NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Reynolds number: 50,000 Max Cl/Cd: 18.63 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls421mod-il-50000-n5.txt Download as CSV file: xf-ls421mod-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421MOD 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4792 0.11665 0.10810 -0.0490 1.0000 0.0833
-14.250 -0.5822 0.09200 0.08310 -0.0633 1.0000 0.0830
-14.000 -0.6380 0.08076 0.07154 -0.0690 1.0000 0.0829
-13.750 -0.6731 0.07369 0.06417 -0.0716 1.0000 0.0832
-13.500 -0.6997 0.06828 0.05845 -0.0727 1.0000 0.0839
-13.250 -0.6987 0.06572 0.05588 -0.0726 1.0000 0.0853
-13.000 -0.6966 0.06346 0.05360 -0.0722 1.0000 0.0869
-12.750 -0.7006 0.06081 0.05083 -0.0716 1.0000 0.0887
-12.500 -0.7073 0.05811 0.04795 -0.0706 1.0000 0.0905
-12.250 -0.7157 0.05554 0.04513 -0.0691 1.0000 0.0923
-12.000 -0.7053 0.05434 0.04406 -0.0677 1.0000 0.0944
-11.750 -0.7020 0.05303 0.04276 -0.0657 1.0000 0.0966
-11.500 -0.7042 0.05166 0.04131 -0.0632 1.0000 0.0990
-11.250 -0.7111 0.05035 0.03985 -0.0600 1.0000 0.1015
-11.000 -0.7098 0.04972 0.03935 -0.0570 1.0000 0.1038
-10.750 -0.7152 0.04905 0.03872 -0.0534 1.0000 0.1062
-10.500 -0.7224 0.04836 0.03796 -0.0495 1.0000 0.1089
-10.250 -0.7286 0.04768 0.03722 -0.0456 1.0000 0.1117
-10.000 -0.7093 0.04675 0.03638 -0.0457 0.9953 0.1167
-9.750 -0.6763 0.04552 0.03510 -0.0478 0.9881 0.1245
-9.500 -0.6457 0.04433 0.03384 -0.0497 0.9801 0.1339
-9.250 -0.6176 0.04323 0.03281 -0.0513 0.9719 0.1437
-9.000 -0.5894 0.04209 0.03172 -0.0530 0.9635 0.1555
-8.750 -0.5654 0.04099 0.03069 -0.0540 0.9542 0.1688
-8.500 -0.5387 0.03981 0.02959 -0.0556 0.9460 0.1851
-8.250 -0.5171 0.03870 0.02857 -0.0563 0.9362 0.2029
-8.000 -0.4913 0.03749 0.02748 -0.0579 0.9278 0.2254
-7.750 -0.4722 0.03640 0.02660 -0.0582 0.9180 0.2486
-7.500 -0.4511 0.03531 0.02568 -0.0589 0.9088 0.2778
-7.250 -0.4312 0.03440 0.02503 -0.0589 0.8996 0.3108
-7.000 -0.4125 0.03373 0.02460 -0.0584 0.8894 0.3483
-6.750 -0.3801 0.03346 0.02465 -0.0588 0.8835 0.3950
-6.500 -0.3611 0.03396 0.02538 -0.0563 0.8720 0.4314
-6.250 -0.3245 0.03481 0.02633 -0.0558 0.8650 0.4695
-6.000 -0.2930 0.03568 0.02717 -0.0548 0.8573 0.4994
-5.750 -0.2735 0.03614 0.02755 -0.0532 0.8466 0.5248
-5.500 -0.2382 0.03686 0.02813 -0.0531 0.8402 0.5467
-5.250 -0.2226 0.03739 0.02857 -0.0509 0.8292 0.5658
-5.000 -0.1964 0.03781 0.02886 -0.0501 0.8210 0.5847
-4.750 -0.1542 0.03882 0.02973 -0.0499 0.8159 0.5963
-4.500 -0.1428 0.03934 0.03019 -0.0471 0.8036 0.6102
-4.250 -0.1170 0.03938 0.03009 -0.0467 0.7964 0.6266
-4.000 -0.0885 0.04010 0.03072 -0.0452 0.7882 0.6370
-3.750 -0.0697 0.04040 0.03094 -0.0434 0.7783 0.6505
-3.500 -0.0443 0.04024 0.03064 -0.0431 0.7721 0.6666
-3.250 -0.0213 0.04093 0.03129 -0.0410 0.7619 0.6737
-2.750 0.0346 0.04074 0.03088 -0.0400 0.7484 0.6948
-2.500 0.0376 0.04095 0.03106 -0.0371 0.7362 0.7070
-2.000 0.0947 0.04071 0.03063 -0.0362 0.7228 0.7221
-1.750 0.1000 0.04077 0.03067 -0.0339 0.7118 0.7325
-1.500 0.1333 0.04052 0.03033 -0.0339 0.7059 0.7380
-1.250 0.1479 0.04062 0.03039 -0.0322 0.6969 0.7460
-1.000 0.1622 0.04055 0.03027 -0.0308 0.6881 0.7545
-0.750 0.1960 0.04020 0.02984 -0.0310 0.6829 0.7599
-0.500 0.2036 0.04055 0.03018 -0.0286 0.6725 0.7678
-0.250 0.2227 0.04040 0.02998 -0.0277 0.6649 0.7753
0.000 0.2572 0.03995 0.02945 -0.0282 0.6602 0.7800
0.250 0.2595 0.04052 0.03005 -0.0252 0.6487 0.7866
0.500 0.2824 0.04026 0.02972 -0.0252 0.6419 0.7934
0.750 0.3182 0.03972 0.02910 -0.0258 0.6376 0.7973
1.000 0.3158 0.04054 0.02999 -0.0222 0.6250 0.8028
1.250 0.3455 0.04015 0.02953 -0.0226 0.6191 0.8079
1.500 0.3615 0.04034 0.02971 -0.0218 0.6109 0.8135
1.750 0.3751 0.04058 0.02997 -0.0200 0.6015 0.8176
2.000 0.4100 0.04002 0.02935 -0.0206 0.5964 0.8217
2.250 0.4124 0.04084 0.03021 -0.0182 0.5853 0.8271
2.500 0.4399 0.04069 0.03002 -0.0187 0.5781 0.8319
2.750 0.4780 0.03994 0.02922 -0.0194 0.5738 0.8351
3.000 0.4688 0.04125 0.03063 -0.0156 0.5608 0.8400
3.250 0.5034 0.04075 0.03009 -0.0164 0.5552 0.8440
3.500 0.5150 0.04145 0.03082 -0.0154 0.5456 0.8489
3.750 0.5327 0.04166 0.03104 -0.0144 0.5369 0.8527
4.000 0.5746 0.04076 0.03009 -0.0156 0.5323 0.8557
4.250 0.5624 0.04249 0.03193 -0.0121 0.5191 0.8606
4.500 0.6032 0.04178 0.03119 -0.0136 0.5132 0.8645
4.750 0.6014 0.04302 0.03250 -0.0111 0.5019 0.8690
5.000 0.6286 0.04272 0.03220 -0.0108 0.4941 0.8726
5.250 0.6776 0.04148 0.03088 -0.0127 0.4887 0.8756
5.500 0.6648 0.04355 0.03309 -0.0099 0.4749 0.8802
5.750 0.7184 0.04184 0.03129 -0.0118 0.4696 0.8834
6.000 0.6996 0.04435 0.03395 -0.0085 0.4555 0.8885
6.250 0.7478 0.04267 0.03219 -0.0095 0.4499 0.8924
6.500 0.7378 0.04534 0.03501 -0.0081 0.4358 0.8973
6.750 0.7827 0.04365 0.03325 -0.0086 0.4300 0.9006
7.000 0.7707 0.04644 0.03618 -0.0070 0.4162 0.9051
7.250 0.8179 0.04466 0.03432 -0.0077 0.4100 0.9090
7.500 0.8062 0.04765 0.03747 -0.0065 0.3963 0.9138
7.750 0.8512 0.04568 0.03539 -0.0065 0.3901 0.9185
8.000 0.8374 0.04902 0.03890 -0.0055 0.3764 0.9239
8.250 0.8755 0.04768 0.03748 -0.0055 0.3692 0.9286
8.500 0.8670 0.05062 0.04057 -0.0048 0.3564 0.9338
8.750 0.8861 0.05124 0.04119 -0.0047 0.3470 0.9386
9.000 0.8951 0.05264 0.04264 -0.0044 0.3365 0.9440
9.250 0.9000 0.05463 0.04471 -0.0043 0.3262 0.9499
9.500 0.9185 0.05514 0.04522 -0.0041 0.3171 0.9565
9.750 0.9148 0.05817 0.04836 -0.0042 0.3065 0.9634
10.000 0.9380 0.05822 0.04838 -0.0042 0.2986 0.9716
10.250 0.9280 0.06211 0.05240 -0.0048 0.2884 0.9813
10.500 0.9474 0.06227 0.05256 -0.0048 0.2809 1.0000
10.750 0.9401 0.06673 0.05715 -0.0062 0.2714 1.0000
11.000 0.9610 0.06779 0.05819 -0.0071 0.2642 1.0000
11.250 0.9652 0.07098 0.06144 -0.0084 0.2566 1.0000
11.500 0.9607 0.07532 0.06589 -0.0100 0.2483 1.0000
11.750 1.0125 0.07244 0.06284 -0.0098 0.2442 1.0000
12.000 0.9366 0.08671 0.07753 -0.0142 0.2327 1.0000
12.250 0.9804 0.08446 0.07518 -0.0140 0.2292 1.0000
12.500 0.8936 0.10207 0.09312 -0.0204 0.2164 1.0000
12.750 0.9277 0.10095 0.09198 -0.0205 0.2135 1.0000
13.000 0.9779 0.09733 0.08828 -0.0196 0.2117 1.0000
13.250 0.8789 0.11873 0.10998 -0.0285 0.1981 1.0000
13.500 0.9138 0.11715 0.10838 -0.0283 0.1964 1.0000
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Polar data table (+)
Polar graphs
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