CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 50,000 Max Cl/Cd: 32.79 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cast102-il-50000.txt Download as CSV file: xf-cast102-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4661 0.13352 0.12608 -0.0250 1.0000 0.2428
-11.000 -0.4809 0.13236 0.12501 -0.0258 1.0000 0.2545
-10.750 -0.4715 0.12879 0.12146 -0.0248 1.0000 0.2695
-10.500 -0.4650 0.12552 0.11823 -0.0239 1.0000 0.2846
-10.250 -0.4627 0.12267 0.11543 -0.0229 1.0000 0.3002
-10.000 -0.4664 0.12037 0.11320 -0.0219 1.0000 0.3162
-9.750 -0.4401 0.11575 0.10854 -0.0201 1.0000 0.3366
-9.500 -0.4350 0.11327 0.10611 -0.0184 1.0000 0.3587
-9.250 -0.4353 0.11087 0.10378 -0.0165 1.0000 0.3801
-9.000 -0.4287 0.10865 0.10160 -0.0142 1.0000 0.4064
-8.750 -0.4108 0.10540 0.09837 -0.0122 1.0000 0.4336
-8.500 -0.4008 0.10299 0.09600 -0.0098 1.0000 0.4641
-8.250 -0.3922 0.10076 0.09378 -0.0073 1.0000 0.4952
-8.000 -0.3777 0.09787 0.09093 -0.0055 1.0000 0.5237
-7.750 -0.3694 0.09519 0.08829 -0.0036 1.0000 0.5472
-7.500 -0.3606 0.09246 0.08559 -0.0021 1.0000 0.5664
-7.250 -0.3588 0.08992 0.08311 -0.0003 1.0000 0.5792
-6.500 -0.4524 0.08197 0.07559 0.0047 1.0000 0.4892
-6.250 -0.5250 0.07862 0.07253 0.0075 1.0000 0.4424
-6.000 -0.5954 0.07305 0.06718 0.0062 1.0000 0.4054
-5.750 -0.6504 0.05894 0.05259 -0.0109 1.0000 0.3086
-5.500 -0.6224 0.05106 0.04279 -0.0204 1.0000 0.1911
-5.250 -0.5960 0.04742 0.03838 -0.0201 1.0000 0.1598
-5.000 -0.5718 0.04465 0.03496 -0.0194 1.0000 0.1452
-4.750 -0.5487 0.04169 0.03172 -0.0187 1.0000 0.1392
-4.500 -0.5223 0.03997 0.02922 -0.0177 1.0000 0.1305
-4.250 -0.4969 0.03745 0.02653 -0.0170 1.0000 0.1261
-4.000 -0.4698 0.03552 0.02422 -0.0162 1.0000 0.1217
-3.750 -0.4425 0.03405 0.02231 -0.0153 1.0000 0.1187
-3.500 -0.4160 0.03262 0.02073 -0.0144 1.0000 0.1190
-3.250 -0.3903 0.03137 0.01949 -0.0133 1.0000 0.1226
-3.000 -0.3650 0.03041 0.01847 -0.0119 1.0000 0.1260
-2.750 -0.3407 0.02961 0.01757 -0.0103 1.0000 0.1289
-2.500 -0.3177 0.02876 0.01667 -0.0090 1.0000 0.1332
-2.250 -0.2952 0.02785 0.01577 -0.0081 1.0000 0.1432
-2.000 -0.0786 0.02927 0.01967 -0.0212 1.0000 1.0000
-1.750 -0.0735 0.02896 0.01920 -0.0186 1.0000 1.0000
-1.500 -0.0687 0.02865 0.01876 -0.0159 1.0000 1.0000
-1.250 -0.0644 0.02834 0.01834 -0.0131 1.0000 1.0000
-1.000 -0.0606 0.02801 0.01792 -0.0103 1.0000 1.0000
-0.750 -0.0573 0.02768 0.01751 -0.0074 1.0000 1.0000
-0.500 -0.0547 0.02734 0.01708 -0.0045 1.0000 1.0000
-0.250 -0.0527 0.02698 0.01666 -0.0014 1.0000 1.0000
0.000 -0.0512 0.02660 0.01623 0.0017 1.0000 1.0000
0.250 -0.0498 0.02621 0.01580 0.0049 1.0000 1.0000
0.500 -0.0478 0.02583 0.01537 0.0078 1.0000 1.0000
0.750 -0.0403 0.02559 0.01507 0.0098 1.0000 1.0000
1.000 -0.0258 0.02556 0.01496 0.0105 1.0000 1.0000
1.250 -0.0067 0.02570 0.01502 0.0104 1.0000 1.0000
1.500 0.0148 0.02597 0.01521 0.0099 1.0000 1.0000
1.750 0.0376 0.02633 0.01552 0.0092 1.0000 1.0000
2.000 0.0609 0.02678 0.01591 0.0084 1.0000 1.0000
2.250 0.0842 0.02729 0.01640 0.0076 1.0000 1.0000
2.500 0.1072 0.02788 0.01696 0.0068 1.0000 1.0000
2.750 0.1298 0.02852 0.01762 0.0061 1.0000 1.0000
3.000 0.1519 0.02924 0.01835 0.0054 1.0000 1.0000
3.250 0.1732 0.03003 0.01918 0.0047 1.0000 1.0000
3.500 0.1938 0.03092 0.02013 0.0040 1.0000 1.0000
3.750 0.2134 0.03191 0.02120 0.0033 1.0000 1.0000
4.000 0.2715 0.03376 0.02322 -0.0048 0.9802 1.0000
4.250 0.3546 0.03536 0.02508 -0.0161 0.9388 1.0000
4.500 0.4347 0.03587 0.02589 -0.0252 0.8989 1.0000
4.750 0.4962 0.03529 0.02565 -0.0298 0.8576 1.0000
5.000 0.5605 0.03365 0.02439 -0.0332 0.8151 1.0000
5.250 0.6245 0.03064 0.02184 -0.0346 0.7668 1.0000
5.500 0.6778 0.02661 0.01819 -0.0325 0.6981 1.0000
5.750 0.7666 0.02338 0.01396 -0.0345 0.5165 1.0000
6.000 0.7984 0.02505 0.01490 -0.0345 0.4398 1.0000
6.250 0.8322 0.02666 0.01623 -0.0354 0.3917 1.0000
6.500 0.8646 0.02824 0.01763 -0.0361 0.3569 1.0000
6.750 0.8947 0.02989 0.01928 -0.0365 0.3300 1.0000
7.000 0.9235 0.03161 0.02091 -0.0367 0.3058 1.0000
7.250 0.9454 0.03330 0.02281 -0.0357 0.2834 1.0000
7.500 0.9658 0.03483 0.02427 -0.0346 0.2578 1.0000
7.750 0.9831 0.03609 0.02535 -0.0331 0.2296 1.0000
8.000 0.9970 0.03768 0.02714 -0.0309 0.2038 1.0000
8.250 1.0139 0.04008 0.02964 -0.0292 0.1808 1.0000
8.500 1.0290 0.04253 0.03228 -0.0273 0.1619 1.0000
8.750 1.0434 0.04546 0.03548 -0.0254 0.1493 1.0000
9.000 1.0625 0.04853 0.03858 -0.0244 0.1402 1.0000
9.250 1.0632 0.05200 0.04274 -0.0209 0.1347 1.0000
9.500 1.0859 0.05479 0.04535 -0.0207 0.1268 1.0000
9.750 1.0802 0.05881 0.05002 -0.0169 0.1254 1.0000
10.000 1.0724 0.06313 0.05483 -0.0135 0.1247 1.0000
10.250 1.0598 0.06759 0.05969 -0.0101 0.1245 1.0000
10.500 1.0435 0.07211 0.06453 -0.0069 0.1247 1.0000
10.750 1.0242 0.07660 0.06925 -0.0039 0.1252 1.0000
11.000 1.0038 0.08115 0.07396 -0.0014 0.1258 1.0000
11.250 0.9855 0.08616 0.07909 0.0001 0.1264 1.0000
11.500 0.7530 0.13612 0.12895 -0.0407 0.3058 1.0000
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Polar data table (+)
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