CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 200,000 Max Cl/Cd: 63.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cast102-il-200000.txt Download as CSV file: xf-cast102-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CAST 10-2/DOA 2 AIRFOIL
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 -0.5260 0.08795 0.08449 -0.0453 1.0000 0.0420
-9.250 -0.5536 0.08425 0.08082 -0.0449 1.0000 0.0417
-9.000 -0.5876 0.08137 0.07794 -0.0427 1.0000 0.0412
-8.750 -0.6262 0.07946 0.07603 -0.0383 1.0000 0.0407
-8.500 -0.6474 0.07696 0.07349 -0.0352 1.0000 0.0408
-8.250 -0.6624 0.07428 0.07075 -0.0325 1.0000 0.0412
-8.000 -0.6734 0.07151 0.06790 -0.0300 1.0000 0.0417
-7.750 -0.6812 0.06864 0.06493 -0.0278 1.0000 0.0426
-7.500 -0.6858 0.06568 0.06184 -0.0257 1.0000 0.0438
-7.250 -0.6817 0.06474 0.06015 -0.0247 0.9977 0.0476
-7.000 -0.6737 0.05736 0.05269 -0.0260 0.9959 0.0490
-6.750 -0.6546 0.05396 0.04938 -0.0273 0.9943 0.0508
-6.500 -0.6367 0.05136 0.04665 -0.0277 0.9918 0.0538
-6.000 -0.5986 0.04507 0.03969 -0.0286 0.9873 0.0625
-5.750 -0.5749 0.04269 0.03724 -0.0295 0.9857 0.0661
-5.500 -0.5530 0.04056 0.03460 -0.0295 0.9832 0.0752
-5.250 -0.5314 0.03808 0.03216 -0.0299 0.9809 0.0793
-5.000 -0.5084 0.03614 0.02993 -0.0302 0.9787 0.0909
-4.750 -0.4837 0.03444 0.02806 -0.0309 0.9769 0.1049
-4.500 -0.4574 0.03261 0.02617 -0.0320 0.9753 0.1212
-4.250 -0.4272 0.03180 0.02521 -0.0334 0.9736 0.1450
-3.750 -0.3423 0.02571 0.01750 -0.0307 0.9719 0.0486
-3.500 -0.3171 0.02447 0.01622 -0.0301 0.9700 0.0467
-3.250 -0.2897 0.02322 0.01490 -0.0300 0.9682 0.0458
-3.000 -0.2609 0.02240 0.01403 -0.0302 0.9660 0.0461
-2.750 -0.2303 0.02200 0.01356 -0.0309 0.9638 0.0477
-2.500 -0.1995 0.02110 0.01271 -0.0317 0.9623 0.0483
-2.250 -0.1666 0.02025 0.01190 -0.0333 0.9608 0.0499
-2.000 -0.1310 0.01978 0.01145 -0.0354 0.9594 0.0529
-1.750 -0.1039 0.01958 0.01121 -0.0357 0.9566 0.0583
-1.500 -0.0782 0.01926 0.01085 -0.0357 0.9529 0.0656
-1.250 -0.0428 0.01695 0.01085 -0.0388 0.9524 0.6611
-1.000 -0.0198 0.01743 0.01157 -0.0368 0.9488 0.7473
-0.750 0.0086 0.01784 0.01203 -0.0363 0.9461 0.7785
-0.500 0.0397 0.01828 0.01252 -0.0363 0.9439 0.8047
-0.250 0.0518 0.01842 0.01269 -0.0331 0.9376 0.8169
0.000 0.0774 0.01862 0.01292 -0.0324 0.9337 0.8325
0.250 0.1167 0.01870 0.01296 -0.0348 0.9303 0.8397
0.500 0.1455 0.01859 0.01285 -0.0350 0.9210 0.8443
0.750 0.2056 0.01808 0.01230 -0.0408 0.9140 0.8479
1.000 0.2370 0.01772 0.01193 -0.0413 0.9024 0.8534
1.250 0.2917 0.01712 0.01135 -0.0460 0.8984 0.8570
1.500 0.3132 0.01696 0.01122 -0.0446 0.8878 0.8634
1.750 0.3689 0.01622 0.01050 -0.0495 0.8841 0.8678
2.000 0.3921 0.01600 0.01035 -0.0482 0.8746 0.8736
2.250 0.4343 0.01536 0.00976 -0.0503 0.8701 0.8794
2.500 0.4616 0.01505 0.00953 -0.0497 0.8618 0.8864
2.750 0.4978 0.01440 0.00894 -0.0505 0.8555 0.8928
3.000 0.5255 0.01394 0.00856 -0.0498 0.8454 0.9007
3.250 0.5623 0.01313 0.00783 -0.0505 0.8382 0.9075
3.500 0.5878 0.01258 0.00736 -0.0491 0.8242 0.9170
3.750 0.6132 0.01201 0.00687 -0.0477 0.8067 0.9278
4.000 0.6357 0.01158 0.00652 -0.0458 0.7817 0.9396
4.250 0.6633 0.01114 0.00612 -0.0449 0.7420 0.9519
4.500 0.6968 0.01089 0.00530 -0.0448 0.6061 0.9623
4.750 0.7131 0.01222 0.00565 -0.0428 0.4391 0.9790
5.000 0.7393 0.01333 0.00624 -0.0436 0.3481 0.9986
5.250 0.7527 0.01396 0.00659 -0.0418 0.3027 1.0000
5.500 0.7724 0.01461 0.00701 -0.0411 0.2662 1.0000
5.750 0.7938 0.01523 0.00746 -0.0405 0.2390 1.0000
6.000 0.8157 0.01581 0.00792 -0.0400 0.2179 1.0000
6.250 0.8377 0.01640 0.00840 -0.0394 0.2007 1.0000
6.500 0.8599 0.01694 0.00886 -0.0388 0.1847 1.0000
6.750 0.8823 0.01744 0.00931 -0.0383 0.1698 1.0000
7.000 0.9049 0.01791 0.00980 -0.0377 0.1572 1.0000
7.250 0.9274 0.01835 0.01028 -0.0371 0.1448 1.0000
7.500 0.9493 0.01881 0.01075 -0.0364 0.1315 1.0000
7.750 0.9705 0.01929 0.01124 -0.0356 0.1158 1.0000
8.000 0.9907 0.01988 0.01177 -0.0347 0.0909 1.0000
8.250 1.0067 0.02092 0.01266 -0.0329 0.0682 1.0000
8.500 1.0223 0.02198 0.01368 -0.0311 0.0588 1.0000
8.750 1.0375 0.02308 0.01475 -0.0293 0.0534 1.0000
9.000 1.0550 0.02412 0.01588 -0.0278 0.0498 1.0000
9.250 1.0725 0.02507 0.01688 -0.0265 0.0465 1.0000
9.500 1.0881 0.02660 0.01836 -0.0250 0.0437 1.0000
9.750 1.1078 0.02783 0.01972 -0.0240 0.0421 1.0000
10.000 1.1279 0.02916 0.02120 -0.0230 0.0406 1.0000
10.250 1.1482 0.03062 0.02278 -0.0222 0.0392 1.0000
10.500 1.1675 0.03211 0.02437 -0.0213 0.0379 1.0000
10.750 1.1869 0.03383 0.02614 -0.0206 0.0366 1.0000
11.000 1.2096 0.03701 0.02952 -0.0208 0.0353 1.0000
11.250 1.2196 0.03877 0.03157 -0.0185 0.0348 1.0000
11.500 1.2274 0.04095 0.03405 -0.0161 0.0344 1.0000
11.750 1.2311 0.04336 0.03678 -0.0133 0.0341 1.0000
12.000 1.2301 0.04601 0.03974 -0.0101 0.0339 1.0000
12.250 1.2247 0.04890 0.04295 -0.0068 0.0338 1.0000
12.500 1.2149 0.05205 0.04642 -0.0035 0.0337 1.0000
12.750 1.2011 0.05552 0.05019 -0.0003 0.0338 1.0000
13.000 1.1839 0.05931 0.05427 0.0024 0.0338 1.0000
13.250 1.1639 0.06352 0.05875 0.0044 0.0339 1.0000
13.500 1.1416 0.06825 0.06373 0.0055 0.0340 1.0000
13.750 1.1171 0.07363 0.06935 0.0056 0.0342 1.0000
14.000 1.0907 0.07986 0.07579 0.0042 0.0344 1.0000
14.250 1.0626 0.08716 0.08329 0.0012 0.0347 1.0000
14.500 1.0334 0.09586 0.09214 -0.0036 0.0350 1.0000
14.750 1.0050 0.10573 0.10213 -0.0092 0.0354 1.0000
15.000 0.6383 0.13938 0.13614 -0.0164 0.0532 1.0000
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Polar data table (+)
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