DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 100,000 Max Cl/Cd: 43.77 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du8608418-il-100000-n5.txt Download as CSV file: xf-du8608418-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4476 0.12049 0.11599 -0.0064 1.0000 0.0237
-11.000 -0.5488 0.12298 0.11814 -0.0010 1.0000 0.0239
-10.750 -0.5454 0.11865 0.11384 -0.0027 1.0000 0.0222
-10.500 -0.5436 0.11401 0.10923 -0.0049 1.0000 0.0210
-10.250 -0.5433 0.10902 0.10429 -0.0074 1.0000 0.0199
-9.250 -0.5441 0.08690 0.08235 -0.0215 1.0000 0.0168
-9.000 -0.5470 0.08183 0.07734 -0.0246 1.0000 0.0165
-8.750 -0.5516 0.07570 0.07125 -0.0299 1.0000 0.0164
-8.500 -0.5592 0.07016 0.06569 -0.0337 1.0000 0.0163
-8.250 -0.5683 0.06579 0.06128 -0.0351 1.0000 0.0161
-8.000 -0.5746 0.06114 0.05651 -0.0361 1.0000 0.0161
-7.750 -0.5790 0.05707 0.05230 -0.0361 1.0000 0.0159
-7.500 -0.5834 0.05311 0.04812 -0.0350 1.0000 0.0161
-7.250 -0.5890 0.04999 0.04477 -0.0324 1.0000 0.0162
-7.000 -0.5867 0.04695 0.04131 -0.0305 0.9950 0.0168
-6.750 -0.5801 0.04172 0.03567 -0.0308 0.9869 0.0178
-6.500 -0.5635 0.03809 0.03155 -0.0310 0.9825 0.0183
-6.250 -0.5462 0.03469 0.02766 -0.0304 0.9784 0.0186
-6.000 -0.5249 0.03155 0.02401 -0.0301 0.9750 0.0188
-5.750 -0.5006 0.02882 0.02080 -0.0299 0.9724 0.0194
-5.500 -0.4745 0.02645 0.01802 -0.0298 0.9704 0.0202
-5.250 -0.4476 0.02444 0.01568 -0.0297 0.9685 0.0215
-5.000 -0.4223 0.02309 0.01405 -0.0292 0.9659 0.0248
-4.750 -0.3965 0.02172 0.01247 -0.0288 0.9637 0.0276
-4.500 -0.3723 0.02016 0.01084 -0.0284 0.9615 0.0306
-4.250 -0.3462 0.01909 0.00958 -0.0281 0.9592 0.0353
-4.000 -0.3194 0.01812 0.00852 -0.0282 0.9572 0.0463
-3.750 -0.2924 0.01714 0.00764 -0.0283 0.9554 0.0761
-3.500 -0.2719 0.01605 0.00704 -0.0275 0.9523 0.1657
-3.250 -0.2505 0.01504 0.00676 -0.0269 0.9495 0.3239
-2.750 -0.1963 0.01371 0.00731 -0.0240 0.9472 0.7733
-2.500 -0.1738 0.01417 0.00761 -0.0219 0.9444 0.8696
-2.250 -0.1438 0.01447 0.00770 -0.0216 0.9425 0.9068
-2.000 -0.0995 0.01465 0.00766 -0.0243 0.9422 0.9321
-1.750 -0.0447 0.01469 0.00745 -0.0294 0.9427 0.9499
-1.500 0.0120 0.01461 0.00719 -0.0353 0.9431 0.9638
-1.250 0.0656 0.01447 0.00690 -0.0407 0.9429 0.9754
-1.000 0.1178 0.01428 0.00658 -0.0460 0.9422 0.9858
-0.750 0.1672 0.01408 0.00630 -0.0508 0.9403 0.9958
-0.500 0.2034 0.01401 0.00619 -0.0530 0.9359 1.0000
-0.250 0.2343 0.01402 0.00616 -0.0540 0.9304 1.0000
0.000 0.2610 0.01407 0.00619 -0.0540 0.9232 1.0000
0.250 0.2906 0.01409 0.00620 -0.0544 0.9160 1.0000
0.500 0.3138 0.01418 0.00629 -0.0536 0.9068 1.0000
0.750 0.3388 0.01423 0.00636 -0.0530 0.8976 1.0000
1.000 0.3632 0.01427 0.00643 -0.0520 0.8875 1.0000
1.250 0.3833 0.01434 0.00652 -0.0501 0.8752 1.0000
1.500 0.4031 0.01439 0.00661 -0.0481 0.8625 1.0000
1.750 0.4227 0.01445 0.00670 -0.0460 0.8496 1.0000
2.000 0.4421 0.01450 0.00684 -0.0439 0.8368 1.0000
2.250 0.4614 0.01455 0.00695 -0.0418 0.8238 1.0000
2.500 0.4806 0.01456 0.00705 -0.0396 0.8097 1.0000
2.750 0.4989 0.01453 0.00713 -0.0375 0.7929 1.0000
3.000 0.5163 0.01445 0.00720 -0.0354 0.7694 1.0000
3.250 0.5332 0.01437 0.00730 -0.0334 0.7360 1.0000
3.500 0.5522 0.01398 0.00704 -0.0308 0.6969 1.0000
3.750 0.5724 0.01342 0.00630 -0.0275 0.6352 1.0000
4.000 0.5892 0.01346 0.00589 -0.0240 0.5445 1.0000
4.250 0.6039 0.01407 0.00605 -0.0212 0.4517 1.0000
4.500 0.6191 0.01480 0.00640 -0.0190 0.3710 1.0000
4.750 0.6350 0.01553 0.00682 -0.0170 0.3023 1.0000
5.000 0.6515 0.01624 0.00736 -0.0153 0.2469 1.0000
5.250 0.6683 0.01695 0.00790 -0.0135 0.2017 1.0000
5.500 0.6851 0.01766 0.00847 -0.0118 0.1642 1.0000
5.750 0.7019 0.01838 0.00911 -0.0101 0.1340 1.0000
6.000 0.7182 0.01916 0.00983 -0.0083 0.1130 1.0000
6.250 0.7351 0.01994 0.01061 -0.0066 0.0939 1.0000
6.500 0.7519 0.02080 0.01148 -0.0050 0.0792 1.0000
6.750 0.7687 0.02181 0.01255 -0.0032 0.0691 1.0000
7.000 0.7861 0.02281 0.01368 -0.0018 0.0579 1.0000
7.250 0.8037 0.02390 0.01481 -0.0005 0.0476 1.0000
7.500 0.8214 0.02504 0.01604 0.0008 0.0384 1.0000
7.750 0.8396 0.02648 0.01768 0.0022 0.0315 1.0000
8.000 0.8555 0.02807 0.01930 0.0034 0.0262 1.0000
8.250 0.8743 0.03009 0.02166 0.0048 0.0235 1.0000
8.500 0.8917 0.03244 0.02433 0.0061 0.0212 1.0000
8.750 0.9073 0.03461 0.02677 0.0074 0.0195 1.0000
9.000 0.9182 0.03688 0.02919 0.0086 0.0174 1.0000
9.250 0.9280 0.03966 0.03242 0.0103 0.0159 1.0000
9.500 0.9336 0.04289 0.03612 0.0121 0.0152 1.0000
9.750 0.9323 0.04658 0.04036 0.0142 0.0147 1.0000
10.000 0.9258 0.05012 0.04428 0.0163 0.0145 1.0000
10.250 0.9127 0.05362 0.04808 0.0186 0.0145 1.0000
10.500 0.8962 0.05755 0.05226 0.0197 0.0144 1.0000
10.750 0.8779 0.06199 0.05694 0.0196 0.0144 1.0000
11.000 0.8595 0.06693 0.06206 0.0181 0.0146 1.0000
11.250 0.8389 0.07312 0.06833 0.0146 0.0147 1.0000
11.500 0.8176 0.08116 0.07650 0.0087 0.0150 1.0000
11.750 0.7981 0.09113 0.08653 0.0012 0.0155 1.0000
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Polar data table (+)
Polar graphs
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