LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 100,000 Max Cl/Cd: 48.7 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188root-il-100000-n5.txt Download as CSV file: xf-l188root-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 ROOT AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5790 0.08256 0.07681 -0.0620 1.0000 0.0420
-11.750 -0.6284 0.06996 0.06408 -0.0711 1.0000 0.0414
-11.500 -0.6670 0.06265 0.05660 -0.0750 1.0000 0.0411
-11.250 -0.7005 0.05802 0.05180 -0.0749 1.0000 0.0410
-11.000 -0.7333 0.05532 0.04898 -0.0711 1.0000 0.0410
-10.750 -0.7654 0.05352 0.04709 -0.0651 1.0000 0.0410
-10.500 -0.7922 0.05126 0.04463 -0.0596 1.0000 0.0412
-10.250 -0.8146 0.04876 0.04185 -0.0545 1.0000 0.0416
-10.000 -0.8331 0.04598 0.03866 -0.0497 1.0000 0.0422
-9.750 -0.8213 0.04386 0.03636 -0.0494 0.9970 0.0431
-9.500 -0.7985 0.04215 0.03451 -0.0506 0.9929 0.0442
-9.250 -0.7782 0.03997 0.03205 -0.0513 0.9880 0.0454
-9.000 -0.7559 0.03743 0.02910 -0.0522 0.9839 0.0468
-8.750 -0.7352 0.03507 0.02621 -0.0524 0.9790 0.0487
-8.500 -0.7081 0.03397 0.02512 -0.0535 0.9748 0.0503
-8.250 -0.6786 0.03267 0.02366 -0.0549 0.9714 0.0525
-8.000 -0.6534 0.03118 0.02188 -0.0551 0.9667 0.0546
-7.750 -0.6263 0.02992 0.02046 -0.0557 0.9621 0.0568
-7.500 -0.5953 0.02901 0.01952 -0.0571 0.9587 0.0595
-7.250 -0.5622 0.02790 0.01819 -0.0587 0.9560 0.0629
-7.000 -0.5395 0.02700 0.01726 -0.0582 0.9497 0.0654
-6.750 -0.5093 0.02623 0.01647 -0.0592 0.9456 0.0692
-6.500 -0.4758 0.02536 0.01544 -0.0607 0.9427 0.0736
-6.250 -0.4482 0.02464 0.01478 -0.0612 0.9382 0.0777
-6.000 -0.4229 0.02405 0.01408 -0.0610 0.9322 0.0831
-5.750 -0.3930 0.02334 0.01343 -0.0619 0.9282 0.0887
-5.500 -0.3603 0.02270 0.01275 -0.0632 0.9252 0.0965
-5.250 -0.3400 0.02223 0.01232 -0.0621 0.9179 0.1035
-5.000 -0.3126 0.02168 0.01179 -0.0623 0.9129 0.1131
-4.750 -0.2816 0.02113 0.01127 -0.0632 0.9094 0.1258
-4.500 -0.2580 0.02071 0.01088 -0.0626 0.9034 0.1402
-4.250 -0.2341 0.02025 0.01052 -0.0622 0.8972 0.1591
-3.750 -0.1775 0.01909 0.00969 -0.0630 0.8893 0.2341
-3.500 -0.1605 0.01852 0.00946 -0.0615 0.8811 0.3011
-3.250 -0.1388 0.01757 0.00931 -0.0606 0.8764 0.4518
-3.000 -0.1114 0.01727 0.00939 -0.0600 0.8732 0.5686
-2.750 -0.0933 0.01736 0.00957 -0.0579 0.8649 0.6176
-2.500 -0.0663 0.01737 0.00959 -0.0573 0.8601 0.6558
-2.250 -0.0368 0.01735 0.00957 -0.0570 0.8567 0.6856
-2.000 -0.0160 0.01749 0.00969 -0.0555 0.8493 0.7091
-1.750 0.0096 0.01754 0.00973 -0.0546 0.8440 0.7300
-1.500 0.0380 0.01753 0.00972 -0.0540 0.8403 0.7525
-1.250 0.0585 0.01768 0.00989 -0.0521 0.8339 0.7796
-1.000 0.0799 0.01779 0.01006 -0.0500 0.8279 0.8038
-0.750 0.1075 0.01775 0.01000 -0.0493 0.8240 0.8210
-0.500 0.1356 0.01770 0.00990 -0.0493 0.8194 0.8309
-0.250 0.1592 0.01778 0.00998 -0.0485 0.8123 0.8392
0.000 0.1889 0.01771 0.00987 -0.0488 0.8082 0.8484
0.250 0.2214 0.01759 0.00973 -0.0494 0.8051 0.8565
0.500 0.2422 0.01776 0.00990 -0.0483 0.7971 0.8675
0.750 0.2724 0.01774 0.00990 -0.0487 0.7926 0.8762
1.000 0.3045 0.01765 0.00979 -0.0493 0.7893 0.8868
1.250 0.3315 0.01781 0.00999 -0.0493 0.7827 0.8971
1.500 0.3620 0.01787 0.01007 -0.0499 0.7774 0.9081
1.750 0.3974 0.01782 0.01004 -0.0512 0.7738 0.9190
2.000 0.4336 0.01785 0.01010 -0.0529 0.7695 0.9293
2.250 0.4649 0.01806 0.01037 -0.0540 0.7625 0.9423
2.500 0.5033 0.01802 0.01036 -0.0561 0.7579 0.9538
2.750 0.5418 0.01786 0.01024 -0.0581 0.7488 0.9648
3.000 0.5838 0.01727 0.00963 -0.0600 0.7363 0.9741
3.250 0.6228 0.01685 0.00919 -0.0616 0.7201 0.9851
3.500 0.6613 0.01668 0.00905 -0.0637 0.7051 0.9968
3.750 0.6814 0.01665 0.00904 -0.0624 0.6911 1.0000
4.000 0.6989 0.01663 0.00900 -0.0604 0.6771 1.0000
4.250 0.7190 0.01661 0.00897 -0.0588 0.6620 1.0000
4.500 0.7398 0.01661 0.00897 -0.0572 0.6451 1.0000
4.750 0.7609 0.01664 0.00898 -0.0558 0.6258 1.0000
5.000 0.7827 0.01666 0.00896 -0.0543 0.6036 1.0000
5.250 0.8016 0.01680 0.00908 -0.0525 0.5757 1.0000
5.500 0.8210 0.01695 0.00913 -0.0506 0.5395 1.0000
5.750 0.8386 0.01722 0.00919 -0.0485 0.4868 1.0000
6.000 0.8506 0.01781 0.00933 -0.0455 0.4088 1.0000
6.250 0.8574 0.01878 0.00982 -0.0420 0.3414 1.0000
6.500 0.8656 0.01977 0.01048 -0.0390 0.2912 1.0000
6.750 0.8754 0.02070 0.01116 -0.0363 0.2536 1.0000
7.000 0.8863 0.02155 0.01184 -0.0339 0.2241 1.0000
7.250 0.8975 0.02239 0.01255 -0.0315 0.2013 1.0000
7.500 0.9101 0.02321 0.01327 -0.0294 0.1823 1.0000
7.750 0.9232 0.02405 0.01403 -0.0274 0.1665 1.0000
8.000 0.9366 0.02492 0.01483 -0.0256 0.1536 1.0000
8.250 0.9498 0.02583 0.01568 -0.0238 0.1425 1.0000
8.500 0.9650 0.02666 0.01653 -0.0223 0.1324 1.0000
8.750 0.9789 0.02760 0.01743 -0.0208 0.1242 1.0000
9.000 0.9931 0.02854 0.01836 -0.0193 0.1166 1.0000
9.250 1.0075 0.02952 0.01935 -0.0178 0.1101 1.0000
9.500 1.0219 0.03050 0.02035 -0.0165 0.1041 1.0000
9.750 1.0357 0.03157 0.02141 -0.0151 0.0990 1.0000
10.000 1.0507 0.03258 0.02249 -0.0138 0.0939 1.0000
10.250 1.0635 0.03373 0.02362 -0.0125 0.0899 1.0000
10.500 1.0789 0.03482 0.02480 -0.0113 0.0856 1.0000
10.750 1.0930 0.03595 0.02599 -0.0102 0.0818 1.0000
11.000 1.1057 0.03720 0.02720 -0.0090 0.0789 1.0000
11.250 1.1207 0.03842 0.02857 -0.0079 0.0755 1.0000
11.500 1.1343 0.03968 0.02992 -0.0068 0.0725 1.0000
11.750 1.1468 0.04099 0.03125 -0.0057 0.0701 1.0000
12.000 1.1597 0.04241 0.03271 -0.0046 0.0678 1.0000
12.250 1.1722 0.04389 0.03440 -0.0035 0.0653 1.0000
12.500 1.1832 0.04540 0.03602 -0.0024 0.0631 1.0000
12.750 1.1938 0.04692 0.03758 -0.0014 0.0613 1.0000
13.000 1.2050 0.04854 0.03919 -0.0005 0.0598 1.0000
13.250 1.2124 0.05054 0.04149 0.0006 0.0579 1.0000
13.500 1.2185 0.05257 0.04372 0.0017 0.0562 1.0000
13.750 1.2240 0.05459 0.04587 0.0026 0.0547 1.0000
14.000 1.2299 0.05657 0.04793 0.0035 0.0536 1.0000
14.250 1.2376 0.05849 0.04986 0.0042 0.0525 1.0000
14.500 1.2364 0.06137 0.05299 0.0050 0.0515 1.0000
14.750 1.2310 0.06469 0.05663 0.0057 0.0504 1.0000
15.000 1.2245 0.06816 0.06035 0.0061 0.0494 1.0000
15.250 1.2172 0.07175 0.06416 0.0062 0.0486 1.0000
15.500 1.2096 0.07547 0.06807 0.0060 0.0478 1.0000
15.750 1.2016 0.07935 0.07212 0.0055 0.0471 1.0000
16.000 1.1933 0.08345 0.07637 0.0047 0.0466 1.0000
16.250 1.1847 0.08777 0.08083 0.0036 0.0461 1.0000
16.500 1.1778 0.09200 0.08516 0.0024 0.0457 1.0000
16.750 1.1571 0.09861 0.09200 -0.0004 0.0454 1.0000
17.000 1.1242 0.10793 0.10163 -0.0053 0.0453 1.0000
17.250 1.0828 0.12009 0.11409 -0.0127 0.0454 1.0000
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Polar data table (+)
Polar graphs
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