NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 500,000 Max Cl/Cd: 82.47 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413-il-500000-n5.txt Download as CSV file: xf-ls413-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7232 0.06531 0.06231 -0.0686 1.0000 0.0161
-13.250 -0.7619 0.05493 0.05167 -0.0766 1.0000 0.0160
-13.000 -0.7892 0.04843 0.04493 -0.0802 1.0000 0.0160
-12.750 -0.8104 0.04383 0.04012 -0.0813 1.0000 0.0160
-12.500 -0.8312 0.04064 0.03677 -0.0797 1.0000 0.0160
-12.250 -0.8394 0.03715 0.03303 -0.0806 0.9948 0.0160
-12.000 -0.8306 0.03364 0.02921 -0.0837 0.9871 0.0161
-11.750 -0.8133 0.03087 0.02614 -0.0863 0.9823 0.0162
-11.500 -0.7957 0.02878 0.02380 -0.0873 0.9751 0.0163
-11.250 -0.7730 0.02697 0.02175 -0.0888 0.9705 0.0164
-11.000 -0.7513 0.02550 0.02009 -0.0894 0.9642 0.0165
-10.750 -0.7279 0.02404 0.01845 -0.0902 0.9585 0.0166
-10.500 -0.7045 0.02261 0.01688 -0.0908 0.9530 0.0168
-10.250 -0.6809 0.02153 0.01569 -0.0911 0.9465 0.0170
-10.000 -0.6557 0.02061 0.01467 -0.0915 0.9413 0.0171
-9.750 -0.6311 0.01981 0.01380 -0.0917 0.9354 0.0173
-9.500 -0.6059 0.01908 0.01299 -0.0919 0.9297 0.0175
-9.000 -0.5547 0.01773 0.01149 -0.0923 0.9189 0.0179
-8.750 -0.5288 0.01711 0.01078 -0.0925 0.9130 0.0182
-8.500 -0.5025 0.01651 0.01010 -0.0926 0.9079 0.0185
-8.250 -0.4761 0.01593 0.00946 -0.0929 0.9021 0.0188
-8.000 -0.4493 0.01538 0.00884 -0.0931 0.8968 0.0191
-7.500 -0.3944 0.01439 0.00771 -0.0938 0.8876 0.0198
-7.250 -0.3664 0.01396 0.00722 -0.0942 0.8828 0.0201
-7.000 -0.3384 0.01345 0.00668 -0.0946 0.8785 0.0207
-6.750 -0.3099 0.01308 0.00628 -0.0951 0.8744 0.0214
-6.500 -0.2811 0.01274 0.00593 -0.0956 0.8695 0.0222
-6.250 -0.2522 0.01241 0.00557 -0.0961 0.8649 0.0230
-6.000 -0.2231 0.01210 0.00520 -0.0966 0.8609 0.0238
-5.750 -0.1936 0.01178 0.00485 -0.0972 0.8570 0.0248
-5.500 -0.1640 0.01146 0.00454 -0.0979 0.8528 0.0261
-5.250 -0.1344 0.01122 0.00427 -0.0984 0.8488 0.0278
-5.000 -0.1047 0.01100 0.00401 -0.0990 0.8453 0.0296
-4.750 -0.0747 0.01076 0.00378 -0.0997 0.8419 0.0324
-4.500 -0.0447 0.01056 0.00358 -0.1003 0.8380 0.0357
-4.250 -0.0146 0.01035 0.00338 -0.1009 0.8344 0.0405
-4.000 0.0155 0.01015 0.00319 -0.1016 0.8310 0.0466
-3.750 0.0458 0.00996 0.00302 -0.1022 0.8280 0.0577
-3.500 0.0769 0.00962 0.00285 -0.1033 0.8244 0.0952
-3.250 0.1089 0.00910 0.00265 -0.1048 0.8203 0.1801
-3.000 0.1419 0.00850 0.00246 -0.1066 0.8163 0.2974
-2.750 0.1751 0.00798 0.00230 -0.1083 0.8130 0.4061
-2.500 0.2087 0.00749 0.00224 -0.1101 0.8099 0.5319
-2.250 0.2396 0.00738 0.00234 -0.1108 0.8062 0.6016
-2.000 0.2696 0.00740 0.00243 -0.1112 0.8022 0.6353
-1.750 0.2993 0.00746 0.00250 -0.1115 0.7982 0.6570
-1.500 0.3291 0.00750 0.00250 -0.1118 0.7941 0.6657
-1.250 0.3586 0.00750 0.00251 -0.1121 0.7877 0.6697
-1.000 0.3880 0.00753 0.00248 -0.1123 0.7806 0.6741
-0.750 0.4177 0.00755 0.00246 -0.1127 0.7725 0.6793
-0.500 0.4467 0.00757 0.00247 -0.1128 0.7647 0.6832
-0.250 0.4759 0.00760 0.00248 -0.1130 0.7558 0.6872
0.000 0.5049 0.00765 0.00248 -0.1131 0.7453 0.6923
0.250 0.5340 0.00769 0.00251 -0.1133 0.7342 0.6980
0.500 0.5623 0.00775 0.00255 -0.1133 0.7185 0.7030
0.750 0.5904 0.00783 0.00255 -0.1132 0.6978 0.7069
1.000 0.6189 0.00792 0.00257 -0.1133 0.6782 0.7099
1.500 0.6746 0.00818 0.00267 -0.1133 0.6302 0.7150
1.750 0.6998 0.00850 0.00278 -0.1127 0.5769 0.7173
2.000 0.7224 0.00909 0.00301 -0.1118 0.5029 0.7199
2.250 0.7450 0.00974 0.00331 -0.1110 0.4294 0.7229
2.500 0.7683 0.01034 0.00361 -0.1104 0.3682 0.7258
2.750 0.7917 0.01093 0.00391 -0.1098 0.3082 0.7285
3.000 0.8163 0.01136 0.00418 -0.1093 0.2709 0.7310
3.250 0.8408 0.01178 0.00446 -0.1089 0.2361 0.7336
3.500 0.8652 0.01222 0.00474 -0.1084 0.2027 0.7362
3.750 0.8901 0.01261 0.00501 -0.1080 0.1779 0.7392
4.000 0.9154 0.01295 0.00527 -0.1077 0.1615 0.7424
4.250 0.9409 0.01328 0.00554 -0.1074 0.1478 0.7454
4.500 0.9658 0.01360 0.00583 -0.1070 0.1347 0.7478
4.750 0.9905 0.01393 0.00611 -0.1065 0.1233 0.7504
5.000 1.0154 0.01424 0.00640 -0.1061 0.1139 0.7533
5.250 1.0402 0.01456 0.00671 -0.1056 0.1061 0.7565
5.500 1.0646 0.01491 0.00703 -0.1051 0.0992 0.7600
5.750 1.0890 0.01523 0.00735 -0.1046 0.0940 0.7631
6.000 1.1130 0.01555 0.00769 -0.1040 0.0889 0.7659
6.250 1.1361 0.01594 0.00808 -0.1033 0.0839 0.7691
6.500 1.1602 0.01624 0.00842 -0.1028 0.0807 0.7725
6.750 1.1834 0.01660 0.00878 -0.1021 0.0767 0.7761
7.000 1.2055 0.01703 0.00921 -0.1012 0.0727 0.7794
7.250 1.2282 0.01737 0.00960 -0.1004 0.0699 0.7826
7.500 1.2503 0.01774 0.01000 -0.0995 0.0664 0.7864
7.750 1.2714 0.01818 0.01044 -0.0985 0.0631 0.7907
8.000 1.2921 0.01862 0.01091 -0.0974 0.0604 0.7948
8.250 1.3126 0.01900 0.01136 -0.0962 0.0580 0.7987
8.500 1.3316 0.01945 0.01184 -0.0948 0.0553 0.8030
8.750 1.3475 0.01996 0.01236 -0.0929 0.0526 0.8075
9.000 1.3650 0.02044 0.01291 -0.0913 0.0508 0.8117
9.250 1.3829 0.02093 0.01347 -0.0898 0.0488 0.8160
9.500 1.4004 0.02149 0.01407 -0.0883 0.0467 0.8209
9.750 1.4170 0.02213 0.01474 -0.0867 0.0447 0.8258
10.000 1.4334 0.02276 0.01544 -0.0851 0.0430 0.8306
10.250 1.4501 0.02337 0.01613 -0.0837 0.0413 0.8361
10.750 1.4810 0.02481 0.01767 -0.0805 0.0377 0.8479
11.000 1.4953 0.02562 0.01855 -0.0789 0.0363 0.8550
11.250 1.5101 0.02638 0.01941 -0.0773 0.0351 0.8620
11.500 1.5241 0.02721 0.02032 -0.0757 0.0338 0.8702
11.750 1.5371 0.02811 0.02130 -0.0741 0.0326 0.8791
12.000 1.5488 0.02911 0.02236 -0.0723 0.0315 0.8898
12.500 1.5679 0.03108 0.02458 -0.0681 0.0299 0.9330
12.750 1.5761 0.03210 0.02570 -0.0660 0.0292 1.0000
13.000 1.5875 0.03332 0.02700 -0.0647 0.0283 1.0000
13.250 1.5979 0.03464 0.02838 -0.0633 0.0274 1.0000
13.500 1.6069 0.03608 0.02987 -0.0619 0.0266 1.0000
13.750 1.6137 0.03775 0.03161 -0.0605 0.0258 1.0000
14.000 1.6224 0.03927 0.03322 -0.0593 0.0252 1.0000
14.250 1.6306 0.04085 0.03490 -0.0581 0.0245 1.0000
14.500 1.6378 0.04254 0.03669 -0.0569 0.0238 1.0000
14.750 1.6436 0.04440 0.03863 -0.0558 0.0232 1.0000
15.000 1.6483 0.04641 0.04073 -0.0548 0.0227 1.0000
15.250 1.6515 0.04861 0.04301 -0.0538 0.0222 1.0000
15.500 1.6526 0.05111 0.04559 -0.0529 0.0216 1.0000
15.750 1.6516 0.05392 0.04850 -0.0521 0.0212 1.0000
16.000 1.6535 0.05652 0.05123 -0.0516 0.0209 1.0000
16.250 1.6540 0.05934 0.05417 -0.0512 0.0206 1.0000
16.500 1.6530 0.06243 0.05739 -0.0510 0.0202 1.0000
16.750 1.6507 0.06581 0.06089 -0.0510 0.0199 1.0000
17.000 1.6468 0.06950 0.06472 -0.0513 0.0196 1.0000
17.250 1.6419 0.07348 0.06883 -0.0519 0.0193 1.0000
17.500 1.6352 0.07787 0.07334 -0.0528 0.0191 1.0000
17.750 1.6263 0.08271 0.07832 -0.0540 0.0188 1.0000
18.000 1.6156 0.08803 0.08377 -0.0557 0.0186 1.0000
18.250 1.6025 0.09392 0.08980 -0.0579 0.0184 1.0000
18.500 1.5869 0.10042 0.09645 -0.0606 0.0182 1.0000
18.750 1.5685 0.10758 0.10376 -0.0639 0.0181 1.0000
19.000 1.5481 0.11533 0.11166 -0.0677 0.0179 1.0000
19.250 1.5259 0.12359 0.12008 -0.0720 0.0179 1.0000
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Polar data table (+)
Polar graphs
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