NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Reynolds number: 200,000 Max Cl/Cd: 39.84 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls013-il-200000.txt Download as CSV file: xf-ls013-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0013 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8467 0.10241 0.09874 -0.0047 1.0000 0.0515
-13.000 -0.8492 0.09698 0.09334 -0.0056 1.0000 0.0509
-12.750 -0.8763 0.08764 0.08392 -0.0112 1.0000 0.0500
-12.500 -0.9122 0.07844 0.07458 -0.0167 1.0000 0.0491
-12.250 -0.9497 0.07054 0.06646 -0.0201 1.0000 0.0482
-12.000 -0.9864 0.06381 0.05946 -0.0213 1.0000 0.0475
-11.750 -1.0195 0.05823 0.05357 -0.0204 1.0000 0.0469
-11.500 -1.0445 0.05387 0.04890 -0.0178 1.0000 0.0467
-11.250 -1.0566 0.04992 0.04461 -0.0155 1.0000 0.0468
-11.000 -1.0595 0.04635 0.04069 -0.0137 1.0000 0.0472
-10.750 -1.0557 0.04317 0.03718 -0.0121 1.0000 0.0478
-10.500 -1.0470 0.04046 0.03414 -0.0108 1.0000 0.0489
-10.250 -1.0354 0.03803 0.03132 -0.0096 1.0000 0.0502
-10.000 -1.0211 0.03611 0.02897 -0.0084 1.0000 0.0513
-9.750 -1.0026 0.03291 0.02554 -0.0081 1.0000 0.0526
-9.500 -0.9795 0.03119 0.02379 -0.0082 1.0000 0.0541
-9.250 -0.9561 0.02997 0.02249 -0.0081 1.0000 0.0561
-9.000 -0.9322 0.02871 0.02106 -0.0081 1.0000 0.0584
-8.750 -0.9078 0.02757 0.01967 -0.0080 1.0000 0.0604
-8.500 -0.8818 0.02550 0.01754 -0.0083 1.0000 0.0627
-8.250 -0.8558 0.02446 0.01653 -0.0087 1.0000 0.0655
-8.000 -0.8297 0.02360 0.01558 -0.0089 1.0000 0.0689
-7.750 -0.8038 0.02291 0.01473 -0.0091 1.0000 0.0716
-7.500 -0.7799 0.02139 0.01331 -0.0091 1.0000 0.0753
-7.250 -0.7604 0.02078 0.01271 -0.0083 1.0000 0.0790
-7.000 -0.7461 0.02036 0.01220 -0.0064 0.9993 0.0825
-6.750 -0.7119 0.01918 0.01108 -0.0085 0.9942 0.0878
-6.500 -0.6770 0.01850 0.01039 -0.0105 0.9885 0.0945
-6.250 -0.6430 0.01754 0.00949 -0.0125 0.9833 0.1021
-6.000 -0.6096 0.01689 0.00882 -0.0141 0.9771 0.1118
-5.750 -0.5771 0.01614 0.00813 -0.0157 0.9713 0.1254
-5.500 -0.5487 0.01526 0.00744 -0.0167 0.9648 0.1468
-5.250 -0.5222 0.01432 0.00680 -0.0173 0.9583 0.1924
-5.000 -0.5007 0.01313 0.00625 -0.0173 0.9512 0.3047
-4.750 -0.4803 0.01208 0.00584 -0.0167 0.9441 0.4315
-4.500 -0.4594 0.01153 0.00596 -0.0155 0.9378 0.5651
-4.250 -0.4342 0.01161 0.00620 -0.0146 0.9317 0.6279
-4.000 -0.4084 0.01183 0.00642 -0.0138 0.9266 0.6632
-3.750 -0.3818 0.01206 0.00665 -0.0132 0.9207 0.6883
-3.500 -0.3559 0.01235 0.00692 -0.0123 0.9151 0.7085
-3.250 -0.3308 0.01269 0.00722 -0.0111 0.9109 0.7255
-3.000 -0.3037 0.01298 0.00750 -0.0107 0.9055 0.7399
-2.750 -0.2779 0.01326 0.00776 -0.0098 0.9003 0.7528
-2.500 -0.2532 0.01355 0.00800 -0.0086 0.8961 0.7660
-2.250 -0.2277 0.01395 0.00843 -0.0074 0.8915 0.7777
-2.000 -0.2034 0.01435 0.00885 -0.0059 0.8864 0.7896
-1.750 -0.1791 0.01459 0.00906 -0.0046 0.8820 0.8008
-1.500 -0.1543 0.01479 0.00925 -0.0035 0.8782 0.8075
-1.250 -0.1258 0.01484 0.00927 -0.0040 0.8731 0.8156
-1.000 -0.1009 0.01498 0.00941 -0.0030 0.8684 0.8209
-0.750 -0.0751 0.01504 0.00944 -0.0024 0.8647 0.8277
-0.500 -0.0484 0.01511 0.00952 -0.0023 0.8601 0.8338
-0.250 -0.0235 0.01524 0.00967 -0.0013 0.8544 0.8407
0.000 0.0000 0.01523 0.00964 0.0000 0.8489 0.8489
0.250 0.0235 0.01524 0.00967 0.0013 0.8407 0.8544
0.500 0.0483 0.01511 0.00952 0.0023 0.8338 0.8601
0.750 0.0751 0.01504 0.00944 0.0024 0.8277 0.8647
1.000 0.1009 0.01497 0.00941 0.0030 0.8209 0.8684
1.250 0.1258 0.01484 0.00927 0.0040 0.8156 0.8731
1.500 0.1543 0.01479 0.00925 0.0035 0.8076 0.8782
1.750 0.1791 0.01459 0.00906 0.0046 0.8008 0.8820
2.000 0.2034 0.01435 0.00885 0.0059 0.7896 0.8864
2.250 0.2277 0.01395 0.00843 0.0074 0.7777 0.8915
2.500 0.2531 0.01356 0.00800 0.0086 0.7661 0.8961
2.750 0.2779 0.01326 0.00775 0.0098 0.7528 0.9003
3.000 0.3037 0.01298 0.00750 0.0107 0.7399 0.9055
3.250 0.3308 0.01269 0.00722 0.0112 0.7255 0.9109
3.500 0.3558 0.01235 0.00692 0.0123 0.7086 0.9151
3.750 0.3817 0.01206 0.00665 0.0132 0.6883 0.9207
4.000 0.4084 0.01183 0.00642 0.0138 0.6632 0.9266
4.250 0.4341 0.01161 0.00620 0.0146 0.6279 0.9317
4.500 0.4594 0.01153 0.00596 0.0155 0.5651 0.9378
4.750 0.4802 0.01208 0.00584 0.0167 0.4315 0.9441
5.000 0.5007 0.01313 0.00625 0.0173 0.3048 0.9512
5.250 0.5222 0.01432 0.00680 0.0173 0.1924 0.9583
5.500 0.5487 0.01526 0.00744 0.0167 0.1468 0.9648
5.750 0.5771 0.01614 0.00813 0.0157 0.1253 0.9713
6.000 0.6096 0.01689 0.00882 0.0141 0.1118 0.9772
6.250 0.6430 0.01754 0.00949 0.0125 0.1021 0.9834
6.500 0.6771 0.01850 0.01039 0.0105 0.0945 0.9885
6.750 0.7119 0.01918 0.01108 0.0084 0.0878 0.9943
7.000 0.7462 0.02036 0.01220 0.0064 0.0824 0.9994
7.250 0.7603 0.02078 0.01271 0.0083 0.0790 1.0000
7.500 0.7799 0.02139 0.01331 0.0091 0.0753 1.0000
7.750 0.8038 0.02291 0.01473 0.0091 0.0716 1.0000
8.000 0.8298 0.02360 0.01558 0.0089 0.0688 1.0000
8.250 0.8559 0.02446 0.01653 0.0086 0.0655 1.0000
8.500 0.8819 0.02550 0.01754 0.0083 0.0627 1.0000
8.750 0.9079 0.02757 0.01967 0.0080 0.0604 1.0000
9.000 0.9323 0.02872 0.02107 0.0081 0.0584 1.0000
9.250 0.9562 0.02997 0.02250 0.0081 0.0561 1.0000
9.500 0.9796 0.03120 0.02380 0.0081 0.0541 1.0000
9.750 1.0027 0.03291 0.02554 0.0081 0.0526 1.0000
10.000 1.0212 0.03613 0.02899 0.0084 0.0513 1.0000
10.250 1.0356 0.03805 0.03134 0.0095 0.0502 1.0000
10.500 1.0471 0.04048 0.03416 0.0108 0.0489 1.0000
10.750 1.0559 0.04319 0.03720 0.0121 0.0478 1.0000
11.000 1.0597 0.04638 0.04073 0.0136 0.0472 1.0000
11.250 1.0568 0.04995 0.04464 0.0155 0.0468 1.0000
11.500 1.0446 0.05392 0.04896 0.0177 0.0467 1.0000
11.750 1.0197 0.05828 0.05363 0.0203 0.0470 1.0000
12.000 0.9869 0.06385 0.05951 0.0211 0.0475 1.0000
12.250 0.9501 0.07063 0.06655 0.0199 0.0482 1.0000
12.500 0.9127 0.07854 0.07468 0.0165 0.0491 1.0000
12.750 0.8768 0.08778 0.08407 0.0110 0.0500 1.0000
13.000 0.8503 0.09705 0.09341 0.0054 0.0509 1.0000
13.250 0.8480 0.10245 0.09878 0.0045 0.0515 1.0000
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Polar data table (+)
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