NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 200,000 Max Cl/Cd: 69.47 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413-il-200000.txt Download as CSV file: xf-ls413-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3919 0.09506 0.09176 -0.0395 1.0000 0.0748
-10.000 -0.4004 0.09297 0.08971 -0.0377 1.0000 0.0758
-9.750 -0.4116 0.09040 0.08718 -0.0363 1.0000 0.0771
-9.500 -0.4159 0.08474 0.08154 -0.0398 0.9981 0.0795
-9.250 -0.4671 0.07030 0.06707 -0.0543 0.9940 0.0825
-9.000 -0.5188 0.06190 0.05839 -0.0634 0.9844 0.0832
-8.750 -0.5813 0.06917 0.06569 -0.0543 0.9934 0.0775
-8.250 -0.5714 0.05601 0.05179 -0.0686 0.9808 0.0863
-8.000 -0.5506 0.05346 0.04926 -0.0696 0.9767 0.0883
-7.750 -0.5270 0.05055 0.04619 -0.0723 0.9731 0.0926
-7.500 -0.5025 0.04618 0.04141 -0.0771 0.9702 0.1010
-7.250 -0.4746 0.03311 0.02616 -0.0786 0.9654 0.0505
-7.000 -0.4455 0.03028 0.02318 -0.0798 0.9622 0.0493
-6.750 -0.4119 0.02834 0.02095 -0.0816 0.9597 0.0495
-6.500 -0.3764 0.02676 0.01910 -0.0835 0.9578 0.0498
-6.250 -0.3403 0.02515 0.01729 -0.0855 0.9564 0.0499
-6.000 -0.3097 0.02399 0.01597 -0.0863 0.9536 0.0502
-5.750 -0.2850 0.02262 0.01453 -0.0859 0.9492 0.0508
-5.500 -0.2540 0.02136 0.01332 -0.0868 0.9466 0.0523
-5.250 -0.2199 0.02051 0.01251 -0.0884 0.9445 0.0544
-5.000 -0.1835 0.01985 0.01184 -0.0904 0.9428 0.0581
-4.750 -0.1456 0.01891 0.01095 -0.0929 0.9415 0.0627
-4.500 -0.1053 0.01820 0.01027 -0.0959 0.9403 0.0693
-4.250 -0.0862 0.01778 0.00990 -0.0949 0.9333 0.0768
-4.000 -0.0483 0.01708 0.00930 -0.0975 0.9308 0.1003
-3.750 0.0018 0.01441 0.00896 -0.1047 0.9311 0.5840
-3.500 0.0369 0.01467 0.00927 -0.1056 0.9285 0.6500
-3.250 0.0721 0.01495 0.00950 -0.1065 0.9264 0.6807
-3.000 0.1045 0.01529 0.00984 -0.1066 0.9246 0.7005
-2.750 0.1159 0.01594 0.01051 -0.1029 0.9165 0.7170
-2.500 0.1389 0.01655 0.01117 -0.1005 0.9129 0.7384
-2.250 0.1636 0.01705 0.01169 -0.0984 0.9102 0.7574
-2.000 0.1824 0.01744 0.01208 -0.0960 0.9049 0.7679
-1.750 0.2093 0.01755 0.01214 -0.0959 0.8997 0.7755
-1.500 0.2422 0.01748 0.01203 -0.0969 0.8967 0.7807
-1.250 0.2734 0.01745 0.01198 -0.0972 0.8943 0.7859
-1.000 0.3100 0.01740 0.01187 -0.0989 0.8925 0.7947
-0.750 0.3203 0.01780 0.01232 -0.0954 0.8837 0.8002
-0.500 0.3529 0.01773 0.01223 -0.0962 0.8805 0.8061
-0.250 0.3902 0.01750 0.01196 -0.0980 0.8778 0.8112
0.000 0.4108 0.01754 0.01203 -0.0962 0.8703 0.8160
0.250 0.4429 0.01725 0.01173 -0.0966 0.8646 0.8216
0.500 0.4819 0.01678 0.01124 -0.0983 0.8608 0.8266
0.750 0.5029 0.01674 0.01122 -0.0966 0.8518 0.8305
1.000 0.5373 0.01612 0.01059 -0.0969 0.8456 0.8344
1.250 0.5662 0.01582 0.01030 -0.0967 0.8353 0.8386
1.500 0.6025 0.01529 0.00974 -0.0977 0.8287 0.8422
1.750 0.6264 0.01507 0.00955 -0.0965 0.8177 0.8452
2.000 0.6556 0.01466 0.00914 -0.0960 0.8083 0.8488
2.250 0.6849 0.01437 0.00886 -0.0959 0.7977 0.8525
2.500 0.7151 0.01418 0.00870 -0.0963 0.7862 0.8563
2.750 0.7427 0.01390 0.00844 -0.0957 0.7752 0.8596
3.000 0.7703 0.01361 0.00815 -0.0951 0.7631 0.8631
3.250 0.7975 0.01341 0.00799 -0.0947 0.7475 0.8669
3.500 0.8256 0.01326 0.00786 -0.0945 0.7284 0.8710
3.750 0.8506 0.01310 0.00773 -0.0936 0.7050 0.8748
4.000 0.8747 0.01295 0.00757 -0.0924 0.6748 0.8787
4.250 0.8990 0.01294 0.00743 -0.0914 0.6266 0.8828
4.500 0.9197 0.01335 0.00737 -0.0898 0.5341 0.8875
4.750 0.9274 0.01429 0.00770 -0.0859 0.4290 0.8921
5.000 0.9371 0.01539 0.00829 -0.0830 0.3389 0.8972
5.250 0.9510 0.01650 0.00896 -0.0811 0.2704 0.9023
5.500 0.9636 0.01727 0.00949 -0.0786 0.2285 0.9074
5.750 0.9790 0.01806 0.01007 -0.0767 0.2004 0.9137
6.000 0.9963 0.01871 0.01064 -0.0752 0.1808 0.9198
6.250 1.0123 0.01938 0.01122 -0.0733 0.1670 0.9265
6.500 1.0298 0.02006 0.01183 -0.0718 0.1558 0.9336
6.750 1.0477 0.02055 0.01238 -0.0702 0.1465 0.9421
7.000 1.0627 0.02127 0.01301 -0.0683 0.1387 0.9523
7.250 1.0801 0.02160 0.01345 -0.0666 0.1320 0.9678
7.500 1.0994 0.02236 0.01413 -0.0657 0.1253 1.0000
7.750 1.1257 0.02311 0.01497 -0.0662 0.1189 1.0000
8.000 1.1505 0.02396 0.01579 -0.0665 0.1131 1.0000
8.250 1.1765 0.02500 0.01684 -0.0669 0.1076 1.0000
8.500 1.2007 0.02579 0.01769 -0.0670 0.1023 1.0000
8.750 1.2284 0.02715 0.01892 -0.0678 0.0969 1.0000
9.000 1.2498 0.02788 0.01983 -0.0673 0.0930 1.0000
9.250 1.2713 0.02874 0.02074 -0.0670 0.0887 1.0000
9.500 1.3001 0.03033 0.02220 -0.0679 0.0839 1.0000
9.750 1.3173 0.03111 0.02320 -0.0667 0.0810 1.0000
10.000 1.3361 0.03209 0.02430 -0.0659 0.0776 1.0000
10.250 1.3550 0.03309 0.02528 -0.0652 0.0746 1.0000
10.500 1.3795 0.03485 0.02708 -0.0653 0.0712 1.0000
10.750 1.3931 0.03594 0.02837 -0.0637 0.0688 1.0000
11.000 1.4079 0.03716 0.02973 -0.0623 0.0663 1.0000
11.250 1.4233 0.03836 0.03098 -0.0612 0.0642 1.0000
11.500 1.4455 0.04019 0.03278 -0.0611 0.0619 1.0000
11.750 1.4562 0.04218 0.03502 -0.0594 0.0603 1.0000
12.000 1.4625 0.04382 0.03691 -0.0572 0.0588 1.0000
12.250 1.4692 0.04555 0.03883 -0.0551 0.0572 1.0000
12.500 1.4750 0.04730 0.04075 -0.0532 0.0558 1.0000
12.750 1.4816 0.04906 0.04262 -0.0515 0.0547 1.0000
13.000 1.4897 0.05091 0.04455 -0.0500 0.0536 1.0000
13.250 1.4991 0.05351 0.04722 -0.0489 0.0525 1.0000
13.500 1.4939 0.05729 0.05127 -0.0468 0.0517 1.0000
13.750 1.4822 0.06039 0.05467 -0.0443 0.0514 1.0000
14.000 1.4678 0.06400 0.05858 -0.0422 0.0510 1.0000
14.250 1.4502 0.06815 0.06303 -0.0406 0.0507 1.0000
14.500 1.4294 0.07287 0.06804 -0.0395 0.0504 1.0000
14.750 1.4050 0.07829 0.07375 -0.0392 0.0502 1.0000
15.000 1.3766 0.08460 0.08035 -0.0399 0.0501 1.0000
15.250 1.3440 0.09207 0.08809 -0.0419 0.0502 1.0000
15.500 1.3061 0.10130 0.09759 -0.0460 0.0503 1.0000
15.750 1.2610 0.11331 0.10987 -0.0529 0.0508 1.0000
16.000 1.2010 0.13080 0.12759 -0.0647 0.0515 1.0000
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Polar data table (+)
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