AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 85-L-120/17 (ah85l120-il) Reynolds number: 100,000 Max Cl/Cd: 37.64 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah85l120-il-100000.txt Download as CSV file: xf-ah85l120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 85-L-120/17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.8300 0.05182 0.04570 -0.0083 1.0000 0.0866
-7.500 -0.8351 0.04637 0.03919 -0.0014 1.0000 0.0621
-7.250 -0.8284 0.04247 0.03508 0.0015 1.0000 0.0592
-7.000 -0.8212 0.03927 0.03142 0.0050 1.0000 0.0570
-6.750 -0.8110 0.03704 0.02882 0.0080 1.0000 0.0581
-6.500 -0.7975 0.03485 0.02625 0.0106 1.0000 0.0588
-6.250 -0.7795 0.03241 0.02343 0.0128 1.0000 0.0583
-6.000 -0.7579 0.03027 0.02096 0.0144 1.0000 0.0581
-5.750 -0.7341 0.02842 0.01886 0.0156 1.0000 0.0593
-5.500 -0.7102 0.02688 0.01716 0.0167 1.0000 0.0610
-5.250 -0.6884 0.02536 0.01557 0.0180 1.0000 0.0649
-5.000 -0.6718 0.02416 0.01443 0.0198 1.0000 0.0715
-4.750 -0.6572 0.02303 0.01328 0.0222 1.0000 0.0782
-4.500 -0.6456 0.02191 0.01219 0.0251 1.0000 0.0906
-4.250 -0.6366 0.02060 0.01111 0.0282 1.0000 0.1192
-4.000 -0.6498 0.01713 0.00984 0.0349 1.0000 0.4205
-3.750 -0.6492 0.01767 0.01200 0.0445 1.0000 0.7547
-3.500 -0.6397 0.01901 0.01321 0.0506 1.0000 0.8092
-3.250 -0.6166 0.02097 0.01502 0.0555 1.0000 0.8523
-3.000 -0.4619 0.02552 0.01891 0.0385 1.0000 0.8977
-2.750 -0.4070 0.02598 0.01908 0.0336 1.0000 0.9147
-2.500 -0.3441 0.02627 0.01912 0.0269 1.0000 0.9293
-2.250 -0.2902 0.02626 0.01893 0.0213 1.0000 0.9416
-2.000 -0.2430 0.02605 0.01854 0.0165 1.0000 0.9508
-1.750 -0.2084 0.02584 0.01823 0.0139 1.0000 0.9602
-1.500 -0.1766 0.02571 0.01800 0.0118 1.0000 0.9700
-1.250 -0.1341 0.02546 0.01766 0.0075 1.0000 0.9772
-1.000 -0.0978 0.02531 0.01745 0.0043 1.0000 0.9848
-0.750 -0.0597 0.02519 0.01729 0.0007 1.0000 0.9920
-0.500 -0.0202 0.02511 0.01717 -0.0033 1.0000 0.9986
-0.250 -0.0059 0.02509 0.01714 -0.0024 1.0000 1.0000
0.000 0.0000 0.02508 0.01713 0.0000 1.0000 1.0000
0.250 0.0059 0.02509 0.01715 0.0025 1.0000 1.0000
0.500 0.0202 0.02511 0.01717 0.0033 0.9986 1.0000
0.750 0.0591 0.02518 0.01728 -0.0005 0.9921 1.0000
1.000 0.0970 0.02531 0.01745 -0.0041 0.9849 1.0000
1.250 0.1345 0.02545 0.01766 -0.0075 0.9771 1.0000
1.500 0.1762 0.02570 0.01800 -0.0117 0.9700 1.0000
1.750 0.2079 0.02583 0.01821 -0.0138 0.9603 1.0000
2.000 0.2437 0.02603 0.01852 -0.0166 0.9506 1.0000
2.250 0.2899 0.02624 0.01890 -0.0212 0.9412 1.0000
2.500 0.3437 0.02626 0.01911 -0.0268 0.9293 1.0000
2.750 0.4050 0.02601 0.01910 -0.0333 0.9152 1.0000
3.000 0.4621 0.02550 0.01889 -0.0385 0.8974 1.0000
3.250 0.6166 0.02108 0.01513 -0.0557 0.8542 1.0000
3.500 0.6400 0.01905 0.01325 -0.0508 0.8103 1.0000
3.750 0.6508 0.01768 0.01200 -0.0449 0.7587 1.0000
4.000 0.6485 0.01723 0.00985 -0.0346 0.4058 1.0000
4.250 0.6367 0.02060 0.01111 -0.0282 0.1188 1.0000
4.500 0.6457 0.02193 0.01220 -0.0251 0.0888 1.0000
4.750 0.6570 0.02305 0.01329 -0.0222 0.0779 1.0000
5.000 0.6720 0.02419 0.01446 -0.0198 0.0721 1.0000
5.250 0.6889 0.02555 0.01573 -0.0181 0.0644 1.0000
5.500 0.7105 0.02692 0.01722 -0.0167 0.0606 1.0000
5.750 0.7345 0.02850 0.01897 -0.0155 0.0587 1.0000
6.000 0.7585 0.03042 0.02113 -0.0143 0.0575 1.0000
6.250 0.7797 0.03255 0.02359 -0.0127 0.0578 1.0000
6.500 0.7966 0.03462 0.02601 -0.0105 0.0572 1.0000
6.750 0.8101 0.03647 0.02812 -0.0082 0.0548 1.0000
7.000 0.8207 0.03923 0.03140 -0.0050 0.0557 1.0000
7.250 0.8283 0.04253 0.03515 -0.0015 0.0592 1.0000
7.500 0.8348 0.04627 0.03910 0.0014 0.0619 1.0000
7.750 0.8354 0.05106 0.04453 0.0064 0.0750 1.0000
10.500 0.5978 0.09636 0.09169 0.0342 0.1474 1.0000
10.750 0.5777 0.10250 0.09772 0.0298 0.1428 1.0000
11.000 0.5693 0.10682 0.10198 0.0271 0.1361 1.0000
11.250 0.4723 0.09889 0.09451 0.0373 0.1453 1.0000
11.500 0.4282 0.10377 0.09929 0.0317 0.1437 1.0000
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Polar data table (+)
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