DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 50,000 Max Cl/Cd: 31.29 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du8608418-il-50000-n5.txt Download as CSV file: xf-du8608418-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5486 0.10283 0.09627 -0.0170 1.0000 0.0384
-9.250 -0.5440 0.09406 0.08751 -0.0203 1.0000 0.0372
-9.000 -0.5443 0.08932 0.08283 -0.0231 1.0000 0.0366
-8.750 -0.5468 0.08422 0.07778 -0.0268 1.0000 0.0361
-8.500 -0.5519 0.07925 0.07286 -0.0301 1.0000 0.0357
-8.250 -0.5588 0.07488 0.06849 -0.0319 1.0000 0.0352
-8.000 -0.5643 0.07037 0.06393 -0.0335 1.0000 0.0347
-7.750 -0.5684 0.06607 0.05954 -0.0344 1.0000 0.0342
-7.500 -0.5716 0.06181 0.05513 -0.0346 1.0000 0.0339
-7.250 -0.5731 0.05782 0.05093 -0.0341 1.0000 0.0336
-7.000 -0.5735 0.05412 0.04697 -0.0328 1.0000 0.0334
-6.750 -0.5735 0.05077 0.04332 -0.0307 1.0000 0.0339
-6.500 -0.5720 0.04777 0.03998 -0.0282 1.0000 0.0346
-6.250 -0.5683 0.04484 0.03665 -0.0256 1.0000 0.0357
-6.000 -0.5615 0.04203 0.03331 -0.0230 1.0000 0.0371
-5.750 -0.5511 0.03938 0.03010 -0.0205 1.0000 0.0382
-5.500 -0.5376 0.03672 0.02695 -0.0182 1.0000 0.0389
-5.250 -0.5222 0.03388 0.02380 -0.0165 1.0000 0.0400
-5.000 -0.5044 0.03161 0.02125 -0.0148 1.0000 0.0417
-4.750 -0.4846 0.02968 0.01904 -0.0132 1.0000 0.0439
-4.500 -0.4635 0.02798 0.01703 -0.0116 1.0000 0.0483
-4.250 -0.4432 0.02653 0.01543 -0.0102 1.0000 0.0562
-4.000 -0.4211 0.02521 0.01380 -0.0086 1.0000 0.0642
-3.750 -0.4001 0.02393 0.01247 -0.0074 1.0000 0.0806
-3.500 -0.3786 0.02253 0.01112 -0.0062 1.0000 0.1088
-3.250 -0.3605 0.02081 0.01012 -0.0050 1.0000 0.2120
-3.000 -0.3495 0.01903 0.00960 -0.0024 1.0000 0.4363
-2.750 -0.3184 0.01868 0.01078 0.0021 1.0000 0.8802
-2.500 -0.1406 0.01887 0.00960 -0.0246 1.0000 1.0000
-2.250 -0.1324 0.01881 0.00931 -0.0218 1.0000 1.0000
-2.000 -0.1233 0.01878 0.00905 -0.0192 1.0000 1.0000
-1.750 -0.1135 0.01876 0.00883 -0.0165 1.0000 1.0000
-1.500 -0.1032 0.01875 0.00865 -0.0140 1.0000 1.0000
-1.250 -0.0923 0.01876 0.00844 -0.0115 1.0000 1.0000
-1.000 -0.0811 0.01879 0.00832 -0.0091 1.0000 1.0000
-0.750 -0.0696 0.01883 0.00823 -0.0067 1.0000 1.0000
-0.500 -0.0577 0.01889 0.00816 -0.0044 1.0000 1.0000
-0.250 -0.0318 0.01904 0.00819 -0.0049 0.9957 1.0000
0.000 0.0006 0.01926 0.00826 -0.0067 0.9890 1.0000
0.250 0.0354 0.01957 0.00847 -0.0088 0.9824 1.0000
0.500 0.0679 0.01981 0.00866 -0.0105 0.9745 1.0000
0.750 0.1044 0.02013 0.00895 -0.0129 0.9670 1.0000
1.000 0.1404 0.02044 0.00924 -0.0151 0.9584 1.0000
1.250 0.1758 0.02075 0.00957 -0.0172 0.9491 1.0000
1.500 0.2168 0.02109 0.00996 -0.0203 0.9400 1.0000
1.750 0.2583 0.02139 0.01038 -0.0233 0.9296 1.0000
2.000 0.2992 0.02166 0.01076 -0.0261 0.9175 1.0000
2.250 0.3450 0.02187 0.01112 -0.0296 0.9044 1.0000
2.500 0.3907 0.02197 0.01141 -0.0326 0.8892 1.0000
2.750 0.4316 0.02202 0.01171 -0.0344 0.8714 1.0000
3.000 0.4665 0.02203 0.01193 -0.0349 0.8515 1.0000
3.250 0.5011 0.02195 0.01207 -0.0349 0.8313 1.0000
3.500 0.5252 0.02189 0.01222 -0.0330 0.8082 1.0000
3.750 0.5326 0.02193 0.01251 -0.0287 0.7786 1.0000
4.000 0.5413 0.02176 0.01253 -0.0247 0.7440 1.0000
4.250 0.5563 0.02134 0.01232 -0.0212 0.7044 1.0000
4.500 0.5792 0.02063 0.01179 -0.0182 0.6533 1.0000
4.750 0.6106 0.01983 0.01082 -0.0155 0.5687 1.0000
5.000 0.6301 0.02014 0.01061 -0.0122 0.4650 1.0000
5.250 0.6421 0.02110 0.01116 -0.0091 0.3779 1.0000
5.500 0.6536 0.02221 0.01189 -0.0064 0.3078 1.0000
5.750 0.6664 0.02337 0.01276 -0.0042 0.2519 1.0000
6.000 0.6810 0.02457 0.01373 -0.0024 0.2075 1.0000
6.250 0.6979 0.02579 0.01487 -0.0008 0.1725 1.0000
6.500 0.7156 0.02705 0.01604 0.0005 0.1430 1.0000
6.750 0.7369 0.02845 0.01749 0.0016 0.1218 1.0000
7.000 0.7579 0.02986 0.01895 0.0026 0.1033 1.0000
7.250 0.7787 0.03143 0.02066 0.0036 0.0884 1.0000
7.500 0.8021 0.03341 0.02286 0.0046 0.0768 1.0000
7.750 0.8205 0.03521 0.02487 0.0057 0.0646 1.0000
8.000 0.8410 0.03789 0.02789 0.0068 0.0568 1.0000
8.250 0.8555 0.03992 0.02991 0.0079 0.0492 1.0000
8.500 0.8707 0.04336 0.03408 0.0095 0.0449 1.0000
8.750 0.8816 0.04679 0.03797 0.0111 0.0422 1.0000
9.000 0.8899 0.04939 0.04075 0.0124 0.0389 1.0000
9.250 0.8919 0.05295 0.04462 0.0139 0.0368 1.0000
9.500 0.8868 0.05687 0.04907 0.0158 0.0355 1.0000
9.750 0.8767 0.06092 0.05352 0.0174 0.0347 1.0000
10.000 0.8624 0.06468 0.05754 0.0188 0.0344 1.0000
10.250 0.8452 0.06882 0.06187 0.0193 0.0345 1.0000
10.500 0.8261 0.07360 0.06681 0.0183 0.0346 1.0000
10.750 0.8075 0.07900 0.07233 0.0161 0.0351 1.0000
11.000 0.7914 0.08503 0.07842 0.0127 0.0358 1.0000
11.250 0.7750 0.09225 0.08567 0.0078 0.0362 1.0000
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Polar data table (+)
Polar graphs
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