CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.62 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cast102-il-1000000-n5.txt Download as CSV file: xf-cast102-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5478 0.07736 0.07561 -0.0619 0.9758 0.0067
-10.750 -0.5855 0.06593 0.06404 -0.0709 0.9612 0.0067
-10.500 -0.6129 0.05989 0.05784 -0.0732 0.9486 0.0067
-10.250 -0.6338 0.05567 0.05346 -0.0726 0.9381 0.0067
-10.000 -0.6443 0.05178 0.04939 -0.0714 0.9306 0.0067
-9.750 -0.6473 0.04792 0.04534 -0.0705 0.9253 0.0068
-9.500 -0.6471 0.04391 0.04111 -0.0694 0.9202 0.0069
-9.250 -0.6432 0.04008 0.03704 -0.0681 0.9159 0.0070
-8.750 -0.6623 0.02054 0.01581 -0.0609 0.9062 0.0083
-8.500 -0.6417 0.01866 0.01365 -0.0602 0.9034 0.0086
-8.250 -0.6186 0.01758 0.01240 -0.0599 0.9009 0.0087
-8.000 -0.5959 0.01638 0.01102 -0.0594 0.8985 0.0089
-7.750 -0.5716 0.01557 0.01012 -0.0592 0.8962 0.0091
-7.500 -0.5462 0.01502 0.00952 -0.0592 0.8936 0.0092
-7.250 -0.5205 0.01457 0.00902 -0.0591 0.8911 0.0094
-7.000 -0.4947 0.01411 0.00851 -0.0591 0.8887 0.0096
-6.750 -0.4688 0.01365 0.00799 -0.0590 0.8865 0.0098
-6.500 -0.4431 0.01315 0.00743 -0.0589 0.8843 0.0100
-6.250 -0.4173 0.01267 0.00689 -0.0588 0.8822 0.0103
-6.000 -0.3911 0.01219 0.00637 -0.0588 0.8799 0.0106
-5.750 -0.3649 0.01175 0.00588 -0.0588 0.8776 0.0109
-5.500 -0.3384 0.01136 0.00545 -0.0588 0.8754 0.0112
-5.250 -0.3113 0.01107 0.00512 -0.0589 0.8733 0.0114
-5.000 -0.2852 0.01061 0.00462 -0.0589 0.8712 0.0119
-4.750 -0.2583 0.01029 0.00428 -0.0590 0.8691 0.0123
-4.500 -0.2308 0.01003 0.00400 -0.0591 0.8671 0.0127
-4.250 -0.2031 0.00976 0.00373 -0.0594 0.8651 0.0131
-4.000 -0.1753 0.00952 0.00347 -0.0596 0.8631 0.0135
-3.750 -0.1474 0.00928 0.00322 -0.0598 0.8611 0.0140
-3.500 -0.1193 0.00907 0.00299 -0.0601 0.8590 0.0145
-3.250 -0.0910 0.00889 0.00279 -0.0603 0.8569 0.0148
-3.000 -0.0630 0.00865 0.00255 -0.0606 0.8549 0.0159
-2.750 -0.0345 0.00851 0.00240 -0.0609 0.8531 0.0169
-2.500 -0.0059 0.00836 0.00226 -0.0612 0.8513 0.0177
-2.250 0.0229 0.00823 0.00213 -0.0616 0.8494 0.0186
-2.000 0.0516 0.00808 0.00200 -0.0620 0.8473 0.0200
-1.750 0.0803 0.00796 0.00189 -0.0623 0.8438 0.0223
-1.500 0.1087 0.00785 0.00177 -0.0625 0.8388 0.0264
-1.250 0.1372 0.00772 0.00167 -0.0627 0.8322 0.0342
-1.000 0.1600 0.00570 0.00124 -0.0633 0.8257 0.5518
-0.750 0.1884 0.00556 0.00123 -0.0636 0.8188 0.6003
-0.500 0.2169 0.00553 0.00119 -0.0637 0.8087 0.6195
-0.250 0.2452 0.00550 0.00117 -0.0639 0.7955 0.6370
0.000 0.2736 0.00549 0.00116 -0.0640 0.7814 0.6523
0.250 0.3017 0.00552 0.00115 -0.0641 0.7644 0.6598
0.500 0.3297 0.00559 0.00114 -0.0642 0.7428 0.6657
0.750 0.3564 0.00571 0.00115 -0.0640 0.7077 0.6713
1.000 0.3809 0.00603 0.00122 -0.0634 0.6452 0.6747
1.250 0.4026 0.00660 0.00140 -0.0624 0.5508 0.6780
1.500 0.4257 0.00710 0.00158 -0.0617 0.4741 0.6809
1.750 0.4487 0.00759 0.00176 -0.0610 0.3976 0.6840
2.000 0.4724 0.00802 0.00194 -0.0605 0.3331 0.6876
2.250 0.4979 0.00831 0.00207 -0.0602 0.2933 0.6913
2.500 0.5243 0.00852 0.00219 -0.0601 0.2680 0.6950
2.750 0.5505 0.00874 0.00231 -0.0600 0.2449 0.6985
3.000 0.5765 0.00896 0.00245 -0.0599 0.2195 0.7022
3.250 0.6024 0.00920 0.00260 -0.0597 0.1966 0.7060
3.500 0.6286 0.00941 0.00274 -0.0596 0.1793 0.7100
3.750 0.6546 0.00963 0.00290 -0.0594 0.1621 0.7140
4.000 0.6807 0.00983 0.00307 -0.0592 0.1477 0.7184
4.250 0.7069 0.01002 0.00323 -0.0591 0.1378 0.7231
4.500 0.7330 0.01022 0.00339 -0.0590 0.1283 0.7274
4.750 0.7592 0.01041 0.00358 -0.0588 0.1192 0.7317
5.000 0.7849 0.01062 0.00377 -0.0586 0.1095 0.7366
5.250 0.8103 0.01086 0.00397 -0.0584 0.0984 0.7419
5.500 0.8354 0.01112 0.00419 -0.0581 0.0867 0.7471
5.750 0.8601 0.01141 0.00444 -0.0577 0.0742 0.7529
6.000 0.8847 0.01171 0.00470 -0.0573 0.0638 0.7586
6.250 0.9090 0.01202 0.00498 -0.0569 0.0520 0.7642
6.500 0.9312 0.01253 0.00538 -0.0561 0.0317 0.7707
6.750 0.9548 0.01291 0.00574 -0.0556 0.0250 0.7772
7.000 0.9789 0.01321 0.00608 -0.0551 0.0221 0.7849
7.250 1.0031 0.01350 0.00640 -0.0546 0.0207 0.7925
7.500 1.0269 0.01382 0.00677 -0.0541 0.0194 0.8011
7.750 1.0501 0.01418 0.00717 -0.0535 0.0181 0.8095
8.000 1.0738 0.01448 0.00753 -0.0529 0.0175 0.8195
8.250 1.0971 0.01477 0.00790 -0.0523 0.0169 0.8311
8.500 1.1199 0.01508 0.00829 -0.0516 0.0162 0.8450
8.750 1.1419 0.01541 0.00870 -0.0508 0.0154 0.8622
9.000 1.1628 0.01577 0.00915 -0.0497 0.0147 0.8845
9.250 1.1806 0.01617 0.00968 -0.0480 0.0139 0.9179
9.500 1.1991 0.01640 0.01003 -0.0463 0.0136 1.0000
9.750 1.2204 0.01681 0.01049 -0.0454 0.0133 1.0000
10.000 1.2403 0.01724 0.01096 -0.0443 0.0129 1.0000
10.250 1.2597 0.01770 0.01146 -0.0431 0.0125 1.0000
10.500 1.2789 0.01818 0.01199 -0.0419 0.0121 1.0000
10.750 1.2976 0.01870 0.01254 -0.0406 0.0118 1.0000
11.000 1.3158 0.01925 0.01313 -0.0393 0.0114 1.0000
11.250 1.3330 0.01989 0.01380 -0.0379 0.0111 1.0000
11.500 1.3482 0.02066 0.01465 -0.0362 0.0107 1.0000
11.750 1.3648 0.02130 0.01535 -0.0348 0.0105 1.0000
12.000 1.3815 0.02193 0.01604 -0.0335 0.0103 1.0000
12.250 1.3974 0.02260 0.01678 -0.0320 0.0101 1.0000
12.500 1.4125 0.02333 0.01758 -0.0305 0.0099 1.0000
12.750 1.4265 0.02413 0.01845 -0.0289 0.0097 1.0000
13.000 1.4402 0.02495 0.01935 -0.0273 0.0095 1.0000
13.250 1.4531 0.02584 0.02031 -0.0257 0.0094 1.0000
13.500 1.4653 0.02677 0.02131 -0.0241 0.0092 1.0000
13.750 1.4769 0.02775 0.02237 -0.0224 0.0090 1.0000
14.000 1.4873 0.02882 0.02352 -0.0208 0.0089 1.0000
14.250 1.4967 0.02998 0.02475 -0.0190 0.0087 1.0000
14.500 1.5048 0.03126 0.02611 -0.0173 0.0086 1.0000
14.750 1.5112 0.03270 0.02763 -0.0155 0.0084 1.0000
15.000 1.5150 0.03436 0.02939 -0.0136 0.0083 1.0000
15.250 1.5152 0.03638 0.03152 -0.0116 0.0081 1.0000
15.500 1.5157 0.03844 0.03370 -0.0099 0.0080 1.0000
15.750 1.5195 0.04027 0.03563 -0.0086 0.0079 1.0000
16.000 1.5216 0.04232 0.03779 -0.0074 0.0078 1.0000
16.250 1.5220 0.04463 0.04022 -0.0063 0.0078 1.0000
16.500 1.5201 0.04726 0.04296 -0.0054 0.0077 1.0000
16.750 1.5162 0.05028 0.04611 -0.0048 0.0076 1.0000
17.000 1.5106 0.05374 0.04970 -0.0046 0.0076 1.0000
17.250 1.5031 0.05768 0.05378 -0.0050 0.0075 1.0000
17.500 1.4928 0.06230 0.05854 -0.0059 0.0075 1.0000
17.750 1.4793 0.06781 0.06420 -0.0078 0.0074 1.0000
18.000 1.4622 0.07443 0.07098 -0.0106 0.0074 1.0000
18.250 1.4393 0.08256 0.07929 -0.0147 0.0074 1.0000
18.500 1.4097 0.09232 0.08923 -0.0198 0.0074 1.0000
18.750 1.3746 0.10328 0.10038 -0.0255 0.0074 1.0000
19.000 1.3350 0.11494 0.11220 -0.0314 0.0075 1.0000
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