NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.36 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413-il-1000000.txt Download as CSV file: xf-ls413-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4669 0.12244 0.12060 -0.0372 1.0000 0.0217
-12.750 -0.8453 0.04056 0.03754 -0.0817 1.0000 0.0169
-12.500 -0.8683 0.03859 0.03547 -0.0779 0.9992 0.0169
-12.250 -0.8591 0.03454 0.03115 -0.0826 0.9947 0.0169
-12.000 -0.8412 0.03188 0.02831 -0.0855 0.9916 0.0171
-11.750 -0.7365 0.04664 0.04411 -0.0805 0.9975 0.0208
-11.500 -0.7194 0.04401 0.04144 -0.0829 0.9947 0.0196
-11.250 -0.7235 0.03766 0.03472 -0.0889 0.9876 0.0192
-11.000 -0.7198 0.03138 0.02794 -0.0925 0.9826 0.0188
-10.750 -0.7119 0.02662 0.02271 -0.0934 0.9740 0.0184
-10.500 -0.6918 0.02391 0.01968 -0.0943 0.9689 0.0184
-10.250 -0.6716 0.02226 0.01783 -0.0942 0.9611 0.0185
-10.000 -0.6496 0.02052 0.01587 -0.0942 0.9549 0.0185
-9.750 -0.6271 0.01922 0.01442 -0.0940 0.9474 0.0186
-9.500 -0.6033 0.01814 0.01320 -0.0939 0.9411 0.0187
-9.250 -0.5785 0.01720 0.01216 -0.0939 0.9348 0.0189
-9.000 -0.5533 0.01639 0.01124 -0.0939 0.9288 0.0191
-8.750 -0.5274 0.01567 0.01042 -0.0940 0.9234 0.0193
-8.500 -0.5009 0.01501 0.00969 -0.0941 0.9178 0.0195
-8.250 -0.4742 0.01442 0.00903 -0.0943 0.9123 0.0197
-8.000 -0.4470 0.01393 0.00846 -0.0945 0.9072 0.0199
-7.750 -0.4193 0.01345 0.00794 -0.0948 0.9019 0.0201
-7.500 -0.3918 0.01286 0.00728 -0.0951 0.8968 0.0203
-7.250 -0.3644 0.01202 0.00637 -0.0956 0.8921 0.0208
-7.000 -0.3356 0.01152 0.00586 -0.0962 0.8876 0.0213
-6.750 -0.3066 0.01116 0.00548 -0.0968 0.8830 0.0218
-6.500 -0.2774 0.01085 0.00514 -0.0973 0.8787 0.0223
-6.250 -0.2480 0.01056 0.00481 -0.0978 0.8745 0.0230
-6.000 -0.2182 0.01028 0.00450 -0.0984 0.8702 0.0237
-5.750 -0.1885 0.01005 0.00425 -0.0990 0.8660 0.0243
-5.500 -0.1584 0.00965 0.00381 -0.0997 0.8620 0.0260
-5.250 -0.1284 0.00945 0.00361 -0.1003 0.8581 0.0275
-5.000 -0.0982 0.00927 0.00342 -0.1009 0.8542 0.0291
-4.750 -0.0677 0.00897 0.00312 -0.1017 0.8502 0.0321
-4.500 -0.0377 0.00883 0.00296 -0.1022 0.8463 0.0350
-4.250 -0.0071 0.00861 0.00274 -0.1030 0.8425 0.0405
-4.000 0.0236 0.00840 0.00257 -0.1037 0.8386 0.0476
-3.750 0.0545 0.00816 0.00240 -0.1045 0.8348 0.0659
-3.500 0.0870 0.00762 0.00219 -0.1061 0.8312 0.1552
-3.250 0.1206 0.00700 0.00201 -0.1081 0.8276 0.2878
-3.000 0.1545 0.00643 0.00186 -0.1100 0.8243 0.4082
-2.750 0.1887 0.00588 0.00177 -0.1119 0.8206 0.5470
-2.500 0.2196 0.00578 0.00179 -0.1126 0.8164 0.6012
-2.250 0.2496 0.00582 0.00182 -0.1130 0.8113 0.6238
-2.000 0.2797 0.00580 0.00183 -0.1134 0.8058 0.6395
-1.750 0.3094 0.00582 0.00184 -0.1137 0.8000 0.6531
-1.500 0.3390 0.00589 0.00188 -0.1140 0.7945 0.6669
-1.250 0.3689 0.00593 0.00193 -0.1143 0.7886 0.6784
-1.000 0.3983 0.00593 0.00193 -0.1145 0.7822 0.6843
-0.750 0.4279 0.00595 0.00193 -0.1148 0.7755 0.6877
-0.500 0.4576 0.00597 0.00193 -0.1151 0.7688 0.6912
-0.250 0.4871 0.00603 0.00193 -0.1154 0.7616 0.6947
0.000 0.5163 0.00603 0.00192 -0.1156 0.7500 0.6984
0.250 0.5456 0.00605 0.00193 -0.1159 0.7392 0.7016
0.500 0.5748 0.00611 0.00195 -0.1161 0.7304 0.7046
0.750 0.6044 0.00614 0.00199 -0.1164 0.7220 0.7084
1.000 0.6337 0.00622 0.00203 -0.1166 0.7115 0.7124
1.250 0.6624 0.00626 0.00206 -0.1168 0.6977 0.7168
1.500 0.6910 0.00635 0.00212 -0.1169 0.6826 0.7205
1.750 0.7195 0.00646 0.00218 -0.1170 0.6613 0.7235
2.000 0.7472 0.00665 0.00225 -0.1169 0.6300 0.7262
2.250 0.7729 0.00703 0.00237 -0.1166 0.5725 0.7286
2.500 0.7962 0.00763 0.00262 -0.1159 0.4917 0.7312
2.750 0.8187 0.00835 0.00295 -0.1151 0.4046 0.7337
3.000 0.8426 0.00892 0.00324 -0.1145 0.3413 0.7363
3.250 0.8667 0.00945 0.00351 -0.1140 0.2867 0.7391
3.500 0.8916 0.00990 0.00377 -0.1137 0.2461 0.7418
3.750 0.9164 0.01035 0.00403 -0.1133 0.2068 0.7445
4.000 0.9416 0.01073 0.00427 -0.1129 0.1790 0.7473
4.250 0.9670 0.01106 0.00452 -0.1126 0.1596 0.7501
4.500 0.9926 0.01137 0.00477 -0.1123 0.1436 0.7529
4.750 1.0183 0.01167 0.00501 -0.1120 0.1295 0.7560
5.000 1.0438 0.01198 0.00526 -0.1116 0.1173 0.7591
5.250 1.0693 0.01229 0.00552 -0.1113 0.1079 0.7618
5.500 1.0945 0.01258 0.00578 -0.1109 0.1006 0.7650
5.750 1.1199 0.01284 0.00606 -0.1106 0.0948 0.7680
6.000 1.1450 0.01313 0.00633 -0.1102 0.0898 0.7712
6.250 1.1692 0.01349 0.00667 -0.1096 0.0838 0.7748
6.500 1.1949 0.01372 0.00692 -0.1093 0.0808 0.7781
6.750 1.2191 0.01402 0.00722 -0.1088 0.0767 0.7817
7.000 1.2423 0.01441 0.00760 -0.1080 0.0719 0.7852
7.250 1.2672 0.01464 0.00787 -0.1076 0.0698 0.7890
7.500 1.2910 0.01496 0.00819 -0.1070 0.0667 0.7928
7.750 1.3135 0.01535 0.00857 -0.1062 0.0629 0.7965
8.000 1.3363 0.01569 0.00896 -0.1054 0.0605 0.8003
8.250 1.3594 0.01598 0.00929 -0.1046 0.0584 0.8045
8.500 1.3814 0.01637 0.00967 -0.1037 0.0557 0.8087
8.750 1.4009 0.01688 0.01018 -0.1024 0.0521 0.8130
9.000 1.4227 0.01717 0.01053 -0.1015 0.0506 0.8175
9.250 1.4432 0.01754 0.01093 -0.1003 0.0485 0.8225
9.500 1.4616 0.01800 0.01140 -0.0988 0.0461 0.8273
9.750 1.4752 0.01855 0.01199 -0.0964 0.0436 0.8325
10.000 1.4937 0.01894 0.01244 -0.0949 0.0424 0.8379
10.250 1.5114 0.01942 0.01296 -0.0933 0.0406 0.8433
10.500 1.5275 0.02000 0.01357 -0.0916 0.0387 0.8490
10.750 1.5416 0.02076 0.01436 -0.0896 0.0366 0.8554
11.000 1.5591 0.02126 0.01494 -0.0881 0.0356 0.8617
11.250 1.5755 0.02185 0.01558 -0.0866 0.0342 0.8690
11.500 1.5903 0.02256 0.01632 -0.0849 0.0326 0.8765
11.750 1.6012 0.02355 0.01736 -0.0827 0.0307 0.8858
12.000 1.6171 0.02414 0.01805 -0.0812 0.0301 0.8964
12.250 1.6314 0.02481 0.01882 -0.0795 0.0291 0.9115
12.500 1.6388 0.02541 0.01956 -0.0765 0.0283 1.0000
12.750 1.6520 0.02639 0.02056 -0.0750 0.0273 1.0000
13.000 1.6623 0.02760 0.02180 -0.0733 0.0263 1.0000
13.250 1.6718 0.02886 0.02313 -0.0715 0.0255 1.0000
13.500 1.6850 0.02985 0.02419 -0.0701 0.0251 1.0000
13.750 1.6973 0.03091 0.02531 -0.0688 0.0245 1.0000
14.000 1.7090 0.03204 0.02650 -0.0674 0.0239 1.0000
14.250 1.7193 0.03329 0.02780 -0.0660 0.0233 1.0000
14.500 1.7279 0.03470 0.02925 -0.0646 0.0227 1.0000
14.750 1.7343 0.03633 0.03094 -0.0630 0.0221 1.0000
15.000 1.7366 0.03836 0.03305 -0.0613 0.0215 1.0000
15.250 1.7400 0.04032 0.03511 -0.0598 0.0212 1.0000
15.500 1.7478 0.04191 0.03678 -0.0586 0.0209 1.0000
15.750 1.7537 0.04372 0.03868 -0.0575 0.0207 1.0000
16.000 1.7586 0.04569 0.04073 -0.0564 0.0204 1.0000
16.250 1.7630 0.04774 0.04287 -0.0555 0.0200 1.0000
16.500 1.7665 0.04994 0.04515 -0.0546 0.0197 1.0000
16.750 1.7691 0.05231 0.04761 -0.0539 0.0194 1.0000
17.000 1.7703 0.05491 0.05030 -0.0533 0.0190 1.0000
17.250 1.7699 0.05779 0.05326 -0.0529 0.0187 1.0000
17.500 1.7668 0.06107 0.05662 -0.0526 0.0183 1.0000
17.750 1.7598 0.06496 0.06062 -0.0526 0.0180 1.0000
18.000 1.7498 0.06942 0.06519 -0.0529 0.0178 1.0000
18.250 1.7359 0.07465 0.07055 -0.0537 0.0175 1.0000
18.500 1.7290 0.07903 0.07505 -0.0546 0.0174 1.0000
18.750 1.7212 0.08365 0.07980 -0.0558 0.0172 1.0000
19.000 1.7116 0.08869 0.08497 -0.0573 0.0171 1.0000
19.250 1.6990 0.09436 0.09077 -0.0593 0.0170 1.0000
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Polar data table (+)
Polar graphs
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