NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Reynolds number: 500,000 Max Cl/Cd: 52.72 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls013-il-500000.txt Download as CSV file: xf-ls013-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0846 0.11689 0.11417 0.0155 1.0000 0.0213
-17.000 -1.1328 0.10200 0.09903 0.0061 1.0000 0.0212
-16.750 -1.1658 0.09107 0.08788 -0.0008 1.0000 0.0211
-16.500 -1.1919 0.08214 0.07874 -0.0063 1.0000 0.0211
-16.250 -1.2128 0.07482 0.07121 -0.0104 1.0000 0.0212
-16.000 -1.2295 0.06879 0.06498 -0.0134 1.0000 0.0213
-15.750 -1.2432 0.06370 0.05968 -0.0155 1.0000 0.0214
-15.500 -1.2620 0.05823 0.05400 -0.0169 1.0000 0.0216
-15.250 -1.2748 0.05374 0.04935 -0.0174 1.0000 0.0219
-15.000 -1.2787 0.05054 0.04605 -0.0175 1.0000 0.0221
-14.750 -1.2784 0.04792 0.04335 -0.0175 1.0000 0.0224
-14.500 -1.2766 0.04558 0.04092 -0.0174 1.0000 0.0227
-14.250 -1.2736 0.04341 0.03867 -0.0170 1.0000 0.0230
-14.000 -1.2701 0.04134 0.03649 -0.0165 1.0000 0.0234
-13.750 -1.2661 0.03936 0.03438 -0.0158 1.0000 0.0238
-13.500 -1.2610 0.03752 0.03241 -0.0150 1.0000 0.0242
-13.250 -1.2545 0.03583 0.03057 -0.0141 1.0000 0.0247
-13.000 -1.2469 0.03432 0.02891 -0.0130 1.0000 0.0252
-12.750 -1.2381 0.03303 0.02746 -0.0119 1.0000 0.0256
-12.500 -1.2309 0.03092 0.02522 -0.0104 1.0000 0.0262
-12.250 -1.2197 0.02954 0.02379 -0.0092 1.0000 0.0268
-12.000 -1.2070 0.02853 0.02275 -0.0080 1.0000 0.0273
-11.750 -1.1937 0.02764 0.02180 -0.0066 1.0000 0.0279
-11.500 -1.1774 0.02675 0.02083 -0.0056 1.0000 0.0286
-11.250 -1.1592 0.02590 0.01989 -0.0048 1.0000 0.0294
-11.000 -1.1395 0.02515 0.01903 -0.0042 1.0000 0.0302
-10.750 -1.1195 0.02421 0.01798 -0.0036 1.0000 0.0310
-10.500 -1.1011 0.02283 0.01658 -0.0030 1.0000 0.0320
-10.250 -1.0790 0.02209 0.01584 -0.0028 1.0000 0.0329
-10.000 -1.0556 0.02141 0.01513 -0.0027 1.0000 0.0340
-9.750 -1.0311 0.02078 0.01444 -0.0028 1.0000 0.0353
-9.500 -1.0050 0.02028 0.01385 -0.0031 1.0000 0.0364
-9.250 -0.9811 0.01910 0.01264 -0.0033 0.9666 0.0380
-9.000 -0.9594 0.01859 0.01209 -0.0026 0.9496 0.0394
-8.750 -0.9385 0.01817 0.01161 -0.0015 0.9380 0.0409
-8.500 -0.9165 0.01778 0.01113 -0.0006 0.9285 0.0425
-8.250 -0.8943 0.01724 0.01051 0.0001 0.9203 0.0441
-8.000 -0.8736 0.01657 0.00983 0.0010 0.9127 0.0465
-7.750 -0.8492 0.01618 0.00941 0.0014 0.9061 0.0486
-7.500 -0.8244 0.01583 0.00899 0.0018 0.8998 0.0507
-7.250 -0.8016 0.01526 0.00836 0.0025 0.8943 0.0532
-7.000 -0.7764 0.01480 0.00791 0.0026 0.8884 0.0562
-6.750 -0.7508 0.01449 0.00756 0.0029 0.8830 0.0592
-6.500 -0.7254 0.01414 0.00714 0.0032 0.8782 0.0619
-6.250 -0.6997 0.01363 0.00666 0.0033 0.8730 0.0662
-6.000 -0.6730 0.01335 0.00634 0.0033 0.8683 0.0703
-5.750 -0.6474 0.01295 0.00592 0.0036 0.8641 0.0760
-5.500 -0.6201 0.01264 0.00562 0.0034 0.8594 0.0827
-5.250 -0.5933 0.01222 0.00526 0.0034 0.8547 0.0934
-5.000 -0.5666 0.01185 0.00494 0.0034 0.8506 0.1092
-4.750 -0.5403 0.01143 0.00464 0.0034 0.8470 0.1367
-4.500 -0.5132 0.01087 0.00432 0.0031 0.8427 0.1815
-4.250 -0.4870 0.01021 0.00399 0.0029 0.8384 0.2552
-4.000 -0.4606 0.00957 0.00370 0.0026 0.8345 0.3367
-3.750 -0.4342 0.00898 0.00341 0.0024 0.8312 0.4158
-3.500 -0.4073 0.00823 0.00319 0.0021 0.8274 0.5343
-3.250 -0.3791 0.00796 0.00317 0.0019 0.8234 0.6044
-3.000 -0.3503 0.00789 0.00316 0.0018 0.8197 0.6382
-2.750 -0.3215 0.00788 0.00316 0.0017 0.8164 0.6592
-2.500 -0.2921 0.00790 0.00318 0.0015 0.8132 0.6757
-2.250 -0.2625 0.00791 0.00321 0.0012 0.8094 0.6914
-2.000 -0.2332 0.00793 0.00324 0.0010 0.8056 0.7047
-1.750 -0.2037 0.00797 0.00324 0.0007 0.8022 0.7154
-1.500 -0.1750 0.00802 0.00330 0.0008 0.7992 0.7254
-1.250 -0.1457 0.00809 0.00339 0.0006 0.7958 0.7370
-1.000 -0.1162 0.00816 0.00345 0.0004 0.7911 0.7478
-0.750 -0.0875 0.00815 0.00346 0.0004 0.7863 0.7540
-0.500 -0.0587 0.00818 0.00345 0.0004 0.7820 0.7593
-0.250 -0.0287 0.00818 0.00345 0.0000 0.7766 0.7656
0.000 0.0000 0.00816 0.00347 0.0000 0.7710 0.7710
0.250 0.0286 0.00818 0.00345 0.0000 0.7656 0.7766
0.500 0.0587 0.00818 0.00345 -0.0004 0.7593 0.7820
0.750 0.0875 0.00815 0.00346 -0.0004 0.7540 0.7863
1.000 0.1162 0.00816 0.00345 -0.0004 0.7478 0.7911
1.250 0.1457 0.00809 0.00339 -0.0006 0.7370 0.7958
1.500 0.1750 0.00802 0.00330 -0.0008 0.7255 0.7992
1.750 0.2037 0.00797 0.00323 -0.0007 0.7153 0.8022
2.000 0.2331 0.00793 0.00323 -0.0010 0.7045 0.8056
2.250 0.2625 0.00791 0.00321 -0.0012 0.6913 0.8094
2.500 0.2921 0.00790 0.00318 -0.0015 0.6760 0.8132
2.750 0.3215 0.00788 0.00316 -0.0017 0.6592 0.8164
3.000 0.3503 0.00789 0.00316 -0.0018 0.6381 0.8197
3.250 0.3790 0.00796 0.00317 -0.0019 0.6039 0.8234
3.500 0.4072 0.00823 0.00319 -0.0021 0.5342 0.8274
3.750 0.4341 0.00898 0.00341 -0.0024 0.4158 0.8312
4.000 0.4606 0.00957 0.00370 -0.0026 0.3367 0.8345
4.250 0.4870 0.01020 0.00399 -0.0029 0.2553 0.8384
4.500 0.5132 0.01087 0.00432 -0.0031 0.1815 0.8427
4.750 0.5403 0.01143 0.00464 -0.0034 0.1367 0.8470
5.000 0.5666 0.01185 0.00494 -0.0034 0.1092 0.8506
5.250 0.5933 0.01222 0.00526 -0.0034 0.0933 0.8547
5.500 0.6201 0.01264 0.00562 -0.0034 0.0826 0.8594
5.750 0.6474 0.01295 0.00593 -0.0036 0.0759 0.8641
6.000 0.6731 0.01335 0.00634 -0.0033 0.0703 0.8683
6.250 0.6997 0.01363 0.00666 -0.0033 0.0662 0.8730
6.500 0.7255 0.01414 0.00714 -0.0032 0.0619 0.8782
6.750 0.7508 0.01449 0.00756 -0.0029 0.0592 0.8829
7.000 0.7765 0.01479 0.00791 -0.0026 0.0562 0.8884
7.250 0.8017 0.01526 0.00836 -0.0025 0.0532 0.8943
7.500 0.8245 0.01583 0.00899 -0.0018 0.0507 0.8998
7.750 0.8493 0.01618 0.00941 -0.0014 0.0486 0.9061
8.000 0.8736 0.01657 0.00983 -0.0011 0.0465 0.9127
8.250 0.8944 0.01724 0.01051 -0.0001 0.0441 0.9203
8.500 0.9166 0.01778 0.01113 0.0006 0.0425 0.9285
8.750 0.9386 0.01817 0.01161 0.0015 0.0409 0.9380
9.000 0.9595 0.01859 0.01209 0.0025 0.0394 0.9496
9.250 0.9812 0.01911 0.01264 0.0033 0.0380 0.9666
9.500 1.0052 0.02028 0.01385 0.0030 0.0364 1.0000
9.750 1.0313 0.02079 0.01445 0.0027 0.0353 1.0000
10.000 1.0558 0.02142 0.01514 0.0026 0.0340 1.0000
10.250 1.0792 0.02210 0.01584 0.0027 0.0330 1.0000
10.500 1.1013 0.02283 0.01659 0.0029 0.0320 1.0000
10.750 1.1198 0.02421 0.01798 0.0036 0.0310 1.0000
11.000 1.1398 0.02515 0.01903 0.0042 0.0302 1.0000
11.250 1.1596 0.02591 0.01990 0.0048 0.0294 1.0000
11.500 1.1778 0.02676 0.02084 0.0056 0.0286 1.0000
11.750 1.1942 0.02764 0.02180 0.0065 0.0279 1.0000
12.000 1.2076 0.02853 0.02275 0.0079 0.0273 1.0000
12.250 1.2204 0.02954 0.02380 0.0091 0.0268 1.0000
12.500 1.2316 0.03092 0.02522 0.0103 0.0262 1.0000
12.750 1.2389 0.03301 0.02745 0.0117 0.0256 1.0000
13.000 1.2478 0.03431 0.02891 0.0129 0.0252 1.0000
13.250 1.2554 0.03582 0.03057 0.0139 0.0247 1.0000
13.500 1.2620 0.03751 0.03240 0.0148 0.0242 1.0000
13.750 1.2671 0.03935 0.03438 0.0157 0.0238 1.0000
14.000 1.2714 0.04131 0.03646 0.0163 0.0234 1.0000
14.250 1.2750 0.04337 0.03863 0.0168 0.0230 1.0000
14.500 1.2778 0.04556 0.04091 0.0172 0.0227 1.0000
14.750 1.2799 0.04788 0.04331 0.0173 0.0224 1.0000
15.000 1.2801 0.05051 0.04602 0.0173 0.0221 1.0000
15.250 1.2761 0.05373 0.04934 0.0172 0.0218 1.0000
15.500 1.2628 0.05831 0.05408 0.0166 0.0216 1.0000
15.750 1.2450 0.06363 0.05962 0.0152 0.0214 1.0000
16.000 1.2314 0.06874 0.06493 0.0131 0.0213 1.0000
16.250 1.2141 0.07486 0.07125 0.0101 0.0212 1.0000
16.500 1.1936 0.08213 0.07873 0.0060 0.0211 1.0000
16.750 1.1675 0.09110 0.08792 0.0005 0.0211 1.0000
17.000 1.1336 0.10221 0.09926 -0.0065 0.0212 1.0000
17.250 1.0849 0.11725 0.11454 -0.0161 0.0213 1.0000
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Polar data table (+)
Polar graphs
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