LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 200,000 Max Cl/Cd: 72.52 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188root-il-200000.txt Download as CSV file: xf-l188root-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5828 0.07332 0.06933 -0.0712 1.0000 0.0552
-11.000 -0.5898 0.06948 0.06550 -0.0720 1.0000 0.0546
-10.750 -0.7693 0.05933 0.05483 -0.0618 1.0000 0.0485
-10.500 -0.7878 0.05709 0.05253 -0.0572 1.0000 0.0483
-10.250 -0.8064 0.05466 0.05001 -0.0527 1.0000 0.0481
-10.000 -0.8237 0.05194 0.04713 -0.0484 1.0000 0.0479
-9.750 -0.8383 0.04896 0.04393 -0.0443 1.0000 0.0477
-9.500 -0.8343 0.04395 0.03840 -0.0446 0.9963 0.0478
-9.250 -0.8221 0.03967 0.03336 -0.0453 0.9916 0.0486
-9.000 -0.7995 0.03656 0.03010 -0.0465 0.9878 0.0497
-8.750 -0.7684 0.03502 0.02852 -0.0484 0.9847 0.0509
-8.500 -0.7409 0.03289 0.02611 -0.0497 0.9814 0.0521
-8.250 -0.7162 0.03090 0.02377 -0.0501 0.9766 0.0536
-8.000 -0.6858 0.02934 0.02171 -0.0513 0.9729 0.0556
-7.750 -0.6514 0.02751 0.01988 -0.0536 0.9709 0.0578
-7.500 -0.6255 0.02657 0.01886 -0.0537 0.9655 0.0597
-7.250 -0.5939 0.02549 0.01758 -0.0548 0.9615 0.0623
-7.000 -0.5587 0.02422 0.01618 -0.0567 0.9589 0.0654
-6.750 -0.5205 0.02341 0.01538 -0.0592 0.9569 0.0689
-6.500 -0.4967 0.02278 0.01463 -0.0586 0.9504 0.0720
-6.250 -0.4642 0.02178 0.01365 -0.0600 0.9466 0.0761
-6.000 -0.4268 0.02115 0.01300 -0.0621 0.9440 0.0813
-5.750 -0.3883 0.02023 0.01210 -0.0646 0.9421 0.0872
-5.500 -0.3640 0.01984 0.01172 -0.0641 0.9357 0.0931
-5.250 -0.3331 0.01912 0.01105 -0.0651 0.9313 0.1004
-5.000 -0.2971 0.01851 0.01044 -0.0669 0.9283 0.1106
-4.750 -0.2606 0.01792 0.00990 -0.0688 0.9259 0.1235
-4.500 -0.2395 0.01753 0.00957 -0.0678 0.9188 0.1369
-4.250 -0.2118 0.01692 0.00911 -0.0681 0.9137 0.1575
-4.000 -0.1804 0.01623 0.00862 -0.0691 0.9103 0.1927
-3.750 -0.1502 0.01531 0.00812 -0.0700 0.9077 0.2717
-3.500 -0.1413 0.01438 0.00801 -0.0670 0.8979 0.4307
-3.250 -0.1162 0.01391 0.00809 -0.0662 0.8938 0.5844
-3.000 -0.0854 0.01381 0.00809 -0.0661 0.8910 0.6392
-2.750 -0.0656 0.01398 0.00829 -0.0643 0.8827 0.6701
-2.500 -0.0376 0.01399 0.00833 -0.0638 0.8780 0.6958
-2.250 -0.0074 0.01398 0.00831 -0.0637 0.8749 0.7175
-2.000 0.0171 0.01410 0.00842 -0.0627 0.8690 0.7352
-1.750 0.0419 0.01417 0.00849 -0.0617 0.8626 0.7513
-1.500 0.0708 0.01411 0.00841 -0.0614 0.8589 0.7667
-1.250 0.1008 0.01404 0.00831 -0.0613 0.8561 0.7816
-1.000 0.1207 0.01423 0.00853 -0.0596 0.8478 0.7957
-0.750 0.1466 0.01419 0.00852 -0.0585 0.8431 0.8129
-0.500 0.1725 0.01412 0.00848 -0.0571 0.8399 0.8337
-0.250 0.1925 0.01427 0.00868 -0.0552 0.8332 0.8506
0.000 0.2179 0.01423 0.00867 -0.0543 0.8277 0.8597
0.250 0.2476 0.01406 0.00846 -0.0545 0.8241 0.8690
0.500 0.2770 0.01394 0.00835 -0.0544 0.8207 0.8768
0.750 0.2983 0.01410 0.00854 -0.0534 0.8127 0.8874
1.000 0.3274 0.01399 0.00845 -0.0532 0.8086 0.8960
1.250 0.3583 0.01384 0.00827 -0.0535 0.8055 0.9061
1.500 0.3822 0.01404 0.00853 -0.0529 0.7983 0.9170
1.750 0.4132 0.01401 0.00852 -0.0533 0.7934 0.9268
2.000 0.4493 0.01369 0.00817 -0.0543 0.7891 0.9368
2.250 0.4839 0.01335 0.00784 -0.0551 0.7769 0.9456
2.500 0.5199 0.01290 0.00735 -0.0559 0.7653 0.9554
2.750 0.5626 0.01260 0.00701 -0.0584 0.7562 0.9616
3.000 0.6003 0.01254 0.00698 -0.0604 0.7455 0.9710
3.250 0.6447 0.01234 0.00674 -0.0635 0.7362 0.9767
3.500 0.6856 0.01224 0.00667 -0.0662 0.7239 0.9844
3.750 0.7279 0.01214 0.00659 -0.0692 0.7107 0.9919
4.000 0.7709 0.01202 0.00647 -0.0724 0.6960 0.9990
4.250 0.7899 0.01192 0.00636 -0.0709 0.6823 1.0000
4.500 0.8052 0.01185 0.00626 -0.0687 0.6677 1.0000
4.750 0.8220 0.01185 0.00622 -0.0666 0.6505 1.0000
5.000 0.8402 0.01189 0.00624 -0.0646 0.6300 1.0000
5.250 0.8593 0.01196 0.00625 -0.0627 0.6053 1.0000
5.500 0.8775 0.01210 0.00630 -0.0607 0.5728 1.0000
5.750 0.8935 0.01237 0.00639 -0.0582 0.5246 1.0000
6.000 0.9023 0.01299 0.00659 -0.0546 0.4412 1.0000
6.250 0.9025 0.01415 0.00715 -0.0498 0.3494 1.0000
6.500 0.9064 0.01529 0.00785 -0.0459 0.2851 1.0000
6.750 0.9143 0.01628 0.00855 -0.0428 0.2397 1.0000
7.000 0.9243 0.01717 0.00923 -0.0400 0.2083 1.0000
7.250 0.9340 0.01801 0.00990 -0.0372 0.1860 1.0000
7.500 0.9459 0.01881 0.01059 -0.0348 0.1681 1.0000
7.750 0.9583 0.01965 0.01133 -0.0326 0.1540 1.0000
8.000 0.9704 0.02057 0.01214 -0.0304 0.1422 1.0000
8.250 0.9867 0.02127 0.01286 -0.0289 0.1318 1.0000
8.500 1.0011 0.02216 0.01371 -0.0272 0.1232 1.0000
8.750 1.0156 0.02305 0.01453 -0.0255 0.1157 1.0000
9.000 1.0318 0.02390 0.01541 -0.0241 0.1090 1.0000
9.250 1.0471 0.02479 0.01626 -0.0227 0.1032 1.0000
9.500 1.0638 0.02574 0.01723 -0.0214 0.0979 1.0000
9.750 1.0803 0.02658 0.01808 -0.0201 0.0930 1.0000
10.000 1.0979 0.02773 0.01914 -0.0191 0.0886 1.0000
10.250 1.1147 0.02855 0.02009 -0.0178 0.0847 1.0000
10.500 1.1314 0.02947 0.02099 -0.0167 0.0811 1.0000
10.750 1.1522 0.03068 0.02215 -0.0161 0.0777 1.0000
11.000 1.1678 0.03163 0.02325 -0.0148 0.0747 1.0000
11.250 1.1840 0.03260 0.02425 -0.0137 0.0718 1.0000
11.500 1.2075 0.03388 0.02541 -0.0135 0.0690 1.0000
11.750 1.2226 0.03507 0.02679 -0.0122 0.0669 1.0000
12.000 1.2364 0.03623 0.02810 -0.0109 0.0646 1.0000
12.250 1.2510 0.03736 0.02927 -0.0098 0.0625 1.0000
12.500 1.2742 0.03870 0.03052 -0.0096 0.0605 1.0000
12.750 1.2875 0.04039 0.03242 -0.0083 0.0589 1.0000
13.000 1.2962 0.04197 0.03421 -0.0067 0.0574 1.0000
13.250 1.3055 0.04351 0.03590 -0.0053 0.0559 1.0000
13.500 1.3148 0.04499 0.03746 -0.0039 0.0545 1.0000
13.750 1.3302 0.04641 0.03887 -0.0032 0.0532 1.0000
14.000 1.3427 0.04885 0.04143 -0.0023 0.0520 1.0000
14.250 1.3381 0.05124 0.04412 -0.0002 0.0513 1.0000
14.500 1.3330 0.05391 0.04707 0.0017 0.0505 1.0000
14.750 1.3271 0.05675 0.05017 0.0033 0.0498 1.0000
15.000 1.3208 0.05969 0.05333 0.0047 0.0490 1.0000
15.250 1.3156 0.06259 0.05640 0.0057 0.0483 1.0000
15.500 1.3140 0.06524 0.05917 0.0064 0.0476 1.0000
15.750 1.3103 0.06809 0.06214 0.0069 0.0469 1.0000
16.000 1.3091 0.07092 0.06504 0.0072 0.0463 1.0000
16.250 1.3068 0.07445 0.06865 0.0075 0.0457 1.0000
16.500 1.2869 0.07966 0.07408 0.0073 0.0455 1.0000
16.750 1.2600 0.08554 0.08023 0.0062 0.0454 1.0000
17.000 1.2314 0.09225 0.08720 0.0041 0.0454 1.0000
17.250 1.2009 0.09989 0.09508 0.0009 0.0454 1.0000
17.500 1.1639 0.10935 0.10483 -0.0043 0.0456 1.0000
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Polar data table (+)
Polar graphs
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