Coanda 3 (coanda3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 100,000 Max Cl/Cd: 52.65 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda3-il-100000-n5.txt Download as CSV file: xf-coanda3-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4252 0.08880 0.08428 -0.0263 1.0000 0.0321
-8.000 -0.4347 0.08623 0.08179 -0.0254 1.0000 0.0312
-7.750 -0.4458 0.08188 0.07751 -0.0267 1.0000 0.0262
-7.500 -0.4492 0.07871 0.07438 -0.0266 1.0000 0.0259
-7.250 -0.4513 0.07543 0.07113 -0.0265 1.0000 0.0256
-7.000 -0.4514 0.07228 0.06799 -0.0263 1.0000 0.0245
-6.750 -0.4509 0.06854 0.06424 -0.0265 1.0000 0.0238
-6.500 -0.4483 0.06459 0.06021 -0.0268 1.0000 0.0230
-6.250 -0.4439 0.06015 0.05570 -0.0273 1.0000 0.0222
-6.000 -0.4376 0.05494 0.05036 -0.0279 1.0000 0.0209
-5.750 -0.4290 0.04789 0.04309 -0.0285 1.0000 0.0193
-5.500 -0.4154 0.04271 0.03759 -0.0280 1.0000 0.0183
-5.250 -0.4024 0.03860 0.03305 -0.0268 1.0000 0.0177
-5.000 -0.3864 0.03363 0.02751 -0.0262 0.9990 0.0173
-4.750 -0.3589 0.02938 0.02253 -0.0271 0.9954 0.0170
-4.500 -0.3305 0.02630 0.01877 -0.0274 0.9918 0.0169
-4.250 -0.2998 0.02426 0.01620 -0.0279 0.9884 0.0168
-4.000 -0.2693 0.02268 0.01419 -0.0282 0.9846 0.0171
-3.750 -0.2378 0.02150 0.01267 -0.0287 0.9806 0.0176
-3.500 -0.2058 0.02024 0.01109 -0.0294 0.9770 0.0202
-3.250 -0.1748 0.01951 0.01010 -0.0299 0.9720 0.0216
-3.000 -0.1406 0.01882 0.00921 -0.0309 0.9683 0.0239
-2.750 -0.1113 0.01812 0.00847 -0.0311 0.9628 0.0296
-2.500 -0.0769 0.01816 0.00855 -0.0323 0.9577 0.0818
-2.250 -0.0442 0.01833 0.00855 -0.0333 0.9520 0.0953
-2.000 -0.0119 0.01862 0.00870 -0.0344 0.9455 0.1109
-1.750 0.0240 0.01874 0.00876 -0.0365 0.9412 0.1277
-1.500 0.0519 0.01842 0.00840 -0.0366 0.9331 0.1311
-1.250 0.0909 0.01807 0.00798 -0.0388 0.9280 0.1369
-1.000 0.1210 0.01776 0.00757 -0.0392 0.9184 0.1404
-0.750 0.1567 0.01731 0.00716 -0.0407 0.9105 0.1448
-0.500 0.1934 0.01696 0.00678 -0.0423 0.9027 0.1511
-0.250 0.2273 0.01663 0.00645 -0.0434 0.8934 0.1585
0.000 0.2706 0.01618 0.00604 -0.0463 0.8866 0.1734
0.250 0.3036 0.01570 0.00581 -0.0472 0.8747 0.2146
0.750 0.4527 0.01370 0.00578 -0.0670 0.8633 1.0000
1.000 0.4823 0.01360 0.00568 -0.0671 0.8488 1.0000
1.250 0.5139 0.01345 0.00551 -0.0675 0.8313 1.0000
1.500 0.5409 0.01333 0.00539 -0.0669 0.8066 1.0000
1.750 0.5737 0.01315 0.00521 -0.0674 0.7778 1.0000
2.000 0.6092 0.01301 0.00503 -0.0684 0.7468 1.0000
2.250 0.6414 0.01300 0.00496 -0.0689 0.7133 1.0000
2.500 0.6708 0.01311 0.00503 -0.0688 0.6751 1.0000
2.750 0.6956 0.01333 0.00517 -0.0679 0.6315 1.0000
3.000 0.7176 0.01363 0.00536 -0.0664 0.5776 1.0000
3.250 0.7374 0.01404 0.00561 -0.0646 0.5142 1.0000
3.500 0.7555 0.01457 0.00592 -0.0625 0.4557 1.0000
3.750 0.7693 0.01541 0.00632 -0.0598 0.3851 1.0000
4.000 0.7820 0.01635 0.00679 -0.0571 0.3125 1.0000
4.250 0.7986 0.01703 0.00724 -0.0551 0.2550 1.0000
4.500 0.8136 0.01793 0.00773 -0.0529 0.1741 1.0000
4.750 0.8208 0.02005 0.00879 -0.0498 0.0288 1.0000
5.000 0.8388 0.02101 0.00983 -0.0477 0.0234 1.0000
5.250 0.8572 0.02190 0.01095 -0.0458 0.0204 1.0000
5.500 0.8731 0.02309 0.01237 -0.0436 0.0176 1.0000
5.750 0.8868 0.02442 0.01395 -0.0411 0.0166 1.0000
6.000 0.8990 0.02572 0.01544 -0.0383 0.0161 1.0000
6.250 0.9114 0.02692 0.01682 -0.0356 0.0158 1.0000
6.500 0.9231 0.02830 0.01840 -0.0328 0.0154 1.0000
6.750 0.9368 0.02965 0.01988 -0.0304 0.0148 1.0000
7.000 0.9521 0.03115 0.02152 -0.0283 0.0137 1.0000
7.250 0.9691 0.03294 0.02345 -0.0264 0.0130 1.0000
7.500 0.9878 0.03495 0.02564 -0.0249 0.0129 1.0000
7.750 1.0063 0.03733 0.02827 -0.0233 0.0128 1.0000
8.000 1.0221 0.03976 0.03101 -0.0214 0.0129 1.0000
8.250 1.0343 0.04247 0.03407 -0.0190 0.0130 1.0000
8.500 1.0429 0.04501 0.03695 -0.0164 0.0132 1.0000
8.750 1.0465 0.04793 0.04024 -0.0133 0.0134 1.0000
9.000 1.0469 0.05063 0.04326 -0.0101 0.0136 1.0000
9.250 1.0421 0.05348 0.04642 -0.0064 0.0139 1.0000
9.500 1.0324 0.05625 0.04946 -0.0025 0.0140 1.0000
9.750 1.0201 0.05914 0.05260 0.0011 0.0142 1.0000
10.000 1.0076 0.06218 0.05587 0.0038 0.0144 1.0000
10.250 0.9920 0.06564 0.05955 0.0057 0.0145 1.0000
10.500 0.9763 0.06942 0.06354 0.0066 0.0146 1.0000
10.750 0.9601 0.07357 0.06788 0.0063 0.0147 1.0000
11.000 0.9418 0.07861 0.07310 0.0048 0.0148 1.0000
11.250 0.9237 0.08431 0.07894 0.0021 0.0148 1.0000
11.500 0.9059 0.09083 0.08561 -0.0019 0.0148 1.0000
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Polar data table (+)
Polar graphs
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