LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 100,000 Max Cl/Cd: 55.37 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188tip-il-100000.txt Download as CSV file: xf-l188tip-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4728 0.09639 0.09163 -0.0346 1.0000 0.1331
-8.250 -0.5103 0.09456 0.08993 -0.0334 1.0000 0.1340
-8.000 -0.5492 0.09148 0.08693 -0.0346 1.0000 0.1346
-7.750 -0.5914 0.08840 0.08373 -0.0364 1.0000 0.1353
-7.500 -0.5369 0.08580 0.08134 -0.0277 1.0000 0.1406
-7.250 -0.5462 0.08298 0.07855 -0.0267 1.0000 0.1441
-7.000 -0.6032 0.07921 0.07439 -0.0332 1.0000 0.1511
-6.750 -0.5829 0.07461 0.07009 -0.0293 1.0000 0.1536
-6.500 -0.5754 0.07233 0.06786 -0.0266 1.0000 0.1572
-6.250 -0.5894 0.06804 0.06329 -0.0294 1.0000 0.1685
-6.000 -0.5782 0.06534 0.06071 -0.0267 1.0000 0.1717
-5.750 -0.5685 0.04660 0.03985 -0.0348 1.0000 0.0904
-5.500 -0.5514 0.04288 0.03590 -0.0346 1.0000 0.0893
-5.250 -0.5322 0.03946 0.03212 -0.0343 1.0000 0.0880
-5.000 -0.5109 0.03630 0.02853 -0.0340 1.0000 0.0864
-4.750 -0.4884 0.03382 0.02557 -0.0336 1.0000 0.0868
-4.500 -0.4654 0.03215 0.02340 -0.0331 1.0000 0.0896
-4.250 -0.4417 0.03045 0.02127 -0.0326 1.0000 0.0917
-4.000 -0.4187 0.02889 0.01965 -0.0324 1.0000 0.0951
-3.750 -0.3873 0.02807 0.01867 -0.0335 0.9978 0.1016
-3.500 -0.3463 0.02689 0.01729 -0.0362 0.9942 0.1084
-3.250 -0.3098 0.02633 0.01661 -0.0382 0.9893 0.1188
-3.000 -0.2707 0.02556 0.01591 -0.0408 0.9853 0.1316
-2.750 -0.2344 0.02498 0.01539 -0.0428 0.9806 0.1489
-2.500 -0.1995 0.02434 0.01497 -0.0447 0.9758 0.1742
-2.250 -0.1595 0.02365 0.01465 -0.0475 0.9721 0.2318
-2.000 -0.1326 0.02165 0.01497 -0.0473 0.9691 0.6772
-1.750 -0.1137 0.02174 0.01532 -0.0442 0.9626 0.7999
-1.500 -0.0867 0.02198 0.01570 -0.0424 0.9579 0.8875
-1.250 -0.0397 0.02225 0.01591 -0.0461 0.9512 1.0000
-1.000 -0.0038 0.02258 0.01601 -0.0488 0.9450 1.0000
-0.750 0.0283 0.02297 0.01618 -0.0507 0.9386 1.0000
-0.500 0.0587 0.02331 0.01635 -0.0522 0.9314 1.0000
-0.250 0.1011 0.02381 0.01668 -0.0558 0.9269 1.0000
0.000 0.1208 0.02414 0.01690 -0.0552 0.9181 1.0000
0.250 0.1589 0.02459 0.01722 -0.0578 0.9126 1.0000
0.500 0.1845 0.02504 0.01758 -0.0581 0.9052 1.0000
0.750 0.2161 0.02545 0.01791 -0.0595 0.8984 1.0000
1.000 0.2597 0.02593 0.01831 -0.0629 0.8943 1.0000
1.250 0.2736 0.02637 0.01870 -0.0611 0.8842 1.0000
1.500 0.3149 0.02676 0.01905 -0.0640 0.8793 1.0000
1.750 0.3325 0.02725 0.01951 -0.0628 0.8695 1.0000
2.000 0.3735 0.02754 0.01979 -0.0654 0.8639 1.0000
2.250 0.3933 0.02801 0.02024 -0.0646 0.8536 1.0000
2.500 0.4365 0.02815 0.02039 -0.0673 0.8478 1.0000
2.750 0.4569 0.02854 0.02080 -0.0664 0.8366 1.0000
3.000 0.5079 0.02829 0.02059 -0.0699 0.8311 1.0000
3.250 0.5318 0.02838 0.02071 -0.0691 0.8183 1.0000
3.500 0.5639 0.02816 0.02054 -0.0693 0.8061 1.0000
3.750 0.6082 0.02738 0.01983 -0.0709 0.7958 1.0000
4.000 0.6603 0.02606 0.01863 -0.0733 0.7868 1.0000
4.500 0.7395 0.02396 0.01674 -0.0742 0.7648 1.0000
4.750 0.7892 0.02219 0.01508 -0.0756 0.7555 1.0000
5.000 0.8243 0.02108 0.01410 -0.0751 0.7411 1.0000
5.250 0.8623 0.01983 0.01295 -0.0749 0.7249 1.0000
5.500 0.8950 0.01887 0.01207 -0.0740 0.7038 1.0000
5.750 0.9253 0.01806 0.01132 -0.0727 0.6762 1.0000
6.000 0.9470 0.01769 0.01096 -0.0703 0.6389 1.0000
6.250 0.9668 0.01746 0.01062 -0.0675 0.5831 1.0000
6.500 0.9783 0.01776 0.01046 -0.0634 0.4807 1.0000
6.750 0.9756 0.01922 0.01096 -0.0577 0.3566 1.0000
7.000 0.9755 0.02091 0.01199 -0.0532 0.2840 1.0000
7.250 0.9821 0.02238 0.01304 -0.0498 0.2397 1.0000
7.500 0.9930 0.02370 0.01408 -0.0472 0.2095 1.0000
7.750 1.0082 0.02507 0.01516 -0.0454 0.1873 1.0000
8.000 1.0267 0.02628 0.01630 -0.0441 0.1686 1.0000
8.250 1.0484 0.02758 0.01750 -0.0433 0.1534 1.0000
8.500 1.0736 0.02900 0.01879 -0.0431 0.1405 1.0000
8.750 1.0974 0.03028 0.02005 -0.0427 0.1298 1.0000
9.000 1.1223 0.03175 0.02164 -0.0424 0.1207 1.0000
9.250 1.1531 0.03360 0.02336 -0.0433 0.1127 1.0000
9.500 1.1731 0.03495 0.02498 -0.0421 0.1062 1.0000
9.750 1.2061 0.03731 0.02718 -0.0435 0.1001 1.0000
10.000 1.2210 0.03882 0.02910 -0.0414 0.0957 1.0000
10.250 1.2407 0.04054 0.03097 -0.0404 0.0913 1.0000
10.500 1.2691 0.04365 0.03405 -0.0413 0.0875 1.0000
10.750 1.2744 0.04554 0.03645 -0.0380 0.0852 1.0000
11.000 1.2812 0.04781 0.03911 -0.0353 0.0825 1.0000
11.250 1.2895 0.05032 0.04190 -0.0330 0.0804 1.0000
11.500 1.3006 0.05285 0.04461 -0.0313 0.0785 1.0000
11.750 1.3145 0.05585 0.04768 -0.0305 0.0765 1.0000
12.000 1.3106 0.05977 0.05190 -0.0275 0.0753 1.0000
12.250 1.2941 0.06246 0.05498 -0.0226 0.0748 1.0000
12.500 1.2747 0.06552 0.05837 -0.0180 0.0745 1.0000
12.750 1.2535 0.06901 0.06217 -0.0141 0.0743 1.0000
13.000 1.2308 0.07294 0.06637 -0.0110 0.0743 1.0000
13.250 1.2070 0.07734 0.07102 -0.0087 0.0745 1.0000
13.500 1.1825 0.08225 0.07615 -0.0073 0.0748 1.0000
13.750 1.1580 0.08769 0.08178 -0.0068 0.0751 1.0000
14.000 1.1359 0.09370 0.08794 -0.0072 0.0755 1.0000
14.250 0.7486 0.12483 0.11983 -0.0142 0.1006 1.0000
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Polar data table (+)
Polar graphs
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