CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 50,000 Max Cl/Cd: 30.31 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cast102-il-50000-n5.txt Download as CSV file: xf-cast102-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4863 0.08813 0.08148 -0.0494 1.0000 0.0730
-9.250 -0.5316 0.09157 0.08454 -0.0473 1.0000 0.0795
-9.000 -0.5810 0.08797 0.08092 -0.0464 1.0000 0.0714
-8.750 -0.5875 0.08483 0.07783 -0.0442 1.0000 0.0692
-8.500 -0.6032 0.08174 0.07474 -0.0419 1.0000 0.0674
-8.250 -0.6205 0.07850 0.07144 -0.0395 1.0000 0.0653
-8.000 -0.6595 0.07579 0.06805 -0.0356 1.0000 0.0594
-7.750 -0.6509 0.07169 0.06408 -0.0344 1.0000 0.0581
-7.500 -0.6512 0.06833 0.06063 -0.0324 1.0000 0.0568
-7.250 -0.6512 0.06504 0.05717 -0.0304 1.0000 0.0556
-7.000 -0.6493 0.06173 0.05363 -0.0285 1.0000 0.0542
-6.750 -0.6450 0.05841 0.05000 -0.0266 1.0000 0.0528
-6.500 -0.6379 0.05510 0.04627 -0.0248 1.0000 0.0513
-6.250 -0.6274 0.05192 0.04261 -0.0231 1.0000 0.0499
-6.000 -0.6137 0.04917 0.03926 -0.0213 1.0000 0.0487
-5.750 -0.5978 0.04674 0.03638 -0.0199 1.0000 0.0483
-5.500 -0.5807 0.04423 0.03371 -0.0190 1.0000 0.0493
-5.250 -0.5623 0.04213 0.03141 -0.0181 1.0000 0.0506
-5.000 -0.5422 0.04019 0.02917 -0.0172 1.0000 0.0518
-4.750 -0.5203 0.03832 0.02699 -0.0162 1.0000 0.0522
-4.500 -0.4969 0.03660 0.02496 -0.0153 1.0000 0.0524
-4.250 -0.4729 0.03507 0.02317 -0.0145 1.0000 0.0528
-4.000 -0.4486 0.03374 0.02165 -0.0135 1.0000 0.0535
-3.750 -0.4245 0.03266 0.02041 -0.0125 1.0000 0.0553
-3.500 -0.4010 0.03184 0.01941 -0.0113 1.0000 0.0580
-3.250 -0.3781 0.03102 0.01849 -0.0099 1.0000 0.0601
-3.000 -0.3567 0.03009 0.01755 -0.0086 1.0000 0.0620
-2.750 -0.3355 0.02932 0.01668 -0.0076 1.0000 0.0644
-2.500 -0.3137 0.02864 0.01588 -0.0069 1.0000 0.0681
-2.250 -0.2915 0.02805 0.01514 -0.0063 1.0000 0.0738
-2.000 -0.2682 0.02736 0.01439 -0.0062 1.0000 0.0815
-1.750 -0.2437 0.02676 0.01373 -0.0063 1.0000 0.0927
-1.500 -0.2193 0.02392 0.01351 -0.0071 1.0000 0.5731
-1.250 -0.2121 0.02429 0.01428 -0.0008 1.0000 0.7461
-1.000 -0.2067 0.02461 0.01470 0.0058 1.0000 0.8106
-0.750 -0.2022 0.02484 0.01499 0.0129 0.9986 0.8706
-0.500 -0.1782 0.02523 0.01533 0.0162 0.9958 0.9315
-0.250 -0.1378 0.02550 0.01538 0.0130 0.9927 0.9473
0.000 -0.0993 0.02571 0.01539 0.0098 0.9889 0.9559
0.250 -0.0576 0.02602 0.01555 0.0058 0.9853 0.9649
0.500 -0.0195 0.02624 0.01565 0.0024 0.9806 0.9748
0.750 0.0214 0.02654 0.01585 -0.0015 0.9759 0.9861
1.000 0.0598 0.02678 0.01603 -0.0051 0.9703 1.0000
1.250 0.0847 0.02689 0.01609 -0.0061 0.9630 1.0000
1.500 0.1158 0.02717 0.01631 -0.0082 0.9565 1.0000
1.750 0.1462 0.02742 0.01653 -0.0101 0.9481 1.0000
2.000 0.1819 0.02774 0.01683 -0.0127 0.9387 1.0000
2.250 0.2260 0.02806 0.01715 -0.0166 0.9271 1.0000
2.500 0.2720 0.02824 0.01736 -0.0206 0.9135 1.0000
2.750 0.3126 0.02828 0.01746 -0.0234 0.8986 1.0000
3.000 0.3517 0.02823 0.01749 -0.0257 0.8836 1.0000
3.250 0.3924 0.02806 0.01743 -0.0280 0.8680 1.0000
3.500 0.4236 0.02782 0.01729 -0.0284 0.8494 1.0000
3.750 0.4573 0.02745 0.01704 -0.0291 0.8298 1.0000
4.000 0.4956 0.02684 0.01662 -0.0301 0.8098 1.0000
4.250 0.5214 0.02638 0.01630 -0.0291 0.7852 1.0000
4.500 0.5475 0.02583 0.01589 -0.0280 0.7578 1.0000
4.750 0.5689 0.02536 0.01558 -0.0260 0.7240 1.0000
5.000 0.5892 0.02496 0.01535 -0.0239 0.6801 1.0000
5.250 0.6271 0.02383 0.01426 -0.0234 0.6115 1.0000
5.500 0.6922 0.02284 0.01249 -0.0265 0.4742 1.0000
5.750 0.7113 0.02382 0.01293 -0.0248 0.4035 1.0000
6.000 0.7289 0.02486 0.01365 -0.0234 0.3564 1.0000
6.250 0.7483 0.02587 0.01443 -0.0223 0.3213 1.0000
6.500 0.7700 0.02681 0.01529 -0.0216 0.2928 1.0000
6.750 0.7937 0.02773 0.01617 -0.0213 0.2687 1.0000
7.000 0.8189 0.02867 0.01707 -0.0212 0.2482 1.0000
7.250 0.8466 0.02963 0.01803 -0.0214 0.2306 1.0000
7.500 0.8753 0.03062 0.01911 -0.0219 0.2132 1.0000
7.750 0.9019 0.03166 0.02026 -0.0219 0.1961 1.0000
8.000 0.9217 0.03263 0.02132 -0.0211 0.1775 1.0000
8.500 0.9476 0.03445 0.02314 -0.0177 0.1410 1.0000
8.750 0.9646 0.03562 0.02447 -0.0166 0.1242 1.0000
9.000 0.9822 0.03703 0.02601 -0.0154 0.1090 1.0000
9.250 0.9981 0.03854 0.02760 -0.0142 0.0959 1.0000
9.500 1.0122 0.04006 0.02911 -0.0127 0.0868 1.0000
9.750 1.0325 0.04216 0.03155 -0.0120 0.0785 1.0000
10.000 1.0466 0.04400 0.03344 -0.0107 0.0732 1.0000
10.250 1.0599 0.04620 0.03600 -0.0092 0.0679 1.0000
10.500 1.0707 0.04812 0.03802 -0.0076 0.0646 1.0000
10.750 1.0822 0.05070 0.04080 -0.0062 0.0623 1.0000
11.000 1.0856 0.05384 0.04442 -0.0039 0.0601 1.0000
11.250 1.0840 0.05688 0.04784 -0.0015 0.0582 1.0000
11.500 1.0801 0.05981 0.05105 0.0008 0.0565 1.0000
11.750 1.0755 0.06266 0.05410 0.0028 0.0550 1.0000
12.000 1.0713 0.06548 0.05708 0.0044 0.0538 1.0000
12.250 1.0666 0.06860 0.06031 0.0057 0.0528 1.0000
12.500 1.0491 0.07307 0.06505 0.0069 0.0525 1.0000
12.750 1.0267 0.07832 0.07058 0.0070 0.0524 1.0000
13.000 1.0020 0.08432 0.07683 0.0059 0.0525 1.0000
13.250 0.9754 0.09133 0.08404 0.0033 0.0526 1.0000
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Polar data table (+)
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