DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 200,000 Max Cl/Cd: 63.73 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du8608418-il-200000.txt Download as CSV file: xf-du8608418-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DU86-084/18 8.44%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5341 0.08920 0.08606 -0.0188 1.0000 0.0397
-8.750 -0.5349 0.08480 0.08170 -0.0218 1.0000 0.0407
-8.500 -0.5385 0.07996 0.07691 -0.0260 1.0000 0.0417
-8.250 -0.5471 0.07477 0.07175 -0.0309 1.0000 0.0419
-8.000 -0.5554 0.07033 0.06729 -0.0336 1.0000 0.0424
-7.750 -0.5627 0.06568 0.06255 -0.0355 1.0000 0.0439
-7.500 -0.5750 0.06236 0.05910 -0.0344 1.0000 0.0452
-7.250 -0.5952 0.06135 0.05774 -0.0302 1.0000 0.0467
-5.500 -0.5225 0.03115 0.02509 -0.0233 0.9861 0.0355
-5.250 -0.4971 0.02791 0.02159 -0.0232 0.9845 0.0333
-5.000 -0.4720 0.02401 0.01721 -0.0227 0.9831 0.0304
-4.750 -0.4471 0.02152 0.01429 -0.0217 0.9815 0.0288
-4.500 -0.4216 0.01961 0.01208 -0.0208 0.9798 0.0285
-4.250 -0.3955 0.01819 0.01049 -0.0202 0.9780 0.0295
-4.000 -0.3685 0.01701 0.00921 -0.0199 0.9761 0.0322
-3.750 -0.3419 0.01583 0.00796 -0.0198 0.9743 0.0383
-3.500 -0.3135 0.01481 0.00692 -0.0200 0.9723 0.0504
-3.250 -0.2866 0.01318 0.00598 -0.0204 0.9706 0.1726
-3.000 -0.2662 0.01192 0.00578 -0.0200 0.9682 0.4054
-2.750 -0.2523 0.01086 0.00571 -0.0175 0.9649 0.6236
-2.500 -0.2396 0.01114 0.00676 -0.0119 0.9618 0.8566
-2.250 -0.2204 0.01168 0.00716 -0.0089 0.9583 0.9157
-2.000 -0.1621 0.01223 0.00754 -0.0132 0.9592 0.9523
-1.750 -0.0603 0.01236 0.00739 -0.0275 0.9647 0.9717
-1.500 0.0193 0.01217 0.00703 -0.0380 0.9675 0.9845
-1.250 0.0900 0.01185 0.00660 -0.0469 0.9691 0.9947
-1.000 0.1424 0.01158 0.00623 -0.0524 0.9674 1.0000
-0.750 0.1809 0.01146 0.00606 -0.0550 0.9626 1.0000
-0.500 0.2259 0.01127 0.00583 -0.0588 0.9584 1.0000
-0.250 0.2655 0.01114 0.00568 -0.0614 0.9527 1.0000
0.000 0.3009 0.01103 0.00555 -0.0631 0.9450 1.0000
0.250 0.3296 0.01100 0.00552 -0.0632 0.9352 1.0000
0.500 0.3537 0.01103 0.00555 -0.0622 0.9244 1.0000
0.750 0.3742 0.01110 0.00563 -0.0604 0.9133 1.0000
1.000 0.3924 0.01120 0.00572 -0.0582 0.9024 1.0000
1.250 0.4101 0.01130 0.00584 -0.0559 0.8913 1.0000
1.500 0.4280 0.01139 0.00596 -0.0536 0.8804 1.0000
1.750 0.4458 0.01145 0.00604 -0.0511 0.8694 1.0000
2.000 0.4636 0.01149 0.00613 -0.0485 0.8580 1.0000
2.250 0.4814 0.01150 0.00615 -0.0458 0.8459 1.0000
2.500 0.4996 0.01148 0.00617 -0.0433 0.8328 1.0000
2.750 0.5181 0.01141 0.00616 -0.0409 0.8179 1.0000
3.000 0.5371 0.01124 0.00606 -0.0386 0.8011 1.0000
3.250 0.5568 0.01092 0.00585 -0.0363 0.7823 1.0000
3.500 0.5775 0.01055 0.00565 -0.0347 0.7494 1.0000
3.750 0.5972 0.00994 0.00504 -0.0320 0.7029 1.0000
4.000 0.6131 0.00962 0.00425 -0.0281 0.6082 1.0000
4.250 0.6272 0.01033 0.00434 -0.0252 0.4911 1.0000
4.500 0.6419 0.01118 0.00471 -0.0230 0.3882 1.0000
4.750 0.6573 0.01202 0.00517 -0.0211 0.3025 1.0000
5.000 0.6736 0.01280 0.00564 -0.0194 0.2355 1.0000
5.250 0.6903 0.01355 0.00616 -0.0177 0.1849 1.0000
5.500 0.7066 0.01434 0.00676 -0.0159 0.1439 1.0000
5.750 0.7227 0.01513 0.00740 -0.0141 0.1141 1.0000
6.000 0.7377 0.01603 0.00818 -0.0120 0.0947 1.0000
6.250 0.7533 0.01687 0.00902 -0.0099 0.0809 1.0000
6.500 0.7694 0.01758 0.00979 -0.0080 0.0675 1.0000
6.750 0.7846 0.01846 0.01067 -0.0060 0.0557 1.0000
7.000 0.7995 0.01948 0.01171 -0.0039 0.0439 1.0000
7.250 0.8149 0.02082 0.01309 -0.0019 0.0342 1.0000
7.500 0.8339 0.02232 0.01478 -0.0002 0.0294 1.0000
7.750 0.8523 0.02345 0.01594 0.0009 0.0245 1.0000
8.000 0.8708 0.02636 0.01912 0.0023 0.0223 1.0000
8.250 0.8904 0.02863 0.02173 0.0037 0.0212 1.0000
8.500 0.9070 0.03150 0.02502 0.0052 0.0206 1.0000
8.750 0.9192 0.03496 0.02901 0.0070 0.0204 1.0000
9.000 0.9257 0.03898 0.03352 0.0091 0.0206 1.0000
9.250 0.9268 0.04330 0.03829 0.0112 0.0210 1.0000
9.500 0.9218 0.04781 0.04319 0.0134 0.0215 1.0000
9.750 0.9105 0.05244 0.04814 0.0155 0.0220 1.0000
10.000 0.8937 0.05664 0.05256 0.0177 0.0224 1.0000
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Polar data table (+)
Polar graphs
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