DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 100,000 Max Cl/Cd: 53.62 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du84132v-il-100000.txt Download as CSV file: xf-du84132v-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3719 0.10064 0.09577 -0.0359 1.0000 0.1533
-8.750 -0.3811 0.09861 0.09382 -0.0346 1.0000 0.1576
-8.500 -0.4638 0.09780 0.09327 -0.0359 1.0000 0.1624
-8.250 -0.4478 0.09383 0.08932 -0.0334 1.0000 0.1645
-8.000 -0.4273 0.09165 0.08714 -0.0302 1.0000 0.1670
-7.750 -0.4298 0.08986 0.08541 -0.0276 1.0000 0.1703
-7.500 -0.4503 0.08813 0.08377 -0.0254 1.0000 0.1743
-7.250 -0.5717 0.08400 0.07973 -0.0314 1.0000 0.1800
-7.000 -0.5394 0.08173 0.07760 -0.0258 1.0000 0.1818
-6.750 -0.5277 0.08037 0.07630 -0.0216 1.0000 0.1844
-6.500 -0.5339 0.07806 0.07402 -0.0204 1.0000 0.1888
-6.250 -0.5627 0.07324 0.06915 -0.0238 1.0000 0.1988
-6.000 -0.5473 0.04407 0.03740 -0.0475 0.9932 0.0865
-5.750 -0.5155 0.03996 0.03291 -0.0503 0.9879 0.0816
-5.500 -0.4751 0.03697 0.02877 -0.0534 0.9825 0.0764
-5.250 -0.4410 0.03490 0.02636 -0.0555 0.9767 0.0764
-5.000 -0.4057 0.03287 0.02405 -0.0576 0.9710 0.0768
-4.750 -0.3669 0.03133 0.02227 -0.0599 0.9662 0.0770
-4.500 -0.3365 0.03000 0.02080 -0.0607 0.9589 0.0773
-4.250 -0.2979 0.02878 0.01954 -0.0628 0.9539 0.0785
-4.000 -0.2678 0.02788 0.01865 -0.0635 0.9467 0.0805
-3.750 -0.2324 0.02711 0.01788 -0.0650 0.9404 0.0837
-3.500 -0.1969 0.02651 0.01721 -0.0664 0.9343 0.0883
-3.250 -0.1670 0.02561 0.01650 -0.0673 0.9264 0.0976
-3.000 -0.1244 0.02469 0.01583 -0.0703 0.9217 0.1302
-2.750 -0.1058 0.02256 0.01536 -0.0699 0.9128 0.4054
-2.500 -0.0825 0.02239 0.01635 -0.0674 0.9067 0.6157
-2.250 -0.0663 0.02322 0.01724 -0.0640 0.8960 0.7037
-2.000 -0.0360 0.02425 0.01818 -0.0621 0.8896 0.7608
-1.750 -0.0253 0.02476 0.01863 -0.0578 0.8781 0.7907
-1.500 0.0053 0.02484 0.01861 -0.0565 0.8728 0.8196
-1.250 0.0127 0.02490 0.01861 -0.0520 0.8610 0.8443
-1.000 0.0283 0.02467 0.01833 -0.0481 0.8530 0.8688
-0.750 0.0468 0.02442 0.01800 -0.0454 0.8441 0.8903
-0.500 0.0653 0.02421 0.01772 -0.0428 0.8354 0.9108
-0.250 0.0974 0.02396 0.01739 -0.0426 0.8286 0.9349
0.000 0.1905 0.02371 0.01700 -0.0531 0.8271 0.9592
0.250 0.3377 0.02278 0.01586 -0.0736 0.8280 0.9740
0.500 0.4235 0.02181 0.01478 -0.0838 0.8257 0.9808
0.750 0.4700 0.02163 0.01456 -0.0880 0.8158 0.9881
1.000 0.5306 0.02093 0.01380 -0.0940 0.8114 0.9927
1.250 0.5741 0.02069 0.01354 -0.0975 0.8017 0.9990
1.500 0.6190 0.02008 0.01289 -0.1004 0.7954 1.0000
1.750 0.6305 0.02015 0.01295 -0.0977 0.7831 1.0000
2.000 0.6510 0.02001 0.01281 -0.0964 0.7727 1.0000
2.250 0.6921 0.01938 0.01213 -0.0984 0.7656 1.0000
2.500 0.7103 0.01932 0.01206 -0.0966 0.7541 1.0000
2.750 0.7278 0.01929 0.01204 -0.0947 0.7422 1.0000
3.000 0.7456 0.01925 0.01200 -0.0928 0.7301 1.0000
3.250 0.7679 0.01910 0.01184 -0.0916 0.7183 1.0000
3.500 0.7932 0.01890 0.01163 -0.0909 0.7064 1.0000
3.750 0.8127 0.01883 0.01155 -0.0891 0.6931 1.0000
4.000 0.8284 0.01879 0.01150 -0.0867 0.6785 1.0000
4.250 0.8487 0.01865 0.01134 -0.0850 0.6636 1.0000
4.500 0.8656 0.01861 0.01128 -0.0828 0.6476 1.0000
4.750 0.8832 0.01857 0.01122 -0.0807 0.6309 1.0000
5.000 0.9067 0.01848 0.01106 -0.0795 0.6135 1.0000
5.250 0.9303 0.01848 0.01099 -0.0785 0.5948 1.0000
5.500 0.9490 0.01864 0.01113 -0.0768 0.5750 1.0000
5.750 0.9726 0.01884 0.01129 -0.0761 0.5562 1.0000
6.000 0.9964 0.01913 0.01155 -0.0755 0.5378 1.0000
6.250 1.0208 0.01946 0.01186 -0.0750 0.5202 1.0000
6.500 1.0453 0.01980 0.01216 -0.0745 0.5030 1.0000
6.750 1.0687 0.02017 0.01250 -0.0739 0.4856 1.0000
7.000 1.0899 0.02051 0.01284 -0.0729 0.4677 1.0000
7.250 1.1110 0.02080 0.01315 -0.0719 0.4508 1.0000
7.500 1.1336 0.02114 0.01345 -0.0712 0.4353 1.0000
7.750 1.1547 0.02156 0.01385 -0.0703 0.4188 1.0000
8.000 1.1753 0.02203 0.01428 -0.0693 0.4025 1.0000
8.250 1.1968 0.02259 0.01478 -0.0685 0.3864 1.0000
8.500 1.2167 0.02324 0.01541 -0.0675 0.3697 1.0000
8.750 1.2338 0.02390 0.01610 -0.0660 0.3528 1.0000
9.000 1.2475 0.02453 0.01681 -0.0640 0.3353 1.0000
9.250 1.2575 0.02517 0.01750 -0.0614 0.3166 1.0000
9.500 1.2642 0.02589 0.01822 -0.0583 0.2967 1.0000
9.750 1.2691 0.02677 0.01907 -0.0551 0.2756 1.0000
10.000 1.2751 0.02783 0.01998 -0.0522 0.2550 1.0000
10.250 1.2789 0.02905 0.02121 -0.0492 0.2338 1.0000
10.500 1.2833 0.03024 0.02239 -0.0465 0.2160 1.0000
10.750 1.2890 0.03147 0.02358 -0.0441 0.2012 1.0000
11.000 1.2954 0.03281 0.02486 -0.0421 0.1882 1.0000
11.250 1.3019 0.03425 0.02624 -0.0401 0.1763 1.0000
11.500 1.3086 0.03576 0.02766 -0.0384 0.1653 1.0000
11.750 1.3146 0.03735 0.02934 -0.0367 0.1551 1.0000
12.000 1.3241 0.03910 0.03104 -0.0354 0.1453 1.0000
12.250 1.3380 0.04096 0.03279 -0.0345 0.1353 1.0000
12.500 1.3490 0.04281 0.03463 -0.0335 0.1263 1.0000
12.750 1.3545 0.04489 0.03690 -0.0320 0.1189 1.0000
13.000 1.3719 0.04664 0.03849 -0.0316 0.1113 1.0000
13.250 1.3725 0.04892 0.04110 -0.0299 0.1062 1.0000
13.500 1.3977 0.05074 0.04269 -0.0300 0.0988 1.0000
13.750 1.3929 0.05343 0.04575 -0.0282 0.0951 1.0000
14.000 1.3973 0.05587 0.04832 -0.0272 0.0906 1.0000
14.250 1.4222 0.05866 0.05105 -0.0274 0.0851 1.0000
14.500 1.4131 0.06194 0.05468 -0.0259 0.0832 1.0000
14.750 1.4052 0.06546 0.05851 -0.0249 0.0812 1.0000
15.000 1.3988 0.06903 0.06234 -0.0242 0.0792 1.0000
15.250 1.3918 0.07268 0.06618 -0.0239 0.0773 1.0000
15.750 1.3930 0.08072 0.07440 -0.0240 0.0729 1.0000
16.000 1.3684 0.08599 0.07999 -0.0246 0.0726 1.0000
16.250 1.3416 0.09199 0.08629 -0.0261 0.0724 1.0000
16.500 1.3131 0.09878 0.09336 -0.0285 0.0724 1.0000
16.750 1.2824 0.10651 0.10135 -0.0320 0.0725 1.0000
17.000 1.2491 0.11540 0.11047 -0.0366 0.0728 1.0000
17.250 1.2143 0.12548 0.12073 -0.0424 0.0732 1.0000
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