DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-51 AIRFOIL (dae51-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.36 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae51-il-1000000.txt Download as CSV file: xf-dae51-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2599 0.09814 0.09661 -0.0394 0.9753 0.0116
-10.000 -0.2613 0.09312 0.09158 -0.0404 0.9620 0.0119
-9.000 -0.3580 0.09210 0.09054 -0.0355 0.9802 0.0119
-8.750 -0.3489 0.08914 0.08755 -0.0373 0.9590 0.0120
-8.500 -0.3441 0.08662 0.08498 -0.0377 0.9408 0.0122
-8.250 -0.3391 0.08389 0.08221 -0.0387 0.9266 0.0124
-8.000 -0.3338 0.08087 0.07915 -0.0403 0.9144 0.0126
-7.750 -0.3281 0.07754 0.07579 -0.0426 0.9033 0.0129
-7.500 -0.3210 0.07385 0.07207 -0.0462 0.8936 0.0134
-7.250 -0.3088 0.06908 0.06725 -0.0523 0.8848 0.0140
-7.000 -0.2855 0.06063 0.05875 -0.0656 0.8762 0.0152
-5.750 -0.1782 0.01518 0.01068 -0.0993 0.8448 0.0124
-5.500 -0.1510 0.01414 0.00944 -0.0994 0.8396 0.0128
-5.250 -0.1231 0.01328 0.00844 -0.0996 0.8344 0.0132
-5.000 -0.0952 0.01240 0.00740 -0.0997 0.8289 0.0135
-4.750 -0.0673 0.01165 0.00650 -0.0998 0.8238 0.0139
-4.500 -0.0389 0.01094 0.00568 -0.0999 0.8186 0.0142
-4.250 -0.0106 0.01034 0.00498 -0.1000 0.8132 0.0145
-4.000 0.0176 0.00987 0.00440 -0.1001 0.8080 0.0149
-3.750 0.0464 0.00962 0.00410 -0.1002 0.8025 0.0153
-3.500 0.0747 0.00877 0.00315 -0.1004 0.7971 0.0166
-3.250 0.1033 0.00849 0.00283 -0.1006 0.7918 0.0176
-3.000 0.1322 0.00825 0.00255 -0.1007 0.7859 0.0190
-2.750 0.1609 0.00806 0.00230 -0.1008 0.7802 0.0201
-2.500 0.1899 0.00773 0.00194 -0.1010 0.7745 0.0232
-2.250 0.2187 0.00761 0.00178 -0.1012 0.7684 0.0258
-2.000 0.2475 0.00741 0.00157 -0.1013 0.7626 0.0330
-1.750 0.2765 0.00719 0.00140 -0.1016 0.7560 0.0505
-1.500 0.3052 0.00698 0.00129 -0.1018 0.7496 0.0904
-1.250 0.3341 0.00669 0.00122 -0.1021 0.7427 0.1603
-1.000 0.3627 0.00643 0.00116 -0.1024 0.7358 0.2470
-0.750 0.3915 0.00614 0.00114 -0.1028 0.7285 0.3486
-0.500 0.4199 0.00586 0.00114 -0.1031 0.7209 0.4609
-0.250 0.4484 0.00559 0.00116 -0.1034 0.7129 0.5731
0.000 0.4763 0.00537 0.00119 -0.1034 0.7047 0.6834
0.250 0.5033 0.00512 0.00123 -0.1032 0.6958 0.7910
0.500 0.5273 0.00471 0.00119 -0.1019 0.6869 1.0000
0.750 0.5559 0.00478 0.00119 -0.1020 0.6770 1.0000
1.000 0.5846 0.00485 0.00120 -0.1022 0.6665 1.0000
1.250 0.6132 0.00493 0.00122 -0.1023 0.6558 1.0000
1.500 0.6416 0.00502 0.00124 -0.1024 0.6444 1.0000
1.750 0.6699 0.00512 0.00128 -0.1025 0.6321 1.0000
2.000 0.6983 0.00522 0.00133 -0.1026 0.6193 1.0000
2.250 0.7265 0.00533 0.00138 -0.1027 0.6060 1.0000
2.500 0.7546 0.00545 0.00144 -0.1027 0.5925 1.0000
2.750 0.7826 0.00558 0.00151 -0.1028 0.5785 1.0000
3.000 0.8106 0.00571 0.00160 -0.1029 0.5642 1.0000
3.250 0.8384 0.00586 0.00169 -0.1029 0.5495 1.0000
3.500 0.8661 0.00602 0.00179 -0.1029 0.5341 1.0000
3.750 0.8936 0.00619 0.00191 -0.1029 0.5177 1.0000
4.000 0.9209 0.00639 0.00203 -0.1029 0.4998 1.0000
4.250 0.9482 0.00658 0.00217 -0.1029 0.4810 1.0000
4.500 0.9750 0.00682 0.00232 -0.1028 0.4581 1.0000
4.750 1.0013 0.00711 0.00251 -0.1026 0.4295 1.0000
5.000 1.0277 0.00739 0.00269 -0.1025 0.4056 1.0000
5.250 1.0533 0.00775 0.00291 -0.1023 0.3736 1.0000
5.500 1.0779 0.00823 0.00320 -0.1019 0.3318 1.0000
5.750 1.1027 0.00866 0.00349 -0.1016 0.2985 1.0000
6.000 1.1271 0.00914 0.00380 -0.1012 0.2651 1.0000
6.250 1.1510 0.00966 0.00415 -0.1007 0.2291 1.0000
6.500 1.1745 0.01020 0.00453 -0.1003 0.1963 1.0000
6.750 1.1977 0.01076 0.00493 -0.0997 0.1642 1.0000
7.000 1.2200 0.01140 0.00539 -0.0991 0.1306 1.0000
7.250 1.2418 0.01207 0.00588 -0.0983 0.0999 1.0000
7.500 1.2634 0.01274 0.00640 -0.0975 0.0740 1.0000
7.750 1.2849 0.01338 0.00692 -0.0967 0.0544 1.0000
8.000 1.3068 0.01397 0.00744 -0.0960 0.0410 1.0000
8.250 1.3284 0.01455 0.00798 -0.0952 0.0316 1.0000
8.500 1.3496 0.01516 0.00856 -0.0943 0.0252 1.0000
8.750 1.3712 0.01567 0.00907 -0.0935 0.0221 1.0000
9.000 1.3914 0.01632 0.00974 -0.0924 0.0192 1.0000
9.250 1.4128 0.01680 0.01026 -0.0915 0.0178 1.0000
9.500 1.4323 0.01741 0.01089 -0.0904 0.0163 1.0000
9.750 1.4488 0.01826 0.01181 -0.0888 0.0147 1.0000
10.000 1.4685 0.01877 0.01236 -0.0878 0.0139 1.0000
10.250 1.4864 0.01937 0.01300 -0.0865 0.0130 1.0000
10.500 1.5006 0.02008 0.01376 -0.0845 0.0122 1.0000
10.750 1.5078 0.02122 0.01497 -0.0816 0.0113 1.0000
11.000 1.5180 0.02219 0.01603 -0.0793 0.0109 1.0000
11.250 1.5311 0.02299 0.01691 -0.0776 0.0106 1.0000
11.500 1.5427 0.02393 0.01792 -0.0757 0.0102 1.0000
11.750 1.5534 0.02498 0.01903 -0.0739 0.0098 1.0000
12.000 1.5634 0.02611 0.02023 -0.0722 0.0094 1.0000
12.250 1.5726 0.02734 0.02153 -0.0705 0.0091 1.0000
12.500 1.5795 0.02880 0.02306 -0.0687 0.0087 1.0000
12.750 1.5794 0.03092 0.02527 -0.0665 0.0084 1.0000
13.000 1.5723 0.03375 0.02826 -0.0641 0.0080 1.0000
13.250 1.5816 0.03519 0.02977 -0.0630 0.0079 1.0000
13.500 1.5876 0.03698 0.03167 -0.0618 0.0078 1.0000
13.750 1.5915 0.03899 0.03378 -0.0606 0.0076 1.0000
14.000 1.5941 0.04121 0.03610 -0.0595 0.0075 1.0000
14.250 1.5956 0.04362 0.03861 -0.0585 0.0073 1.0000
14.500 1.5959 0.04619 0.04129 -0.0577 0.0072 1.0000
14.750 1.5957 0.04891 0.04411 -0.0570 0.0070 1.0000
15.000 1.5939 0.05190 0.04721 -0.0565 0.0069 1.0000
15.250 1.5915 0.05507 0.05049 -0.0561 0.0068 1.0000
15.500 1.5889 0.05840 0.05392 -0.0561 0.0066 1.0000
15.750 1.5850 0.06203 0.05766 -0.0562 0.0065 1.0000
16.000 1.5806 0.06585 0.06158 -0.0566 0.0064 1.0000
16.250 1.5745 0.06999 0.06583 -0.0571 0.0063 1.0000
16.500 1.5670 0.07448 0.07043 -0.0579 0.0063 1.0000
16.750 1.5580 0.07932 0.07540 -0.0590 0.0062 1.0000
17.000 1.5475 0.08447 0.08066 -0.0603 0.0061 1.0000
17.250 1.5355 0.08997 0.08629 -0.0618 0.0061 1.0000
17.500 1.5226 0.09577 0.09221 -0.0636 0.0060 1.0000
17.750 1.5083 0.10193 0.09850 -0.0657 0.0060 1.0000
18.000 1.4928 0.10836 0.10505 -0.0681 0.0059 1.0000
18.250 1.4772 0.11497 0.11180 -0.0707 0.0059 1.0000
18.500 1.4619 0.12174 0.11870 -0.0736 0.0058 1.0000
18.750 1.4448 0.12895 0.12605 -0.0769 0.0058 1.0000
19.000 1.4298 0.13595 0.13318 -0.0803 0.0058 1.0000
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Polar data table (+)
Polar graphs
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