0.0033 1.0000
10.250 1.0382 0.06524 0.06219 -0.0103 0.0034 1.0000
10.500 1.0193 0.07039 0.06752 -0.0123 0.0034 1.0000
10.750 1.0030 0.07631 0.07359 -0.0160 0.0034 1.0000
11.000 0.9810 0.08508 0.08259 -0.0229 0.0036 1.0000
11.250 0.9626 0.09410 0.09174 -0.0293 0.0037 1.0000
11.500 0.9404 0.10534 0.10312 -0.0367 0.0038 1.0000
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Polar data table (+)
Polar graphs
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