DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 500,000 Max Cl/Cd: 75.64 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du8608418-il-500000.txt Download as CSV file: xf-du8608418-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4510 0.08978 0.08762 -0.0196 0.9121 0.0152
-9.750 -0.4575 0.08355 0.08141 -0.0221 0.9116 0.0155
-9.500 -0.4601 0.07823 0.07609 -0.0246 0.9110 0.0155
-9.250 -0.4653 0.07274 0.07062 -0.0270 0.9106 0.0159
-9.000 -0.5041 0.07735 0.07505 -0.0355 0.9138 0.0148
-8.750 -0.5105 0.07041 0.06809 -0.0422 0.9116 0.0148
-8.500 -0.5222 0.06557 0.06316 -0.0442 0.9091 0.0148
-8.250 -0.5344 0.06190 0.05940 -0.0438 0.9074 0.0148
-8.000 -0.5396 0.05801 0.05537 -0.0437 0.9060 0.0148
-7.750 -0.5711 0.04869 0.04578 -0.0432 0.9041 0.0155
-7.500 -0.5698 0.04476 0.04166 -0.0424 0.9027 0.0159
-7.250 -0.5608 0.04193 0.03870 -0.0418 0.9018 0.0164
-7.000 -0.5493 0.03923 0.03583 -0.0410 0.9010 0.0169
-6.750 -0.5359 0.03645 0.03285 -0.0402 0.9003 0.0175
-6.500 -0.5210 0.03366 0.02982 -0.0393 0.8994 0.0184
-6.250 -0.5041 0.03090 0.02674 -0.0382 0.8985 0.0196
-6.000 -0.4907 0.02350 0.01850 -0.0346 0.8974 0.0124
-5.750 -0.4708 0.01908 0.01341 -0.0326 0.8964 0.0109
-5.500 -0.4462 0.01747 0.01158 -0.0319 0.8954 0.0115
-5.250 -0.4207 0.01615 0.01010 -0.0314 0.8947 0.0121
-5.000 -0.3947 0.01536 0.00921 -0.0311 0.8938 0.0132
-4.750 -0.3684 0.01473 0.00848 -0.0308 0.8928 0.0142
-4.500 -0.3431 0.01375 0.00739 -0.0302 0.8918 0.0145
-4.250 -0.3192 0.01265 0.00617 -0.0295 0.8906 0.0152
-4.000 -0.2957 0.01162 0.00502 -0.0286 0.8894 0.0186
-3.750 -0.2696 0.01125 0.00458 -0.0283 0.8882 0.0232
-3.500 -0.2451 0.01051 0.00399 -0.0277 0.8869 0.0630
-3.250 -0.2203 0.00985 0.00373 -0.0276 0.8856 0.1532
-3.000 -0.1959 0.00923 0.00356 -0.0274 0.8840 0.2664
-2.750 -0.1721 0.00861 0.00341 -0.0271 0.8820 0.3928
-2.500 -0.1490 0.00805 0.00330 -0.0265 0.8797 0.5166
-2.250 -0.1277 0.00743 0.00319 -0.0253 0.8771 0.6548
-2.000 -0.1134 0.00728 0.00374 -0.0213 0.8744 0.8445
-1.750 -0.0897 0.00757 0.00398 -0.0200 0.8716 0.8806
-1.500 -0.0670 0.00778 0.00415 -0.0184 0.8678 0.8977
-1.250 -0.0447 0.00794 0.00427 -0.0166 0.8640 0.9092
-1.000 -0.0228 0.00809 0.00437 -0.0148 0.8605 0.9192
-0.750 -0.0005 0.00821 0.00446 -0.0132 0.8565 0.9293
-0.500 0.0236 0.00825 0.00447 -0.0118 0.8521 0.9367
-0.250 0.0472 0.00829 0.00446 -0.0104 0.8478 0.9442
0.000 0.0757 0.00834 0.00449 -0.0101 0.8431 0.9503
0.250 0.1015 0.00833 0.00444 -0.0094 0.8373 0.9564
0.500 0.1378 0.00836 0.00443 -0.0108 0.8322 0.9601
0.750 0.1754 0.00832 0.00438 -0.0127 0.8260 0.9643
1.000 0.2031 0.00833 0.00435 -0.0123 0.8210 0.9690
1.250 0.2524 0.00825 0.00428 -0.0168 0.8151 0.9712
1.500 0.2985 0.00816 0.00418 -0.0205 0.8092 0.9747
1.750 0.3391 0.00805 0.00410 -0.0231 0.8017 0.9807
2.000 0.3864 0.00784 0.00388 -0.0270 0.7946 0.9854
2.250 0.4262 0.00756 0.00367 -0.0295 0.7834 0.9893
2.500 0.4564 0.00727 0.00345 -0.0300 0.7689 0.9913
2.750 0.4850 0.00698 0.00322 -0.0300 0.7389 0.9929
3.000 0.5083 0.00672 0.00262 -0.0286 0.6631 0.9943
3.250 0.5315 0.00717 0.00261 -0.0278 0.5621 0.9955
3.500 0.5545 0.00777 0.00279 -0.0273 0.4577 0.9967
3.750 0.5786 0.00833 0.00298 -0.0270 0.3700 0.9979
4.000 0.6033 0.00884 0.00318 -0.0269 0.2960 0.9989
4.250 0.6288 0.00927 0.00340 -0.0269 0.2420 0.9997
4.500 0.6517 0.00967 0.00365 -0.0263 0.1983 1.0000
4.750 0.6728 0.01008 0.00391 -0.0253 0.1595 1.0000
5.000 0.6940 0.01048 0.00418 -0.0243 0.1274 1.0000
5.250 0.7147 0.01090 0.00450 -0.0232 0.1001 1.0000
5.500 0.7351 0.01134 0.00485 -0.0221 0.0775 1.0000
5.750 0.7553 0.01179 0.00521 -0.0209 0.0606 1.0000
6.000 0.7755 0.01218 0.00562 -0.0197 0.0498 1.0000
6.250 0.7954 0.01258 0.00605 -0.0184 0.0418 1.0000
6.500 0.8145 0.01304 0.00648 -0.0169 0.0325 1.0000
6.750 0.8327 0.01358 0.00701 -0.0153 0.0217 1.0000
7.000 0.8471 0.01454 0.00800 -0.0130 0.0144 1.0000
7.250 0.8639 0.01511 0.00867 -0.0111 0.0125 1.0000
7.500 0.8792 0.01577 0.00940 -0.0089 0.0109 1.0000
7.750 0.8906 0.01677 0.01049 -0.0061 0.0099 1.0000
8.000 0.8974 0.01839 0.01230 -0.0026 0.0092 1.0000
8.250 0.9072 0.02062 0.01478 0.0002 0.0089 1.0000
8.500 0.9280 0.02127 0.01557 0.0011 0.0085 1.0000
8.750 0.9479 0.02237 0.01682 0.0020 0.0081 1.0000
9.000 0.9671 0.02370 0.01833 0.0029 0.0076 1.0000
9.250 0.9843 0.02548 0.02035 0.0040 0.0073 1.0000
9.500 0.9988 0.02776 0.02291 0.0053 0.0071 1.0000
9.750 1.0114 0.02999 0.02541 0.0066 0.0068 1.0000
10.000 1.0218 0.03211 0.02778 0.0080 0.0064 1.0000
10.250 1.0263 0.03481 0.03077 0.0099 0.0063 1.0000
10.500 1.0185 0.03853 0.03486 0.0129 0.0064 1.0000
10.750 1.0047 0.04181 0.03841 0.0159 0.0064 1.0000
11.000 0.9855 0.04578 0.04266 0.0180 0.0064 1.0000
11.250 0.9554 0.05146 0.04867 0.0191 0.0066 1.0000
11.500 0.9310 0.05697 0.05440 0.0182 0.0067 1.0000
11.750 0.9094 0.06308 0.06069 0.0152 0.0067 1.0000
12.000 0.8829 0.07212 0.06992 0.0085 0.0070 1.0000
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Polar data table (+)
Polar graphs
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