NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Reynolds number: 100,000 Max Cl/Cd: 37.17 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls421mod-il-100000.txt Download as CSV file: xf-ls421mod-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7794 0.07150 0.06454 -0.0747 1.0000 0.0841
-14.000 -0.8029 0.06698 0.05983 -0.0748 1.0000 0.0840
-13.750 -0.8259 0.06304 0.05569 -0.0740 1.0000 0.0839
-13.500 -0.8484 0.05970 0.05214 -0.0723 1.0000 0.0839
-13.250 -0.8713 0.05706 0.04931 -0.0693 1.0000 0.0839
-13.000 -0.8964 0.05519 0.04731 -0.0647 1.0000 0.0840
-12.750 -0.9202 0.05354 0.04550 -0.0600 1.0000 0.0841
-12.500 -0.9180 0.05187 0.04389 -0.0573 1.0000 0.0850
-12.250 -0.9154 0.05090 0.04300 -0.0544 1.0000 0.0861
-12.000 -0.9245 0.04994 0.04201 -0.0504 1.0000 0.0870
-11.750 -0.9343 0.04886 0.04085 -0.0464 1.0000 0.0879
-11.500 -0.9425 0.04762 0.03948 -0.0428 1.0000 0.0888
-11.250 -0.9484 0.04624 0.03791 -0.0395 1.0000 0.0900
-11.000 -0.9518 0.04476 0.03617 -0.0366 1.0000 0.0912
-10.750 -0.9530 0.04328 0.03435 -0.0340 1.0000 0.0924
-10.500 -0.9197 0.04173 0.03296 -0.0357 0.9965 0.0949
-10.250 -0.8803 0.04022 0.03136 -0.0390 0.9912 0.0986
-10.000 -0.8470 0.03859 0.02957 -0.0412 0.9845 0.1027
-9.750 -0.8071 0.03743 0.02844 -0.0442 0.9790 0.1077
-9.500 -0.7707 0.03608 0.02703 -0.0463 0.9729 0.1131
-9.250 -0.7342 0.03502 0.02597 -0.0487 0.9658 0.1201
-9.000 -0.6905 0.03385 0.02495 -0.0521 0.9614 0.1290
-8.750 -0.6625 0.03287 0.02405 -0.0528 0.9524 0.1378
-8.500 -0.6231 0.03178 0.02307 -0.0556 0.9464 0.1510
-8.250 -0.5901 0.03081 0.02223 -0.0574 0.9393 0.1662
-8.000 -0.5599 0.02983 0.02139 -0.0588 0.9309 0.1849
-7.750 -0.5186 0.02857 0.02038 -0.0622 0.9261 0.2126
-7.500 -0.4974 0.02775 0.01976 -0.0622 0.9158 0.2400
-7.250 -0.4618 0.02654 0.01890 -0.0650 0.9094 0.2831
-7.000 -0.4212 0.02523 0.01808 -0.0686 0.9052 0.3444
-6.750 -0.4056 0.02472 0.01800 -0.0673 0.8934 0.3988
-6.500 -0.3691 0.02454 0.01832 -0.0682 0.8873 0.4714
-6.250 -0.3257 0.02519 0.01915 -0.0690 0.8831 0.5258
-6.000 -0.3100 0.02635 0.02035 -0.0656 0.8703 0.5511
-5.750 -0.2702 0.02750 0.02143 -0.0653 0.8645 0.5750
-5.500 -0.2400 0.02881 0.02269 -0.0635 0.8565 0.5909
-5.250 -0.2138 0.02986 0.02367 -0.0617 0.8467 0.6070
-5.000 -0.1732 0.03159 0.02533 -0.0598 0.8414 0.6148
-4.750 -0.1510 0.03256 0.02624 -0.0576 0.8315 0.6283
-4.500 -0.1180 0.03399 0.02761 -0.0550 0.8234 0.6348
-4.250 -0.0836 0.03434 0.02785 -0.0546 0.8178 0.6487
-4.000 -0.0588 0.03559 0.02908 -0.0516 0.8076 0.6558
-3.750 -0.0334 0.03579 0.02920 -0.0505 0.7993 0.6696
-3.500 0.0080 0.03630 0.02960 -0.0497 0.7944 0.6770
-3.250 0.0172 0.03656 0.02983 -0.0474 0.7828 0.6907
-3.000 0.0548 0.03698 0.03018 -0.0464 0.7761 0.6985
-2.750 0.0841 0.03677 0.02987 -0.0458 0.7710 0.7126
-2.500 0.1070 0.03745 0.03056 -0.0438 0.7596 0.7218
-2.250 0.1284 0.03717 0.03020 -0.0426 0.7525 0.7344
-2.000 0.1709 0.03689 0.02981 -0.0432 0.7480 0.7425
-1.750 0.1706 0.03720 0.03015 -0.0400 0.7357 0.7551
-1.500 0.2119 0.03680 0.02967 -0.0406 0.7295 0.7624
-1.250 0.2217 0.03662 0.02942 -0.0386 0.7226 0.7747
-1.000 0.2508 0.03661 0.02942 -0.0381 0.7125 0.7809
-0.750 0.2734 0.03615 0.02887 -0.0373 0.7064 0.7903
-0.500 0.2938 0.03594 0.02864 -0.0362 0.6984 0.7976
-0.250 0.3173 0.03579 0.02847 -0.0354 0.6891 0.8046
0.000 0.3319 0.03534 0.02793 -0.0339 0.6834 0.8137
0.250 0.3583 0.03521 0.02782 -0.0334 0.6739 0.8189
0.500 0.3799 0.03492 0.02749 -0.0324 0.6657 0.8261
0.750 0.4055 0.03428 0.02675 -0.0320 0.6605 0.8337
1.000 0.4219 0.03445 0.02697 -0.0305 0.6497 0.8395
1.250 0.4428 0.03407 0.02654 -0.0295 0.6425 0.8459
1.500 0.4720 0.03339 0.02573 -0.0298 0.6377 0.8509
1.750 0.4796 0.03374 0.02620 -0.0272 0.6260 0.8556
2.000 0.5095 0.03316 0.02554 -0.0275 0.6196 0.8603
2.250 0.5285 0.03297 0.02530 -0.0266 0.6127 0.8647
2.500 0.5384 0.03308 0.02547 -0.0244 0.6026 0.8691
2.750 0.5777 0.03225 0.02453 -0.0257 0.5967 0.8728
3.000 0.5873 0.03250 0.02484 -0.0236 0.5871 0.8765
3.250 0.6101 0.03221 0.02451 -0.0232 0.5789 0.8808
3.500 0.6535 0.03124 0.02336 -0.0251 0.5730 0.8843
3.750 0.6560 0.03163 0.02391 -0.0220 0.5609 0.8877
4.000 0.6962 0.03076 0.02288 -0.0236 0.5537 0.8910
4.250 0.7057 0.03109 0.02330 -0.0215 0.5432 0.8953
4.500 0.7374 0.03058 0.02271 -0.0222 0.5348 0.8986
4.750 0.7607 0.03041 0.02255 -0.0217 0.5258 0.9015
5.000 0.7831 0.03022 0.02235 -0.0211 0.5159 0.9052
5.250 0.8163 0.02983 0.02186 -0.0220 0.5076 0.9091
5.500 0.8321 0.02998 0.02210 -0.0209 0.4964 0.9124
5.750 0.8682 0.02939 0.02136 -0.0219 0.4878 0.9151
6.000 0.8808 0.02953 0.02161 -0.0201 0.4762 0.9187
6.250 0.9147 0.02915 0.02110 -0.0211 0.4668 0.9226
6.500 0.9310 0.02929 0.02131 -0.0200 0.4550 0.9266
6.750 0.9567 0.02907 0.02103 -0.0197 0.4445 0.9300
7.000 0.9791 0.02895 0.02090 -0.0192 0.4329 0.9335
7.250 0.9971 0.02914 0.02112 -0.0183 0.4212 0.9373
7.500 1.0314 0.02885 0.02063 -0.0194 0.4098 0.9405
7.750 1.0384 0.02917 0.02110 -0.0169 0.3971 0.9453
8.000 1.0611 0.02924 0.02108 -0.0165 0.3853 0.9502
8.250 1.0825 0.02931 0.02108 -0.0160 0.3728 0.9548
8.500 1.0926 0.02977 0.02160 -0.0141 0.3602 0.9597
8.750 1.1156 0.03001 0.02173 -0.0140 0.3481 0.9643
9.000 1.1281 0.03042 0.02213 -0.0126 0.3360 0.9694
9.250 1.1397 0.03113 0.02288 -0.0113 0.3244 0.9753
9.500 1.1667 0.03150 0.02308 -0.0120 0.3129 0.9811
9.750 1.1739 0.03249 0.02419 -0.0108 0.3018 0.9899
10.000 1.1914 0.03318 0.02483 -0.0106 0.2919 1.0000
10.250 1.2082 0.03420 0.02582 -0.0107 0.2819 1.0000
10.500 1.2250 0.03547 0.02711 -0.0110 0.2729 1.0000
10.750 1.2464 0.03650 0.02808 -0.0117 0.2640 1.0000
11.000 1.2625 0.03798 0.02959 -0.0120 0.2561 1.0000
11.250 1.2800 0.03929 0.03091 -0.0125 0.2483 1.0000
11.500 1.3047 0.04053 0.03208 -0.0136 0.2413 1.0000
11.750 1.3105 0.04252 0.03425 -0.0134 0.2349 1.0000
12.000 1.3507 0.04303 0.03449 -0.0154 0.2280 1.0000
12.250 1.3481 0.04559 0.03733 -0.0148 0.2231 1.0000
12.500 1.3562 0.04765 0.03952 -0.0150 0.2178 1.0000
12.750 1.4070 0.04775 0.03929 -0.0175 0.2116 1.0000
13.000 1.3929 0.05103 0.04293 -0.0165 0.2081 1.0000
13.250 1.3878 0.05408 0.04621 -0.0163 0.2042 1.0000
13.500 1.4072 0.05563 0.04775 -0.0172 0.1998 1.0000
13.750 1.4447 0.05645 0.04841 -0.0186 0.1952 1.0000
14.000 1.4196 0.06097 0.05331 -0.0180 0.1927 1.0000
14.250 1.3986 0.06567 0.05831 -0.0181 0.1899 1.0000
14.500 1.3878 0.06980 0.06263 -0.0187 0.1870 1.0000
14.750 1.4270 0.06976 0.06244 -0.0196 0.1832 1.0000
15.000 1.4316 0.07305 0.06581 -0.0203 0.1806 1.0000
15.250 1.3531 0.08399 0.07729 -0.0220 0.1797 1.0000
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Polar data table (+)
Polar graphs
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