Coanda 3 (coanda3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 200,000 Max Cl/Cd: 75.5 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda3-il-200000.txt Download as CSV file: xf-coanda3-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4367 0.10395 0.10054 -0.0284 1.0000 0.0490
-9.250 -0.4439 0.10164 0.09829 -0.0301 1.0000 0.0492
-9.000 -0.4551 0.09937 0.09610 -0.0310 1.0000 0.0493
-8.750 -0.4269 0.09281 0.08945 -0.0250 1.0000 0.0519
-8.500 -0.4263 0.09034 0.08702 -0.0240 1.0000 0.0536
-7.250 -0.4686 0.07905 0.07580 -0.0293 1.0000 0.0607
-7.000 -0.4717 0.07348 0.07031 -0.0273 1.0000 0.0615
-6.750 -0.4687 0.07041 0.06728 -0.0242 1.0000 0.0623
-6.500 -0.4654 0.06726 0.06413 -0.0228 1.0000 0.0629
-6.250 -0.4606 0.06422 0.06106 -0.0218 1.0000 0.0637
-6.000 -0.4547 0.06085 0.05764 -0.0212 1.0000 0.0644
-5.750 -0.4470 0.05727 0.05397 -0.0210 1.0000 0.0649
-5.500 -0.4376 0.05361 0.05021 -0.0207 1.0000 0.0652
-5.250 -0.4304 0.03910 0.03492 -0.0219 1.0000 0.0377
-5.000 -0.4254 0.02718 0.02182 -0.0189 1.0000 0.0288
-4.750 -0.4106 0.02328 0.01732 -0.0166 1.0000 0.0273
-4.500 -0.3921 0.02058 0.01406 -0.0145 1.0000 0.0259
-4.250 -0.3718 0.01874 0.01179 -0.0125 1.0000 0.0254
-4.000 -0.3512 0.01775 0.01056 -0.0109 0.9999 0.0280
-3.750 -0.3151 0.01671 0.00925 -0.0122 0.9962 0.0282
-3.500 -0.2790 0.01610 0.00842 -0.0136 0.9921 0.0282
-3.250 -0.2429 0.01565 0.00776 -0.0150 0.9873 0.0293
-3.000 -0.2042 0.01535 0.00739 -0.0170 0.9833 0.0340
-2.750 -0.1701 0.01521 0.00744 -0.0183 0.9773 0.0693
-2.500 -0.1279 0.01571 0.00780 -0.0212 0.9718 0.0875
-2.250 -0.0886 0.01599 0.00801 -0.0236 0.9647 0.0960
-2.000 -0.0451 0.01639 0.00835 -0.0270 0.9582 0.1089
-1.750 -0.0087 0.01634 0.00827 -0.0290 0.9506 0.1186
-1.500 0.0331 0.01610 0.00798 -0.0318 0.9451 0.1246
-1.250 0.0680 0.01592 0.00783 -0.0334 0.9376 0.1378
-1.000 0.1091 0.01542 0.00732 -0.0360 0.9322 0.1427
-0.750 0.1461 0.01488 0.00687 -0.0378 0.9255 0.1472
-0.500 0.1867 0.01436 0.00638 -0.0402 0.9190 0.1526
-0.250 0.2269 0.01376 0.00588 -0.0425 0.9133 0.1592
0.000 0.2630 0.01332 0.00550 -0.0439 0.9062 0.1683
0.250 0.3075 0.01272 0.00507 -0.0472 0.9029 0.1868
0.500 0.3274 0.01121 0.00487 -0.0456 0.8922 0.5549
0.750 0.5103 0.00999 0.00460 -0.0784 0.9019 1.0000
1.000 0.5428 0.00976 0.00439 -0.0790 0.8868 1.0000
1.250 0.5718 0.00960 0.00422 -0.0788 0.8687 1.0000
1.500 0.6027 0.00944 0.00406 -0.0790 0.8489 1.0000
1.750 0.6292 0.00933 0.00394 -0.0783 0.8233 1.0000
2.000 0.6572 0.00924 0.00383 -0.0779 0.7908 1.0000
2.250 0.6854 0.00923 0.00370 -0.0774 0.7502 1.0000
2.500 0.7097 0.00940 0.00370 -0.0763 0.7055 1.0000
2.750 0.7282 0.00975 0.00377 -0.0739 0.6410 1.0000
3.000 0.7387 0.01035 0.00386 -0.0700 0.5340 1.0000
3.250 0.7485 0.01109 0.00409 -0.0663 0.4402 1.0000
3.500 0.7615 0.01180 0.00446 -0.0634 0.3799 1.0000
3.750 0.7781 0.01234 0.00480 -0.0613 0.3394 1.0000
4.000 0.7949 0.01287 0.00511 -0.0593 0.2917 1.0000
4.250 0.8126 0.01338 0.00541 -0.0574 0.2379 1.0000
4.500 0.8289 0.01408 0.00576 -0.0553 0.1731 1.0000
4.750 0.8365 0.01577 0.00658 -0.0519 0.0415 1.0000
5.000 0.8537 0.01661 0.00745 -0.0497 0.0296 1.0000
5.250 0.8720 0.01736 0.00838 -0.0477 0.0268 1.0000
5.500 0.8890 0.01821 0.00943 -0.0454 0.0257 1.0000
5.750 0.9045 0.01914 0.01052 -0.0429 0.0253 1.0000
6.000 0.9184 0.02018 0.01167 -0.0403 0.0252 1.0000
6.250 0.9318 0.02143 0.01300 -0.0375 0.0252 1.0000
6.500 0.9473 0.02271 0.01436 -0.0351 0.0245 1.0000
6.750 0.9642 0.02403 0.01577 -0.0331 0.0225 1.0000
7.000 0.9842 0.02579 0.01767 -0.0315 0.0231 1.0000
7.250 1.0069 0.02810 0.02013 -0.0303 0.0240 1.0000
7.500 1.0346 0.03250 0.02471 -0.0302 0.0261 1.0000
7.750 1.0556 0.03232 0.02491 -0.0274 0.0298 1.0000
8.000 1.0805 0.03663 0.02996 -0.0246 0.0421 1.0000
13.500 0.6752 0.14811 0.14484 -0.0190 0.0704 1.0000
13.750 0.6450 0.15186 0.14855 -0.0256 0.0687 1.0000
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Polar data table (+)
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