LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 50,000 Max Cl/Cd: 33.41 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188tip-il-50000-n5.txt Download as CSV file: xf-l188tip-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 TIP AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4370 0.10373 0.09623 -0.0489 1.0000 0.0651
-9.750 -0.4444 0.10016 0.09274 -0.0491 1.0000 0.0649
-9.500 -0.4539 0.09659 0.08925 -0.0491 1.0000 0.0646
-9.250 -0.4659 0.09302 0.08577 -0.0490 1.0000 0.0642
-9.000 -0.4813 0.08939 0.08223 -0.0488 1.0000 0.0637
-8.750 -0.5020 0.08567 0.07860 -0.0485 1.0000 0.0631
-8.500 -0.5263 0.08211 0.07513 -0.0476 1.0000 0.0625
-8.250 -0.5464 0.07817 0.07119 -0.0468 1.0000 0.0619
-8.000 -0.5645 0.07410 0.06708 -0.0459 1.0000 0.0615
-7.750 -0.5794 0.06991 0.06278 -0.0450 1.0000 0.0610
-7.500 -0.5902 0.06566 0.05835 -0.0440 1.0000 0.0608
-7.250 -0.5963 0.06145 0.05390 -0.0431 1.0000 0.0607
-7.000 -0.5974 0.05740 0.04953 -0.0421 1.0000 0.0608
-6.750 -0.5938 0.05374 0.04553 -0.0412 1.0000 0.0617
-6.500 -0.5865 0.05026 0.04161 -0.0403 1.0000 0.0633
-6.250 -0.5761 0.04675 0.03752 -0.0396 1.0000 0.0651
-6.000 -0.5618 0.04353 0.03370 -0.0388 1.0000 0.0666
-5.750 -0.5449 0.04139 0.03138 -0.0381 1.0000 0.0680
-5.500 -0.5246 0.03974 0.02954 -0.0378 0.9994 0.0707
-5.250 -0.4936 0.03771 0.02705 -0.0393 0.9957 0.0751
-5.000 -0.4617 0.03559 0.02437 -0.0406 0.9923 0.0786
-4.750 -0.4315 0.03433 0.02305 -0.0418 0.9884 0.0834
-4.500 -0.3981 0.03305 0.02140 -0.0432 0.9848 0.0897
-4.250 -0.3673 0.03192 0.02022 -0.0442 0.9809 0.0956
-4.000 -0.3360 0.03106 0.01910 -0.0449 0.9767 0.1042
-3.750 -0.3037 0.03023 0.01832 -0.0462 0.9730 0.1138
-3.500 -0.2726 0.02952 0.01754 -0.0471 0.9689 0.1258
-3.250 -0.2428 0.02888 0.01686 -0.0478 0.9640 0.1417
-3.000 -0.2102 0.02827 0.01624 -0.0492 0.9598 0.1651
-2.750 -0.1778 0.02756 0.01572 -0.0508 0.9558 0.2019
-2.500 -0.1505 0.02660 0.01522 -0.0517 0.9505 0.2761
-2.250 -0.1269 0.02524 0.01542 -0.0510 0.9466 0.5530
-2.000 -0.1023 0.02520 0.01576 -0.0490 0.9423 0.7196
-1.750 -0.0855 0.02519 0.01584 -0.0458 0.9355 0.8012
-1.500 -0.0522 0.02528 0.01599 -0.0455 0.9309 0.8893
-1.250 0.0163 0.02559 0.01609 -0.0534 0.9285 1.0000
-1.000 0.0386 0.02572 0.01598 -0.0535 0.9210 1.0000
-0.750 0.0667 0.02593 0.01596 -0.0545 0.9144 1.0000
-0.500 0.0990 0.02620 0.01601 -0.0561 0.9091 1.0000
-0.250 0.1202 0.02646 0.01609 -0.0557 0.9010 1.0000
0.000 0.1540 0.02677 0.01623 -0.0575 0.8958 1.0000
0.250 0.1761 0.02709 0.01642 -0.0571 0.8881 1.0000
0.500 0.2060 0.02742 0.01662 -0.0581 0.8819 1.0000
0.750 0.2360 0.02777 0.01687 -0.0591 0.8761 1.0000
1.000 0.2586 0.02815 0.01716 -0.0587 0.8681 1.0000
1.250 0.2933 0.02848 0.01742 -0.0604 0.8632 1.0000
1.500 0.3119 0.02893 0.01782 -0.0594 0.8543 1.0000
1.750 0.3443 0.02927 0.01812 -0.0606 0.8486 1.0000
2.000 0.3657 0.02973 0.01856 -0.0601 0.8403 1.0000
2.250 0.3958 0.03009 0.01891 -0.0609 0.8337 1.0000
2.500 0.4194 0.03054 0.01936 -0.0606 0.8256 1.0000
2.750 0.4489 0.03087 0.01972 -0.0612 0.8183 1.0000
3.000 0.4721 0.03129 0.02016 -0.0608 0.8090 1.0000
3.250 0.5055 0.03147 0.02041 -0.0618 0.8018 1.0000
3.500 0.5269 0.03186 0.02085 -0.0609 0.7907 1.0000
3.750 0.5583 0.03195 0.02102 -0.0614 0.7817 1.0000
4.000 0.5902 0.03189 0.02106 -0.0617 0.7712 1.0000
4.250 0.6162 0.03187 0.02113 -0.0610 0.7578 1.0000
4.500 0.6452 0.03159 0.02096 -0.0604 0.7437 1.0000
4.750 0.6761 0.03107 0.02059 -0.0598 0.7289 1.0000
5.000 0.7073 0.03040 0.02004 -0.0589 0.7133 1.0000
5.250 0.7384 0.02965 0.01944 -0.0580 0.6963 1.0000
5.500 0.7706 0.02880 0.01875 -0.0570 0.6777 1.0000
5.750 0.7945 0.02831 0.01840 -0.0551 0.6550 1.0000
6.000 0.8213 0.02765 0.01785 -0.0534 0.6289 1.0000
6.250 0.8435 0.02726 0.01757 -0.0511 0.5962 1.0000
6.500 0.8611 0.02716 0.01752 -0.0484 0.5540 1.0000
6.750 0.8834 0.02691 0.01715 -0.0461 0.4939 1.0000
7.000 0.9038 0.02705 0.01679 -0.0435 0.4086 1.0000
7.250 0.9121 0.02819 0.01738 -0.0403 0.3388 1.0000
7.500 0.9177 0.02967 0.01846 -0.0373 0.2886 1.0000
7.750 0.9249 0.03119 0.01968 -0.0347 0.2520 1.0000
8.000 0.9342 0.03266 0.02096 -0.0326 0.2231 1.0000
8.250 0.9451 0.03411 0.02224 -0.0307 0.2009 1.0000
8.500 0.9587 0.03546 0.02356 -0.0291 0.1815 1.0000
8.750 0.9740 0.03679 0.02484 -0.0277 0.1656 1.0000
9.000 0.9911 0.03809 0.02611 -0.0265 0.1519 1.0000
9.250 1.0105 0.03936 0.02735 -0.0255 0.1402 1.0000
9.500 1.0319 0.04061 0.02865 -0.0248 0.1295 1.0000
9.750 1.0559 0.04192 0.03010 -0.0243 0.1198 1.0000
10.000 1.0796 0.04333 0.03148 -0.0239 0.1121 1.0000
10.250 1.1015 0.04486 0.03324 -0.0233 0.1046 1.0000
10.500 1.1258 0.04653 0.03491 -0.0231 0.0989 1.0000
10.750 1.1434 0.04842 0.03712 -0.0221 0.0932 1.0000
11.000 1.1626 0.05020 0.03893 -0.0215 0.0890 1.0000
11.250 1.1781 0.05253 0.04154 -0.0205 0.0852 1.0000
11.500 1.1856 0.05493 0.04430 -0.0187 0.0816 1.0000
11.750 1.1940 0.05717 0.04672 -0.0172 0.0787 1.0000
12.000 1.2063 0.05941 0.04902 -0.0162 0.0763 1.0000
12.250 1.2050 0.06249 0.05241 -0.0142 0.0745 1.0000
12.500 1.1944 0.06596 0.05631 -0.0118 0.0730 1.0000
12.750 1.1817 0.06964 0.06033 -0.0097 0.0716 1.0000
13.000 1.1671 0.07358 0.06457 -0.0082 0.0705 1.0000
13.250 1.1500 0.07792 0.06919 -0.0072 0.0696 1.0000
13.500 1.1291 0.08292 0.07445 -0.0070 0.0690 1.0000
13.750 1.1015 0.08908 0.08088 -0.0078 0.0689 1.0000
14.000 1.0626 0.09748 0.08956 -0.0107 0.0694 1.0000
14.250 1.0100 0.10998 0.10228 -0.0174 0.0708 1.0000
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Polar data table (+)
Polar graphs
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