DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.2 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df101-il-1000000-n5.txt Download as CSV file: xf-df101-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DF 101 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7215 0.10930 0.10723 -0.0240 1.0000 0.0036
-15.000 -0.7454 0.10025 0.09810 -0.0284 1.0000 0.0035
-14.750 -0.7732 0.09093 0.08870 -0.0332 1.0000 0.0035
-14.500 -0.8059 0.08129 0.07898 -0.0384 1.0000 0.0034
-14.250 -0.8350 0.07255 0.07015 -0.0434 1.0000 0.0034
-14.000 -0.8806 0.06114 0.05861 -0.0504 1.0000 0.0034
-13.750 -0.9132 0.05131 0.04863 -0.0571 1.0000 0.0034
-13.500 -0.9361 0.04172 0.03885 -0.0657 1.0000 0.0034
-13.250 -0.9540 0.03509 0.03201 -0.0720 1.0000 0.0034
-13.000 -0.9731 0.03142 0.02815 -0.0721 1.0000 0.0034
-12.750 -0.9777 0.02980 0.02643 -0.0697 1.0000 0.0034
-12.500 -0.9821 0.02837 0.02488 -0.0664 1.0000 0.0034
-12.250 -0.9812 0.02679 0.02316 -0.0638 1.0000 0.0034
-12.000 -0.9756 0.02554 0.02180 -0.0614 1.0000 0.0034
-11.750 -0.9684 0.02443 0.02057 -0.0589 1.0000 0.0035
-11.500 -0.9507 0.02280 0.01876 -0.0589 0.9967 0.0035
-11.250 -0.9305 0.02102 0.01678 -0.0593 0.9906 0.0036
-11.000 -0.9057 0.01971 0.01531 -0.0601 0.9864 0.0037
-10.750 -0.8776 0.01868 0.01417 -0.0612 0.9834 0.0039
-10.500 -0.8511 0.01777 0.01316 -0.0617 0.9785 0.0040
-10.250 -0.8228 0.01697 0.01227 -0.0625 0.9738 0.0041
-10.000 -0.7934 0.01629 0.01149 -0.0635 0.9695 0.0042
-9.750 -0.7676 0.01570 0.01083 -0.0635 0.9627 0.0044
-9.500 -0.7408 0.01513 0.01018 -0.0637 0.9566 0.0046
-9.250 -0.7166 0.01462 0.00960 -0.0632 0.9494 0.0048
-9.000 -0.6921 0.01413 0.00902 -0.0628 0.9426 0.0050
-8.750 -0.6680 0.01369 0.00850 -0.0622 0.9358 0.0052
-8.500 -0.6441 0.01322 0.00794 -0.0616 0.9289 0.0053
-8.250 -0.6196 0.01282 0.00746 -0.0611 0.9225 0.0055
-8.000 -0.5957 0.01232 0.00687 -0.0604 0.9156 0.0057
-7.750 -0.5715 0.01183 0.00631 -0.0598 0.9092 0.0061
-7.500 -0.5465 0.01146 0.00588 -0.0593 0.9025 0.0064
-7.250 -0.5211 0.01113 0.00549 -0.0588 0.8962 0.0068
-7.000 -0.4954 0.01082 0.00513 -0.0584 0.8894 0.0073
-6.750 -0.4696 0.01054 0.00478 -0.0579 0.8828 0.0077
-6.500 -0.4435 0.01026 0.00446 -0.0576 0.8758 0.0082
-6.250 -0.4176 0.00998 0.00414 -0.0572 0.8687 0.0094
-6.000 -0.3911 0.00975 0.00388 -0.0569 0.8614 0.0108
-5.750 -0.3648 0.00952 0.00361 -0.0565 0.8536 0.0126
-5.500 -0.3381 0.00931 0.00338 -0.0563 0.8457 0.0145
-5.250 -0.3114 0.00913 0.00314 -0.0560 0.8376 0.0162
-5.000 -0.2847 0.00893 0.00291 -0.0557 0.8287 0.0185
-4.750 -0.2578 0.00878 0.00272 -0.0554 0.8200 0.0203
-4.500 -0.2312 0.00858 0.00250 -0.0551 0.8102 0.0244
-4.250 -0.2045 0.00839 0.00231 -0.0548 0.8004 0.0317
-4.000 -0.1783 0.00812 0.00208 -0.0545 0.7903 0.0503
-3.750 -0.1527 0.00780 0.00187 -0.0541 0.7795 0.0849
-3.500 -0.1266 0.00754 0.00170 -0.0538 0.7682 0.1175
-3.250 -0.1000 0.00737 0.00157 -0.0535 0.7565 0.1409
-3.000 -0.0732 0.00724 0.00146 -0.0532 0.7445 0.1629
-2.750 -0.0465 0.00713 0.00137 -0.0530 0.7319 0.1834
-2.500 -0.0197 0.00705 0.00130 -0.0527 0.7183 0.2035
-2.250 0.0070 0.00696 0.00123 -0.0524 0.7041 0.2261
-2.000 0.0339 0.00690 0.00117 -0.0522 0.6890 0.2447
-1.750 0.0608 0.00688 0.00113 -0.0519 0.6730 0.2588
-1.500 0.0877 0.00688 0.00108 -0.0517 0.6550 0.2700
-1.250 0.1144 0.00690 0.00105 -0.0514 0.6347 0.2831
-1.000 0.1412 0.00691 0.00102 -0.0511 0.6167 0.2963
-0.750 0.1682 0.00691 0.00100 -0.0509 0.6014 0.3117
-0.500 0.1952 0.00690 0.00099 -0.0507 0.5866 0.3289
-0.250 0.2221 0.00689 0.00098 -0.0504 0.5720 0.3489
0.000 0.2490 0.00688 0.00099 -0.0502 0.5571 0.3699
0.250 0.2757 0.00686 0.00099 -0.0500 0.5422 0.3975
0.500 0.3023 0.00684 0.00101 -0.0497 0.5262 0.4276
0.750 0.3286 0.00682 0.00103 -0.0494 0.5095 0.4637
1.000 0.3545 0.00677 0.00107 -0.0491 0.4925 0.5105
1.250 0.3803 0.00676 0.00112 -0.0487 0.4739 0.5556
1.500 0.4058 0.00675 0.00117 -0.0482 0.4538 0.6033
1.750 0.4311 0.00673 0.00124 -0.0477 0.4350 0.6538
2.000 0.4557 0.00673 0.00131 -0.0470 0.4139 0.7066
2.250 0.4788 0.00670 0.00141 -0.0461 0.3892 0.7739
2.500 0.5002 0.00664 0.00153 -0.0446 0.3674 0.8586
2.750 0.5244 0.00672 0.00168 -0.0436 0.3462 0.9150
3.000 0.5521 0.00692 0.00182 -0.0435 0.3218 0.9427
3.250 0.5833 0.00713 0.00195 -0.0443 0.2993 0.9589
3.500 0.6148 0.00735 0.00209 -0.0452 0.2806 0.9699
3.750 0.6489 0.00758 0.00223 -0.0467 0.2603 0.9766
4.000 0.6799 0.00779 0.00237 -0.0475 0.2452 0.9830
4.250 0.7146 0.00801 0.00253 -0.0491 0.2295 0.9868
4.500 0.7503 0.00823 0.00269 -0.0510 0.2168 0.9939
4.750 0.7936 0.00846 0.00287 -0.0545 0.2041 1.0000
5.250 0.8389 0.00882 0.00318 -0.0525 0.1867 1.0000
5.500 0.8616 0.00902 0.00335 -0.0515 0.1788 1.0000
5.750 0.8844 0.00922 0.00352 -0.0505 0.1703 1.0000
6.000 0.9072 0.00943 0.00371 -0.0496 0.1616 1.0000
6.250 0.9291 0.00971 0.00392 -0.0485 0.1476 1.0000
6.500 0.9512 0.00998 0.00414 -0.0475 0.1360 1.0000
6.750 0.9733 0.01027 0.00437 -0.0464 0.1251 1.0000
7.000 0.9953 0.01057 0.00463 -0.0454 0.1131 1.0000
7.250 1.0170 0.01090 0.00490 -0.0444 0.1007 1.0000
7.500 1.0388 0.01123 0.00519 -0.0433 0.0896 1.0000
7.750 1.0601 0.01161 0.00551 -0.0423 0.0776 1.0000
8.000 1.0804 0.01207 0.00589 -0.0410 0.0639 1.0000
8.250 1.1006 0.01253 0.00629 -0.0398 0.0516 1.0000
8.500 1.1202 0.01303 0.00672 -0.0385 0.0398 1.0000
8.750 1.1393 0.01356 0.00720 -0.0372 0.0292 1.0000
9.000 1.1577 0.01413 0.00772 -0.0357 0.0206 1.0000
9.250 1.1766 0.01464 0.00821 -0.0344 0.0157 1.0000
9.500 1.1962 0.01508 0.00868 -0.0331 0.0134 1.0000
9.750 1.2151 0.01556 0.00916 -0.0317 0.0119 1.0000
10.000 1.2336 0.01603 0.00966 -0.0303 0.0106 1.0000
10.250 1.2521 0.01647 0.01014 -0.0289 0.0101 1.0000
10.500 1.2685 0.01693 0.01064 -0.0271 0.0096 1.0000
10.750 1.2831 0.01742 0.01117 -0.0250 0.0092 1.0000
11.000 1.2971 0.01793 0.01173 -0.0229 0.0088 1.0000
11.250 1.3099 0.01853 0.01238 -0.0207 0.0084 1.0000
11.500 1.3215 0.01923 0.01313 -0.0184 0.0080 1.0000
11.750 1.3339 0.01989 0.01386 -0.0164 0.0078 1.0000
12.000 1.3474 0.02051 0.01453 -0.0146 0.0076 1.0000
12.250 1.3599 0.02119 0.01527 -0.0128 0.0073 1.0000
12.500 1.3725 0.02189 0.01602 -0.0111 0.0070 1.0000
12.750 1.3848 0.02263 0.01680 -0.0095 0.0065 1.0000
13.000 1.3936 0.02363 0.01790 -0.0075 0.0066 1.0000
13.250 1.4030 0.02462 0.01893 -0.0058 0.0062 1.0000
13.500 1.4114 0.02572 0.02009 -0.0042 0.0060 1.0000
13.750 1.4181 0.02699 0.02144 -0.0025 0.0058 1.0000
14.000 1.4222 0.02851 0.02303 -0.0009 0.0054 1.0000
14.250 1.4288 0.02992 0.02453 0.0003 0.0054 1.0000
14.500 1.4352 0.03141 0.02609 0.0014 0.0053 1.0000
14.750 1.4406 0.03304 0.02781 0.0024 0.0052 1.0000
15.000 1.4433 0.03501 0.02988 0.0033 0.0051 1.0000
15.250 1.4483 0.03684 0.03178 0.0039 0.0050 1.0000
15.500 1.4507 0.03902 0.03406 0.0043 0.0048 1.0000
15.750 1.4514 0.04148 0.03662 0.0045 0.0047 1.0000
16.000 1.4508 0.04418 0.03941 0.0046 0.0047 1.0000
16.250 1.4481 0.04726 0.04260 0.0043 0.0046 1.0000
16.500 1.4467 0.05033 0.04577 0.0038 0.0045 1.0000
16.750 1.4397 0.05425 0.04981 0.0029 0.0045 1.0000
17.000 1.4343 0.05813 0.05378 0.0018 0.0043 1.0000
17.250 1.4256 0.06264 0.05841 0.0003 0.0043 1.0000
17.500 1.4132 0.06788 0.06378 -0.0016 0.0043 1.0000
17.750 1.4025 0.07305 0.06907 -0.0037 0.0042 1.0000
18.000 1.3885 0.07897 0.07510 -0.0063 0.0041 1.0000
18.250 1.3718 0.08551 0.08177 -0.0093 0.0041 1.0000
18.500 1.3513 0.09295 0.08935 -0.0129 0.0041 1.0000
18.750 1.3304 0.10068 0.09722 -0.0168 0.0040 1.0000
19.000 1.3086 0.10876 0.10542 -0.0209 0.0040 1.0000
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Polar data table (+)
Polar graphs
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