DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-51 AIRFOIL (dae51-il) Reynolds number: 500,000 Max Cl/Cd: 121.21 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae51-il-500000.txt Download as CSV file: xf-dae51-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: DAE-51 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3448 0.09821 0.09600 -0.0325 1.0000 0.0191
-8.750 -0.3423 0.09378 0.09161 -0.0375 1.0000 0.0198
-8.500 -0.3393 0.09013 0.08800 -0.0404 1.0000 0.0199
-8.250 -0.3270 0.08546 0.08334 -0.0459 0.9907 0.0199
-8.000 -0.3188 0.07926 0.07715 -0.0512 0.9797 0.0204
-7.750 -0.3039 0.07602 0.07390 -0.0542 0.9695 0.0207
-7.500 -0.2914 0.07300 0.07086 -0.0569 0.9573 0.0211
-7.250 -0.2807 0.06971 0.06754 -0.0601 0.9445 0.0215
-7.000 -0.2680 0.06600 0.06380 -0.0645 0.9332 0.0222
-6.750 -0.2522 0.06155 0.05929 -0.0704 0.9234 0.0232
-6.250 -0.1960 0.04573 0.04294 -0.0920 0.9054 0.0259
-6.000 -0.1829 0.03746 0.03435 -0.0972 0.8985 0.0267
-5.750 -0.1615 0.03521 0.03204 -0.0983 0.8918 0.0273
-5.500 -0.1388 0.03298 0.02966 -0.0994 0.8857 0.0280
-5.250 -0.1142 0.03045 0.02694 -0.1007 0.8800 0.0293
-5.000 -0.0860 0.02766 0.02375 -0.1017 0.8738 0.0324
-4.750 -0.0580 0.01692 0.01154 -0.1030 0.8691 0.0209
-4.500 -0.0301 0.01528 0.00960 -0.1031 0.8633 0.0207
-4.250 -0.0028 0.01432 0.00852 -0.1031 0.8576 0.0216
-4.000 0.0246 0.01366 0.00774 -0.1030 0.8527 0.0226
-3.750 0.0528 0.01267 0.00661 -0.1030 0.8466 0.0230
-3.500 0.0807 0.01187 0.00570 -0.1029 0.8411 0.0238
-3.250 0.1088 0.01127 0.00499 -0.1028 0.8358 0.0248
-3.000 0.1371 0.01084 0.00449 -0.1027 0.8296 0.0260
-2.750 0.1650 0.01007 0.00365 -0.1028 0.8244 0.0288
-2.500 0.1936 0.00985 0.00341 -0.1029 0.8182 0.0326
-2.250 0.2221 0.00940 0.00292 -0.1029 0.8122 0.0381
-2.000 0.2507 0.00910 0.00260 -0.1030 0.8065 0.0487
-1.750 0.2794 0.00872 0.00233 -0.1032 0.7999 0.0850
-1.500 0.3076 0.00823 0.00217 -0.1035 0.7942 0.1980
-1.250 0.3359 0.00776 0.00213 -0.1039 0.7873 0.3384
-1.000 0.3637 0.00734 0.00210 -0.1041 0.7809 0.4780
-0.750 0.3911 0.00696 0.00212 -0.1041 0.7740 0.6196
-0.500 0.4165 0.00658 0.00213 -0.1034 0.7670 0.7572
-0.250 0.4369 0.00611 0.00208 -0.1011 0.7600 0.9419
0.000 0.4693 0.00610 0.00198 -0.1020 0.7523 1.0000
0.250 0.4980 0.00614 0.00195 -0.1021 0.7445 1.0000
0.500 0.5265 0.00620 0.00191 -0.1021 0.7364 1.0000
0.750 0.5550 0.00624 0.00190 -0.1022 0.7275 1.0000
1.000 0.5833 0.00632 0.00188 -0.1022 0.7192 1.0000
1.250 0.6117 0.00637 0.00189 -0.1023 0.7093 1.0000
1.500 0.6400 0.00644 0.00191 -0.1023 0.6995 1.0000
1.750 0.6681 0.00653 0.00192 -0.1023 0.6897 1.0000
2.000 0.6963 0.00660 0.00196 -0.1024 0.6785 1.0000
2.250 0.7243 0.00669 0.00201 -0.1024 0.6671 1.0000
2.500 0.7523 0.00679 0.00206 -0.1024 0.6554 1.0000
2.750 0.7801 0.00690 0.00212 -0.1023 0.6432 1.0000
3.000 0.8077 0.00702 0.00220 -0.1023 0.6303 1.0000
3.250 0.8353 0.00716 0.00229 -0.1022 0.6168 1.0000
3.500 0.8627 0.00731 0.00239 -0.1021 0.6026 1.0000
3.750 0.8900 0.00746 0.00250 -0.1021 0.5878 1.0000
4.000 0.9171 0.00763 0.00264 -0.1020 0.5726 1.0000
4.250 0.9441 0.00781 0.00279 -0.1018 0.5563 1.0000
4.500 0.9709 0.00801 0.00294 -0.1017 0.5386 1.0000
4.750 0.9974 0.00823 0.00313 -0.1015 0.5195 1.0000
5.000 1.0235 0.00849 0.00332 -0.1012 0.4982 1.0000
5.250 1.0490 0.00879 0.00353 -0.1009 0.4720 1.0000
5.500 1.0746 0.00909 0.00376 -0.1006 0.4467 1.0000
5.750 1.0995 0.00945 0.00404 -0.1002 0.4183 1.0000
6.000 1.1230 0.00993 0.00436 -0.0996 0.3800 1.0000
6.250 1.1462 0.01047 0.00472 -0.0991 0.3408 1.0000
6.500 1.1692 0.01101 0.00511 -0.0985 0.3050 1.0000
6.750 1.1912 0.01165 0.00557 -0.0977 0.2662 1.0000
7.000 1.2126 0.01235 0.00608 -0.0970 0.2258 1.0000
7.250 1.2335 0.01308 0.00662 -0.0961 0.1878 1.0000
7.500 1.2533 0.01389 0.00722 -0.0951 0.1499 1.0000
7.750 1.2720 0.01479 0.00791 -0.0940 0.1123 1.0000
8.000 1.2898 0.01573 0.00865 -0.0927 0.0792 1.0000
8.250 1.3071 0.01669 0.00946 -0.0914 0.0553 1.0000
8.500 1.3244 0.01761 0.01030 -0.0899 0.0414 1.0000
8.750 1.3403 0.01860 0.01127 -0.0883 0.0334 1.0000
9.000 1.3594 0.01924 0.01199 -0.0871 0.0300 1.0000
9.250 1.3729 0.02031 0.01307 -0.0851 0.0264 1.0000
9.500 1.3882 0.02111 0.01396 -0.0833 0.0244 1.0000
9.750 1.4017 0.02187 0.01478 -0.0813 0.0226 1.0000
10.000 1.4121 0.02288 0.01584 -0.0790 0.0211 1.0000
10.250 1.4118 0.02470 0.01777 -0.0755 0.0196 1.0000
10.500 1.4238 0.02569 0.01886 -0.0737 0.0189 1.0000
10.750 1.4336 0.02688 0.02014 -0.0718 0.0181 1.0000
11.000 1.4427 0.02816 0.02151 -0.0700 0.0172 1.0000
11.250 1.4512 0.02953 0.02294 -0.0682 0.0164 1.0000
11.500 1.4563 0.03123 0.02470 -0.0664 0.0157 1.0000
11.750 1.4521 0.03385 0.02743 -0.0638 0.0150 1.0000
12.000 1.4557 0.03586 0.02955 -0.0620 0.0146 1.0000
12.250 1.4623 0.03761 0.03144 -0.0606 0.0142 1.0000
12.500 1.4673 0.03956 0.03350 -0.0592 0.0138 1.0000
12.750 1.4714 0.04165 0.03570 -0.0578 0.0134 1.0000
13.000 1.4746 0.04387 0.03804 -0.0565 0.0131 1.0000
13.250 1.4772 0.04618 0.04047 -0.0554 0.0128 1.0000
13.500 1.4791 0.04862 0.04301 -0.0544 0.0125 1.0000
13.750 1.4802 0.05119 0.04568 -0.0535 0.0122 1.0000
14.000 1.4802 0.05390 0.04849 -0.0527 0.0119 1.0000
14.250 1.4785 0.05688 0.05156 -0.0519 0.0117 1.0000
14.500 1.4736 0.06032 0.05512 -0.0510 0.0114 1.0000
14.750 1.4623 0.06476 0.05974 -0.0495 0.0111 1.0000
15.000 1.4591 0.06825 0.06341 -0.0498 0.0110 1.0000
15.250 1.4545 0.07209 0.06743 -0.0503 0.0108 1.0000
15.500 1.4482 0.07629 0.07180 -0.0509 0.0107 1.0000
15.750 1.4401 0.08089 0.07658 -0.0518 0.0106 1.0000
16.000 1.4307 0.08588 0.08175 -0.0530 0.0105 1.0000
16.250 1.4195 0.09132 0.08738 -0.0546 0.0104 1.0000
16.500 1.4069 0.09716 0.09340 -0.0567 0.0104 1.0000
16.750 1.3930 0.10346 0.09988 -0.0591 0.0103 1.0000
17.000 1.3779 0.11024 0.10684 -0.0621 0.0103 1.0000
17.250 1.3619 0.11748 0.11427 -0.0657 0.0103 1.0000
17.500 1.3448 0.12521 0.12218 -0.0698 0.0103 1.0000
17.750 1.3263 0.13360 0.13075 -0.0745 0.0103 1.0000
18.000 1.3073 0.14259 0.13991 -0.0800 0.0103 1.0000
18.250 1.2874 0.15230 0.14979 -0.0861 0.0104 1.0000
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