DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 500,000 Max Cl/Cd: 59.07 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du8608418-il-500000-n5.txt Download as CSV file: xf-du8608418-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5449 0.08419 0.08149 -0.0224 0.8486 0.0047
-9.250 -0.5497 0.07909 0.07642 -0.0255 0.8482 0.0047
-9.000 -0.5592 0.07324 0.07060 -0.0298 0.8477 0.0046
-8.750 -0.5759 0.06687 0.06424 -0.0349 0.8470 0.0045
-8.250 -0.6029 0.05584 0.05302 -0.0370 0.8458 0.0044
-8.000 -0.6101 0.04974 0.04673 -0.0369 0.8452 0.0043
-7.750 -0.6139 0.04353 0.04023 -0.0358 0.8444 0.0041
-7.500 -0.6182 0.03608 0.03233 -0.0336 0.8438 0.0039
-7.250 -0.6213 0.02775 0.02321 -0.0301 0.8432 0.0037
-7.000 -0.6081 0.02370 0.01861 -0.0282 0.8427 0.0036
-6.750 -0.5889 0.02114 0.01563 -0.0269 0.8423 0.0037
-6.500 -0.5673 0.01919 0.01335 -0.0260 0.8417 0.0038
-6.250 -0.5441 0.01770 0.01161 -0.0253 0.8411 0.0040
-6.000 -0.5202 0.01643 0.01011 -0.0246 0.8407 0.0042
-5.750 -0.4957 0.01540 0.00892 -0.0241 0.8403 0.0046
-5.500 -0.4708 0.01457 0.00794 -0.0236 0.8398 0.0051
-5.250 -0.4453 0.01395 0.00722 -0.0232 0.8392 0.0056
-5.000 -0.4210 0.01306 0.00621 -0.0227 0.8385 0.0064
-4.750 -0.3950 0.01262 0.00575 -0.0225 0.8379 0.0075
-4.500 -0.3683 0.01236 0.00546 -0.0224 0.8373 0.0092
-4.250 -0.3421 0.01190 0.00492 -0.0221 0.8365 0.0104
-4.000 -0.3159 0.01145 0.00438 -0.0218 0.8359 0.0126
-3.750 -0.2891 0.01120 0.00409 -0.0217 0.8351 0.0160
-3.500 -0.2625 0.01088 0.00377 -0.0215 0.8343 0.0242
-3.250 -0.2358 0.01063 0.00355 -0.0214 0.8334 0.0401
-3.000 -0.2093 0.01029 0.00334 -0.0213 0.8324 0.0724
-2.750 -0.1827 0.00996 0.00315 -0.0213 0.8312 0.1138
-2.500 -0.1569 0.00950 0.00300 -0.0212 0.8299 0.1902
-2.250 -0.1317 0.00900 0.00287 -0.0210 0.8282 0.2884
-2.000 -0.1066 0.00853 0.00276 -0.0208 0.8260 0.3888
-1.750 -0.0817 0.00812 0.00266 -0.0204 0.8236 0.4806
-1.500 -0.0574 0.00770 0.00256 -0.0199 0.8211 0.5804
-1.250 -0.0353 0.00708 0.00248 -0.0187 0.8179 0.7171
-1.000 -0.0164 0.00704 0.00288 -0.0160 0.8144 0.8421
-0.750 0.0106 0.00711 0.00290 -0.0156 0.8112 0.8664
-0.500 0.0373 0.00719 0.00291 -0.0152 0.8084 0.8786
-0.250 0.0643 0.00720 0.00291 -0.0149 0.8042 0.8877
0.000 0.0902 0.00720 0.00291 -0.0142 0.7996 0.8944
0.250 0.1169 0.00718 0.00285 -0.0137 0.7955 0.9009
0.500 0.1426 0.00712 0.00283 -0.0130 0.7890 0.9064
0.750 0.1683 0.00707 0.00277 -0.0123 0.7835 0.9133
1.000 0.1936 0.00701 0.00276 -0.0115 0.7759 0.9190
1.250 0.2188 0.00696 0.00274 -0.0107 0.7669 0.9254
1.500 0.2436 0.00688 0.00271 -0.0098 0.7548 0.9317
1.750 0.2674 0.00673 0.00258 -0.0085 0.7358 0.9387
2.000 0.2910 0.00648 0.00216 -0.0071 0.6961 0.9436
2.250 0.3134 0.00665 0.00201 -0.0057 0.6270 0.9459
2.500 0.3365 0.00702 0.00208 -0.0049 0.5564 0.9471
2.750 0.3602 0.00739 0.00221 -0.0043 0.4911 0.9483
3.000 0.3843 0.00778 0.00235 -0.0039 0.4277 0.9492
3.250 0.4086 0.00817 0.00249 -0.0035 0.3650 0.9500
3.500 0.4335 0.00852 0.00265 -0.0033 0.3144 0.9509
3.750 0.4585 0.00887 0.00282 -0.0031 0.2679 0.9520
4.000 0.4839 0.00922 0.00302 -0.0029 0.2254 0.9527
4.250 0.5094 0.00957 0.00322 -0.0028 0.1877 0.9534
4.500 0.5353 0.00987 0.00342 -0.0028 0.1600 0.9541
4.750 0.5611 0.01020 0.00365 -0.0027 0.1318 0.9547
5.250 0.6125 0.01084 0.00417 -0.0025 0.0898 0.9561
5.500 0.6380 0.01115 0.00444 -0.0023 0.0748 0.9571
5.750 0.6636 0.01148 0.00475 -0.0022 0.0620 0.9578
6.000 0.6889 0.01185 0.00508 -0.0020 0.0485 0.9586
6.250 0.7141 0.01223 0.00542 -0.0019 0.0367 0.9594
6.500 0.7396 0.01257 0.00578 -0.0017 0.0309 0.9602
6.750 0.7649 0.01295 0.00621 -0.0016 0.0252 0.9611
7.000 0.7897 0.01338 0.00665 -0.0013 0.0189 0.9621
7.250 0.8142 0.01386 0.00714 -0.0011 0.0129 0.9631
7.500 0.8379 0.01444 0.00775 -0.0007 0.0091 0.9643
7.750 0.8617 0.01503 0.00839 -0.0003 0.0074 0.9656
8.000 0.8842 0.01580 0.00924 0.0002 0.0056 0.9670
8.250 0.9083 0.01629 0.00982 0.0005 0.0048 0.9684
8.500 0.9317 0.01699 0.01063 0.0008 0.0041 0.9703
8.750 0.9551 0.01775 0.01152 0.0010 0.0036 0.9723
9.000 0.9751 0.01908 0.01303 0.0016 0.0031 0.9750
9.250 0.9975 0.02007 0.01416 0.0019 0.0029 0.9778
9.500 1.0199 0.02108 0.01533 0.0020 0.0027 0.9811
9.750 1.0415 0.02235 0.01679 0.0022 0.0024 0.9871
10.000 1.0598 0.02371 0.01835 0.0028 0.0023 1.0000
10.250 1.0748 0.02518 0.02002 0.0039 0.0021 1.0000
10.500 1.0879 0.02677 0.02182 0.0052 0.0020 1.0000
10.750 1.0988 0.02843 0.02369 0.0066 0.0019 1.0000
11.000 1.1047 0.03020 0.02567 0.0087 0.0019 1.0000
11.250 1.1050 0.03224 0.02794 0.0112 0.0019 1.0000
11.500 1.1050 0.03424 0.03014 0.0131 0.0018 1.0000
11.750 1.1006 0.03676 0.03288 0.0150 0.0018 1.0000
12.000 1.0947 0.03948 0.03584 0.0164 0.0018 1.0000
12.250 1.0840 0.04284 0.03943 0.0175 0.0017 1.0000
12.500 1.0733 0.04641 0.04318 0.0179 0.0017 1.0000
12.750 1.0553 0.05136 0.04838 0.0171 0.0018 1.0000
13.000 1.0374 0.05711 0.05433 0.0145 0.0018 1.0000
13.250 1.0166 0.06479 0.06221 0.0095 0.0018 1.0000
13.500 0.9930 0.07522 0.07280 0.0018 0.0018 1.0000
13.750 0.9586 0.08988 0.08766 -0.0076 0.0019 1.0000
14.000 0.9194 0.10508 0.10297 -0.0159 0.0020 1.0000
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Polar data table (+)
Polar graphs
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