DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 200,000 Max Cl/Cd: 53.84 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du8608418-il-200000-n5.txt Download as CSV file: xf-du8608418-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5469 0.09444 0.09118 -0.0135 0.9783 0.0096
-9.500 -0.5454 0.08866 0.08540 -0.0181 0.9481 0.0095
-9.250 -0.5428 0.08302 0.07976 -0.0231 0.9396 0.0093
-9.000 -0.5432 0.07691 0.07365 -0.0287 0.9327 0.0091
-8.750 -0.5487 0.06985 0.06657 -0.0363 0.9261 0.0090
-8.500 -0.5584 0.06384 0.06047 -0.0403 0.9207 0.0089
-8.250 -0.5660 0.05863 0.05513 -0.0421 0.9171 0.0088
-8.000 -0.5704 0.05337 0.04966 -0.0429 0.9141 0.0086
-7.750 -0.5712 0.04847 0.04452 -0.0429 0.9113 0.0084
-7.500 -0.5695 0.04341 0.03913 -0.0422 0.9091 0.0083
-7.250 -0.5638 0.03876 0.03408 -0.0411 0.9073 0.0081
-7.000 -0.5547 0.03440 0.02924 -0.0397 0.9057 0.0081
-6.750 -0.5418 0.03046 0.02476 -0.0382 0.9040 0.0082
-6.500 -0.5246 0.02732 0.02110 -0.0368 0.9024 0.0083
-6.250 -0.5042 0.02467 0.01791 -0.0357 0.9014 0.0087
-6.000 -0.4814 0.02252 0.01535 -0.0349 0.9005 0.0091
-5.750 -0.4569 0.02105 0.01358 -0.0343 0.8995 0.0102
-5.500 -0.4335 0.01987 0.01230 -0.0341 0.8982 0.0122
-5.250 -0.4085 0.01859 0.01085 -0.0336 0.8970 0.0133
-5.000 -0.3837 0.01738 0.00949 -0.0330 0.8960 0.0145
-4.750 -0.3591 0.01642 0.00840 -0.0324 0.8947 0.0159
-4.500 -0.3352 0.01550 0.00739 -0.0319 0.8933 0.0191
-4.250 -0.3101 0.01486 0.00664 -0.0315 0.8921 0.0231
-4.000 -0.2848 0.01426 0.00590 -0.0310 0.8907 0.0282
-3.750 -0.2597 0.01367 0.00532 -0.0305 0.8894 0.0439
-3.500 -0.2360 0.01295 0.00494 -0.0302 0.8880 0.1092
-3.250 -0.2121 0.01233 0.00467 -0.0299 0.8865 0.1971
-3.000 -0.1888 0.01169 0.00447 -0.0295 0.8847 0.3050
-2.750 -0.1667 0.01105 0.00428 -0.0289 0.8826 0.4258
-2.500 -0.1459 0.01040 0.00415 -0.0277 0.8805 0.5562
-2.250 -0.1277 0.00984 0.00433 -0.0250 0.8784 0.7268
-2.000 -0.1018 0.01027 0.00499 -0.0227 0.8768 0.8418
-1.750 -0.0821 0.01046 0.00505 -0.0209 0.8744 0.8759
-1.500 -0.0580 0.01065 0.00514 -0.0196 0.8717 0.8942
-1.250 -0.0331 0.01079 0.00522 -0.0186 0.8684 0.9083
-1.000 -0.0066 0.01090 0.00525 -0.0179 0.8651 0.9199
-0.750 0.0202 0.01098 0.00526 -0.0173 0.8618 0.9302
-0.500 0.0523 0.01104 0.00524 -0.0178 0.8582 0.9383
-0.250 0.0846 0.01107 0.00523 -0.0186 0.8533 0.9456
0.000 0.1187 0.01109 0.00520 -0.0196 0.8489 0.9523
0.250 0.1565 0.01111 0.00518 -0.0214 0.8444 0.9583
0.500 0.1977 0.01108 0.00513 -0.0241 0.8380 0.9638
0.750 0.2382 0.01105 0.00507 -0.0264 0.8316 0.9708
1.000 0.2809 0.01096 0.00497 -0.0293 0.8228 0.9777
1.250 0.3151 0.01088 0.00492 -0.0306 0.8137 0.9830
1.500 0.3464 0.01077 0.00483 -0.0312 0.8055 0.9853
1.750 0.3754 0.01065 0.00474 -0.0314 0.7960 0.9875
2.000 0.4035 0.01050 0.00468 -0.0316 0.7842 0.9896
2.250 0.4314 0.01036 0.00467 -0.0317 0.7674 0.9916
2.500 0.4590 0.01018 0.00460 -0.0318 0.7422 0.9934
2.750 0.4854 0.00978 0.00418 -0.0309 0.7039 0.9950
3.000 0.5083 0.00946 0.00350 -0.0290 0.6316 0.9967
3.250 0.5298 0.00984 0.00339 -0.0276 0.5358 0.9983
3.500 0.5512 0.01046 0.00362 -0.0266 0.4431 0.9996
3.750 0.5712 0.01102 0.00388 -0.0254 0.3713 1.0000
4.000 0.5903 0.01156 0.00417 -0.0241 0.3086 1.0000
4.250 0.6095 0.01211 0.00450 -0.0229 0.2540 1.0000
4.500 0.6289 0.01262 0.00483 -0.0216 0.2103 1.0000
4.750 0.6484 0.01310 0.00519 -0.0204 0.1735 1.0000
5.000 0.6681 0.01355 0.00561 -0.0191 0.1457 1.0000
5.250 0.6873 0.01402 0.00601 -0.0178 0.1200 1.0000
5.500 0.7060 0.01453 0.00645 -0.0164 0.0973 1.0000
5.750 0.7246 0.01503 0.00693 -0.0149 0.0805 1.0000
6.000 0.7427 0.01554 0.00747 -0.0134 0.0688 1.0000
6.250 0.7602 0.01611 0.00806 -0.0117 0.0592 1.0000
6.500 0.7771 0.01668 0.00862 -0.0099 0.0483 1.0000
6.750 0.7943 0.01723 0.00923 -0.0083 0.0388 1.0000
7.000 0.8116 0.01776 0.00984 -0.0066 0.0308 1.0000
7.250 0.8277 0.01851 0.01063 -0.0048 0.0244 1.0000
7.500 0.8448 0.01934 0.01156 -0.0031 0.0193 1.0000
7.750 0.8603 0.02060 0.01293 -0.0013 0.0160 1.0000
8.000 0.8801 0.02136 0.01381 -0.0003 0.0130 1.0000
8.250 0.8986 0.02240 0.01495 0.0007 0.0112 1.0000
8.500 0.9128 0.02426 0.01699 0.0023 0.0099 1.0000
8.750 0.9300 0.02586 0.01882 0.0036 0.0093 1.0000
9.000 0.9461 0.02777 0.02106 0.0049 0.0087 1.0000
9.250 0.9614 0.02970 0.02327 0.0062 0.0080 1.0000
9.500 0.9776 0.03081 0.02455 0.0071 0.0070 1.0000
9.750 0.9904 0.03208 0.02593 0.0081 0.0061 1.0000
10.250 0.9977 0.03753 0.03205 0.0120 0.0056 1.0000
10.500 0.9947 0.04022 0.03507 0.0145 0.0055 1.0000
10.750 0.9874 0.04323 0.03840 0.0166 0.0053 1.0000
11.000 0.9776 0.04649 0.04193 0.0181 0.0053 1.0000
11.250 0.9641 0.05029 0.04598 0.0189 0.0054 1.0000
11.500 0.9469 0.05486 0.05083 0.0187 0.0052 1.0000
11.750 0.9296 0.05997 0.05615 0.0170 0.0053 1.0000
12.000 0.9112 0.06625 0.06263 0.0133 0.0053 1.0000
12.250 0.8921 0.07423 0.07077 0.0074 0.0054 1.0000
12.500 0.8703 0.08524 0.08193 -0.0008 0.0055 1.0000
12.750 0.8521 0.09537 0.09211 -0.0073 0.0057 1.0000
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Polar data table (+)
Polar graphs
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