LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 50,000 Max Cl/Cd: 29.87 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188root-il-50000-n5.txt Download as CSV file: xf-l188root-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4858 0.10224 0.09429 -0.0528 1.0000 0.0724
-11.000 -0.4974 0.09573 0.08783 -0.0561 1.0000 0.0722
-10.750 -0.5151 0.08822 0.08035 -0.0602 1.0000 0.0719
-10.500 -0.5415 0.08114 0.07330 -0.0640 1.0000 0.0714
-10.250 -0.5737 0.07555 0.06772 -0.0655 1.0000 0.0708
-10.000 -0.6088 0.07181 0.06398 -0.0638 1.0000 0.0704
-9.750 -0.6430 0.06906 0.06122 -0.0598 1.0000 0.0701
-9.500 -0.6715 0.06606 0.05812 -0.0560 1.0000 0.0700
-9.250 -0.6946 0.06306 0.05496 -0.0522 1.0000 0.0700
-9.000 -0.7123 0.06002 0.05170 -0.0486 1.0000 0.0702
-8.750 -0.7253 0.05696 0.04835 -0.0453 1.0000 0.0708
-8.500 -0.7346 0.05386 0.04488 -0.0421 1.0000 0.0718
-8.250 -0.7410 0.05066 0.04115 -0.0390 1.0000 0.0731
-8.000 -0.7325 0.04900 0.03947 -0.0371 1.0000 0.0748
-7.750 -0.7238 0.04731 0.03767 -0.0352 1.0000 0.0766
-7.500 -0.7152 0.04525 0.03535 -0.0332 1.0000 0.0784
-7.250 -0.7051 0.04313 0.03288 -0.0314 1.0000 0.0806
-7.000 -0.6937 0.04100 0.03019 -0.0296 1.0000 0.0836
-6.750 -0.6775 0.03966 0.02888 -0.0285 0.9998 0.0863
-6.500 -0.6474 0.03807 0.02708 -0.0298 0.9954 0.0902
-6.250 -0.6168 0.03643 0.02497 -0.0310 0.9908 0.0956
-6.000 -0.5862 0.03525 0.02384 -0.0323 0.9862 0.1005
-5.750 -0.5537 0.03412 0.02241 -0.0336 0.9822 0.1074
-5.500 -0.5245 0.03312 0.02146 -0.0344 0.9771 0.1139
-5.250 -0.4916 0.03226 0.02039 -0.0356 0.9726 0.1230
-5.000 -0.4613 0.03146 0.01965 -0.0366 0.9681 0.1325
-4.750 -0.4329 0.03072 0.01891 -0.0371 0.9627 0.1440
-4.500 -0.4011 0.03001 0.01819 -0.0383 0.9581 0.1591
-4.250 -0.3734 0.02932 0.01755 -0.0389 0.9527 0.1774
-4.000 -0.3460 0.02863 0.01692 -0.0395 0.9470 0.2030
-3.750 -0.3153 0.02772 0.01630 -0.0410 0.9425 0.2434
-3.500 -0.2926 0.02669 0.01576 -0.0411 0.9366 0.3144
-3.250 -0.2742 0.02573 0.01598 -0.0394 0.9307 0.4886
-3.000 -0.2481 0.02588 0.01644 -0.0380 0.9259 0.6209
-2.750 -0.2290 0.02616 0.01674 -0.0356 0.9190 0.6800
-2.500 -0.2058 0.02645 0.01697 -0.0340 0.9127 0.7267
-2.250 -0.1774 0.02677 0.01722 -0.0330 0.9083 0.7656
-2.000 -0.1609 0.02699 0.01739 -0.0302 0.9010 0.7969
-1.750 -0.1362 0.02727 0.01763 -0.0285 0.8955 0.8297
-1.500 -0.1030 0.02769 0.01802 -0.0277 0.8919 0.8703
-1.250 -0.0585 0.02820 0.01844 -0.0296 0.8887 0.9059
-1.000 -0.0196 0.02848 0.01860 -0.0319 0.8830 0.9246
-0.750 0.0221 0.02862 0.01860 -0.0353 0.8782 0.9356
-0.500 0.0700 0.02876 0.01860 -0.0399 0.8747 0.9448
-0.250 0.1072 0.02894 0.01870 -0.0427 0.8691 0.9564
0.000 0.1477 0.02914 0.01882 -0.0462 0.8632 0.9669
0.250 0.1950 0.02928 0.01890 -0.0509 0.8592 0.9762
0.500 0.2444 0.02938 0.01894 -0.0559 0.8560 0.9855
0.750 0.2749 0.02970 0.01925 -0.0580 0.8479 1.0000
1.000 0.2920 0.02975 0.01927 -0.0571 0.8411 1.0000
1.500 0.3065 0.03008 0.01953 -0.0518 0.8244 1.0000
1.750 0.3130 0.03040 0.01978 -0.0490 0.8157 1.0000
2.000 0.3332 0.03067 0.02002 -0.0483 0.8087 1.0000
2.250 0.3617 0.03092 0.02025 -0.0490 0.8035 1.0000
2.500 0.3722 0.03143 0.02073 -0.0468 0.7935 1.0000
2.750 0.4084 0.03156 0.02087 -0.0484 0.7887 1.0000
3.250 0.4581 0.03209 0.02144 -0.0479 0.7720 1.0000
3.500 0.4719 0.03257 0.02194 -0.0460 0.7598 1.0000
3.750 0.5021 0.03259 0.02202 -0.0462 0.7506 1.0000
4.000 0.5350 0.03236 0.02186 -0.0464 0.7401 1.0000
4.250 0.5584 0.03232 0.02187 -0.0453 0.7264 1.0000
4.500 0.5878 0.03194 0.02159 -0.0446 0.7131 1.0000
4.750 0.6254 0.03113 0.02087 -0.0447 0.7006 1.0000
5.000 0.6631 0.03019 0.02004 -0.0447 0.6872 1.0000
5.250 0.6896 0.02970 0.01966 -0.0433 0.6706 1.0000
5.500 0.7159 0.02916 0.01921 -0.0419 0.6526 1.0000
5.750 0.7313 0.02912 0.01926 -0.0392 0.6308 1.0000
6.000 0.7524 0.02873 0.01898 -0.0370 0.6076 1.0000
6.250 0.7712 0.02846 0.01879 -0.0346 0.5804 1.0000
6.500 0.7884 0.02830 0.01869 -0.0320 0.5467 1.0000
6.750 0.8081 0.02804 0.01841 -0.0296 0.5028 1.0000
7.000 0.8287 0.02788 0.01799 -0.0272 0.4384 1.0000
7.250 0.8448 0.02828 0.01781 -0.0245 0.3686 1.0000
7.500 0.8517 0.02951 0.01858 -0.0215 0.3191 1.0000
7.750 0.8584 0.03091 0.01969 -0.0190 0.2820 1.0000
8.000 0.8664 0.03234 0.02087 -0.0168 0.2539 1.0000
8.250 0.8769 0.03369 0.02209 -0.0150 0.2302 1.0000
8.500 0.8888 0.03502 0.02330 -0.0133 0.2110 1.0000
8.750 0.9023 0.03632 0.02452 -0.0119 0.1945 1.0000
9.000 0.9180 0.03756 0.02571 -0.0107 0.1804 1.0000
9.250 0.9350 0.03877 0.02687 -0.0096 0.1680 1.0000
9.500 0.9536 0.03996 0.02797 -0.0087 0.1574 1.0000
9.750 0.9746 0.04111 0.02925 -0.0080 0.1467 1.0000
10.000 0.9974 0.04230 0.03046 -0.0075 0.1379 1.0000
10.250 1.0189 0.04353 0.03171 -0.0069 0.1300 1.0000
10.500 1.0415 0.04492 0.03324 -0.0064 0.1228 1.0000
10.750 1.0620 0.04633 0.03470 -0.0059 0.1167 1.0000
11.000 1.0827 0.04794 0.03641 -0.0053 0.1112 1.0000
11.250 1.0991 0.04973 0.03842 -0.0045 0.1062 1.0000
11.500 1.1181 0.05129 0.03996 -0.0040 0.1021 1.0000
11.750 1.1288 0.05353 0.04248 -0.0027 0.0984 1.0000
12.000 1.1363 0.05587 0.04511 -0.0014 0.0950 1.0000
12.250 1.1454 0.05798 0.04736 -0.0003 0.0920 1.0000
12.500 1.1615 0.05981 0.04912 0.0003 0.0893 1.0000
12.750 1.1521 0.06314 0.05290 0.0023 0.0874 1.0000
13.000 1.1426 0.06666 0.05678 0.0039 0.0857 1.0000
13.250 1.1317 0.07041 0.06082 0.0051 0.0843 1.0000
13.500 1.1191 0.07439 0.06507 0.0059 0.0831 1.0000
13.750 1.1039 0.07873 0.06964 0.0062 0.0820 1.0000
14.000 1.0863 0.08355 0.07468 0.0060 0.0811 1.0000
14.250 1.0636 0.08928 0.08062 0.0049 0.0805 1.0000
14.500 0.9976 0.10200 0.09373 -0.0008 0.0818 1.0000
14.750 0.8880 0.12956 0.12151 -0.0180 0.0844 1.0000
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