NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 50,000 Max Cl/Cd: 26.31 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417mod-il-50000-n5.txt Download as CSV file: xf-ls417mod-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4816 0.10130 0.09327 -0.0492 1.0000 0.0632
-11.750 -0.5185 0.08988 0.08178 -0.0563 1.0000 0.0623
-11.500 -0.5692 0.07939 0.07113 -0.0624 1.0000 0.0612
-11.250 -0.6120 0.07241 0.06395 -0.0648 1.0000 0.0606
-11.000 -0.6439 0.06780 0.05917 -0.0646 1.0000 0.0603
-10.750 -0.6717 0.06449 0.05571 -0.0624 1.0000 0.0602
-10.500 -0.6952 0.06184 0.05294 -0.0594 1.0000 0.0602
-10.250 -0.7096 0.05927 0.05022 -0.0568 1.0000 0.0605
-10.000 -0.7193 0.05691 0.04770 -0.0541 1.0000 0.0608
-9.750 -0.7254 0.05465 0.04526 -0.0514 1.0000 0.0613
-9.500 -0.7285 0.05252 0.04293 -0.0488 1.0000 0.0621
-9.250 -0.7296 0.05042 0.04057 -0.0462 1.0000 0.0632
-9.000 -0.7290 0.04823 0.03800 -0.0438 1.0000 0.0646
-8.750 -0.7195 0.04684 0.03662 -0.0420 1.0000 0.0661
-8.500 -0.7094 0.04541 0.03510 -0.0401 1.0000 0.0677
-8.250 -0.6983 0.04380 0.03327 -0.0383 1.0000 0.0695
-8.000 -0.6848 0.04219 0.03140 -0.0366 1.0000 0.0712
-7.750 -0.6696 0.04106 0.03031 -0.0350 1.0000 0.0730
-7.500 -0.6543 0.03996 0.02913 -0.0334 1.0000 0.0757
-7.250 -0.6380 0.03890 0.02797 -0.0318 1.0000 0.0788
-7.000 -0.6215 0.03803 0.02712 -0.0302 1.0000 0.0821
-6.750 -0.6037 0.03717 0.02615 -0.0285 1.0000 0.0858
-6.500 -0.5870 0.03641 0.02547 -0.0269 1.0000 0.0897
-6.250 -0.5701 0.03568 0.02471 -0.0253 1.0000 0.0951
-6.000 -0.5535 0.03497 0.02397 -0.0238 1.0000 0.1016
-5.750 -0.5374 0.03418 0.02326 -0.0225 1.0000 0.1090
-5.500 -0.5177 0.03334 0.02249 -0.0219 0.9990 0.1202
-5.250 -0.4848 0.03224 0.02158 -0.0241 0.9934 0.1410
-5.000 -0.4501 0.03084 0.02055 -0.0271 0.9862 0.1801
-4.750 -0.4106 0.02902 0.01951 -0.0317 0.9783 0.2726
-4.500 -0.3760 0.02787 0.01943 -0.0337 0.9683 0.4192
-4.250 -0.3496 0.02905 0.02127 -0.0298 0.9564 0.5243
-4.000 -0.3115 0.03005 0.02216 -0.0300 0.9442 0.5942
-3.750 -0.2681 0.03103 0.02292 -0.0311 0.9333 0.6369
-3.500 -0.2392 0.03174 0.02349 -0.0296 0.9202 0.6623
-3.250 -0.2069 0.03241 0.02400 -0.0286 0.9101 0.6848
-3.000 -0.1752 0.03294 0.02440 -0.0275 0.8997 0.7050
-2.750 -0.1449 0.03323 0.02455 -0.0266 0.8888 0.7232
-2.500 -0.1083 0.03319 0.02437 -0.0274 0.8783 0.7401
-2.250 -0.0785 0.03315 0.02422 -0.0264 0.8661 0.7510
-2.000 -0.0390 0.03275 0.02366 -0.0279 0.8551 0.7629
-1.750 -0.0134 0.03250 0.02333 -0.0267 0.8401 0.7728
-1.500 0.0223 0.03202 0.02273 -0.0275 0.8275 0.7832
-1.250 0.0528 0.03158 0.02220 -0.0270 0.8116 0.7920
-1.000 0.0779 0.03114 0.02167 -0.0262 0.7932 0.8016
-0.750 0.1062 0.03066 0.02112 -0.0252 0.7743 0.8091
-0.500 0.1322 0.03016 0.02053 -0.0247 0.7529 0.8182
-0.250 0.1587 0.02964 0.01995 -0.0235 0.7283 0.8243
0.000 0.1850 0.02914 0.01935 -0.0227 0.7010 0.8313
0.250 0.2097 0.02871 0.01881 -0.0220 0.6698 0.8380
0.500 0.2388 0.02823 0.01816 -0.0214 0.6375 0.8431
0.750 0.2677 0.02786 0.01754 -0.0211 0.6062 0.8489
1.000 0.2962 0.02762 0.01701 -0.0211 0.5787 0.8544
1.250 0.3245 0.02746 0.01656 -0.0208 0.5551 0.8586
1.500 0.3510 0.02744 0.01629 -0.0206 0.5351 0.8633
1.750 0.3768 0.02753 0.01617 -0.0205 0.5183 0.8679
2.000 0.4037 0.02766 0.01607 -0.0207 0.5044 0.8721
2.250 0.4297 0.02778 0.01607 -0.0206 0.4909 0.8760
2.500 0.4571 0.02797 0.01611 -0.0208 0.4794 0.8799
2.750 0.4843 0.02820 0.01625 -0.0212 0.4685 0.8838
3.000 0.5129 0.02845 0.01639 -0.0218 0.4591 0.8876
3.250 0.5391 0.02868 0.01661 -0.0219 0.4491 0.8914
3.500 0.5691 0.02895 0.01675 -0.0226 0.4408 0.8949
3.750 0.5953 0.02931 0.01714 -0.0230 0.4323 0.8985
4.000 0.6225 0.02966 0.01748 -0.0234 0.4240 0.9023
4.250 0.6527 0.02998 0.01767 -0.0240 0.4170 0.9060
4.500 0.6764 0.03040 0.01820 -0.0240 0.4095 0.9103
4.750 0.7025 0.03085 0.01869 -0.0243 0.4020 0.9143
5.000 0.7323 0.03126 0.01902 -0.0251 0.3955 0.9176
5.250 0.7568 0.03179 0.01964 -0.0251 0.3889 0.9214
5.500 0.7804 0.03234 0.02031 -0.0251 0.3819 0.9261
5.750 0.8074 0.03283 0.02080 -0.0255 0.3756 0.9308
6.000 0.8358 0.03335 0.02127 -0.0261 0.3701 0.9354
6.250 0.8555 0.03412 0.02227 -0.0257 0.3633 0.9407
6.500 0.8800 0.03476 0.02301 -0.0259 0.3569 0.9455
6.750 0.9095 0.03529 0.02349 -0.0267 0.3516 0.9502
7.000 0.9311 0.03619 0.02456 -0.0267 0.3457 0.9562
7.250 0.9517 0.03711 0.02570 -0.0267 0.3391 0.9630
7.500 0.9789 0.03780 0.02643 -0.0274 0.3334 0.9704
7.750 1.0111 0.03843 0.02702 -0.0288 0.3286 0.9787
8.000 1.0219 0.03984 0.02882 -0.0280 0.3218 1.0000
8.250 1.0427 0.04096 0.03006 -0.0282 0.3160 1.0000
8.500 1.0729 0.04163 0.03069 -0.0293 0.3111 1.0000
8.750 1.0865 0.04324 0.03252 -0.0290 0.3055 1.0000
9.000 1.0960 0.04504 0.03459 -0.0283 0.2994 1.0000
9.250 1.1205 0.04598 0.03558 -0.0289 0.2942 1.0000
9.500 1.1496 0.04675 0.03633 -0.0299 0.2897 1.0000
9.750 1.1352 0.04996 0.03996 -0.0275 0.2836 1.0000
10.000 1.1406 0.05185 0.04202 -0.0265 0.2785 1.0000
10.250 1.1769 0.05206 0.04218 -0.0279 0.2740 1.0000
10.500 1.1524 0.05597 0.04639 -0.0253 0.2693 1.0000
10.750 1.0918 0.06368 0.05447 -0.0235 0.2635 1.0000
11.000 1.1047 0.06547 0.05633 -0.0239 0.2589 1.0000
11.250 1.1600 0.06337 0.05414 -0.0244 0.2554 1.0000
11.500 0.9584 0.09241 0.08368 -0.0330 0.2415 1.0000
11.750 0.9980 0.09006 0.08136 -0.0315 0.2398 1.0000
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Polar data table (+)
Polar graphs
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