DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.05 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du8608418-il-1000000.txt Download as CSV file: xf-du8608418-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4555 0.08221 0.08032 -0.0171 0.8576 0.0089
-9.250 -0.4601 0.07617 0.07430 -0.0197 0.8574 0.0089
-8.000 -0.5648 0.05537 0.05320 -0.0390 0.8556 0.0088
-7.750 -0.5671 0.05043 0.04811 -0.0386 0.8552 0.0089
-7.500 -0.5662 0.04606 0.04355 -0.0377 0.8547 0.0089
-7.250 -0.5626 0.04197 0.03923 -0.0364 0.8539 0.0089
-7.000 -0.5560 0.03819 0.03519 -0.0350 0.8533 0.0089
-6.750 -0.5461 0.03476 0.03149 -0.0336 0.8528 0.0090
-6.500 -0.5656 0.02014 0.01553 -0.0273 0.8517 0.0056
-6.250 -0.5420 0.01887 0.01406 -0.0266 0.8511 0.0054
-6.000 -0.5196 0.01691 0.01183 -0.0256 0.8506 0.0054
-5.750 -0.4995 0.01404 0.00862 -0.0242 0.8501 0.0058
-5.500 -0.4745 0.01328 0.00778 -0.0239 0.8495 0.0065
-5.250 -0.4486 0.01276 0.00720 -0.0236 0.8489 0.0071
-5.000 -0.4228 0.01220 0.00658 -0.0233 0.8483 0.0076
-4.750 -0.3972 0.01159 0.00589 -0.0229 0.8476 0.0080
-4.500 -0.3711 0.01117 0.00540 -0.0226 0.8469 0.0084
-4.250 -0.3442 0.01102 0.00523 -0.0225 0.8460 0.0089
-4.000 -0.3193 0.01011 0.00416 -0.0219 0.8452 0.0103
-3.750 -0.2924 0.00971 0.00372 -0.0217 0.8445 0.0129
-3.500 -0.2654 0.00934 0.00335 -0.0215 0.8435 0.0215
-3.250 -0.2386 0.00899 0.00311 -0.0214 0.8423 0.0485
-3.000 -0.2126 0.00856 0.00292 -0.0213 0.8407 0.1037
-2.750 -0.1867 0.00815 0.00276 -0.0211 0.8386 0.1732
-2.500 -0.1613 0.00772 0.00262 -0.0209 0.8363 0.2585
-2.250 -0.1364 0.00733 0.00256 -0.0205 0.8338 0.3590
-2.000 -0.1107 0.00698 0.00250 -0.0203 0.8313 0.4458
-1.750 -0.0850 0.00654 0.00238 -0.0201 0.8285 0.5408
-1.500 -0.0612 0.00593 0.00225 -0.0195 0.8256 0.6820
-1.250 -0.0414 0.00562 0.00251 -0.0173 0.8230 0.8580
-1.000 -0.0147 0.00580 0.00265 -0.0168 0.8202 0.8763
-0.750 0.0123 0.00583 0.00267 -0.0164 0.8170 0.8855
-0.500 0.0387 0.00586 0.00269 -0.0158 0.8132 0.8933
-0.250 0.0653 0.00589 0.00269 -0.0153 0.8095 0.9002
0.000 0.0913 0.00594 0.00272 -0.0146 0.8063 0.9055
0.250 0.1178 0.00589 0.00269 -0.0141 0.8022 0.9103
0.500 0.1451 0.00587 0.00265 -0.0138 0.7984 0.9152
0.750 0.1709 0.00581 0.00257 -0.0131 0.7953 0.9188
1.000 0.1972 0.00575 0.00253 -0.0125 0.7912 0.9226
1.250 0.2240 0.00567 0.00248 -0.0121 0.7861 0.9270
1.500 0.2498 0.00553 0.00232 -0.0114 0.7813 0.9312
1.750 0.2743 0.00542 0.00228 -0.0104 0.7731 0.9359
2.000 0.3002 0.00532 0.00221 -0.0098 0.7610 0.9409
2.250 0.3241 0.00510 0.00198 -0.0085 0.7374 0.9457
2.500 0.3437 0.00512 0.00175 -0.0063 0.6751 0.9515
2.750 0.3637 0.00554 0.00185 -0.0047 0.5923 0.9559
3.000 0.3851 0.00587 0.00191 -0.0035 0.5171 0.9586
3.250 0.4096 0.00619 0.00202 -0.0030 0.4559 0.9595
3.500 0.4336 0.00658 0.00214 -0.0026 0.3867 0.9605
3.750 0.4583 0.00697 0.00228 -0.0023 0.3224 0.9612
4.000 0.4835 0.00733 0.00244 -0.0022 0.2683 0.9618
4.250 0.5095 0.00763 0.00259 -0.0021 0.2280 0.9624
4.500 0.5352 0.00794 0.00276 -0.0020 0.1919 0.9631
4.750 0.5611 0.00825 0.00293 -0.0019 0.1580 0.9639
5.000 0.5874 0.00854 0.00314 -0.0019 0.1314 0.9644
5.250 0.6137 0.00885 0.00335 -0.0019 0.1070 0.9649
5.500 0.6396 0.00920 0.00359 -0.0019 0.0817 0.9654
5.750 0.6656 0.00955 0.00384 -0.0019 0.0621 0.9660
6.000 0.6918 0.00988 0.00412 -0.0019 0.0480 0.9665
6.250 0.7182 0.01018 0.00438 -0.0019 0.0386 0.9670
6.500 0.7446 0.01048 0.00470 -0.0019 0.0315 0.9675
6.750 0.7701 0.01086 0.00503 -0.0018 0.0231 0.9683
7.000 0.7954 0.01128 0.00542 -0.0017 0.0137 0.9690
7.250 0.8198 0.01193 0.00608 -0.0013 0.0083 0.9698
7.500 0.8448 0.01243 0.00663 -0.0011 0.0068 0.9707
7.750 0.8678 0.01324 0.00755 -0.0005 0.0056 0.9719
8.000 0.8894 0.01421 0.00867 0.0002 0.0051 0.9732
8.250 0.9134 0.01481 0.00938 0.0005 0.0049 0.9745
8.500 0.9365 0.01555 0.01023 0.0010 0.0047 0.9759
8.750 0.9585 0.01647 0.01128 0.0016 0.0046 0.9776
9.000 0.9809 0.01737 0.01229 0.0020 0.0043 0.9795
9.250 1.0037 0.01824 0.01328 0.0023 0.0041 0.9815
9.500 1.0265 0.01937 0.01454 0.0024 0.0039 0.9841
9.750 1.0506 0.02031 0.01558 0.0022 0.0036 0.9873
10.000 1.0733 0.02143 0.01681 0.0020 0.0032 0.9925
10.250 1.0809 0.02440 0.02010 0.0038 0.0030 1.0000
10.500 1.0816 0.02801 0.02410 0.0062 0.0029 1.0000
10.750 1.0670 0.03264 0.02921 0.0100 0.0028 1.0000
11.000 1.0711 0.03401 0.03075 0.0121 0.0028 1.0000
11.250 1.0581 0.03708 0.03406 0.0148 0.0028 1.0000
11.500 1.0465 0.04018 0.03737 0.0166 0.0028 1.0000
11.750 1.0371 0.04323 0.04060 0.0177 0.0027 1.0000
12.250 0.9908 0.05375 0.05151 0.0167 0.0028 1.0000
12.500 0.9848 0.05783 0.05570 0.0145 0.0029 1.0000
12.750 0.9651 0.06534 0.06337 0.0094 0.0029 1.0000
13.000 0.9483 0.07427 0.07245 0.0026 0.0029 1.0000
13.250 0.9384 0.08273 0.08101 -0.0035 0.0029 1.0000
13.500 0.9313 0.09043 0.08877 -0.0084 0.0029 1.0000
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Polar data table (+)
Polar graphs
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