LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 500,000 Max Cl/Cd: 77.58 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lds2-il-500000-n5.txt Download as CSV file: xf-lds2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LDS-2 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7631 0.05724 0.05424 -0.0608 1.0000 0.0110
-12.750 -0.7968 0.04829 0.04506 -0.0679 1.0000 0.0110
-12.500 -0.8238 0.04210 0.03861 -0.0715 1.0000 0.0110
-12.250 -0.8420 0.03829 0.03459 -0.0718 1.0000 0.0110
-12.000 -0.8559 0.03563 0.03170 -0.0698 1.0000 0.0111
-11.750 -0.8704 0.03354 0.02941 -0.0658 1.0000 0.0112
-11.500 -0.8794 0.03163 0.02730 -0.0618 1.0000 0.0113
-11.250 -0.8808 0.02991 0.02542 -0.0586 1.0000 0.0114
-11.000 -0.8773 0.02863 0.02403 -0.0557 1.0000 0.0116
-10.500 -0.8420 0.02640 0.02161 -0.0547 0.9937 0.0119
-10.250 -0.8168 0.02522 0.02031 -0.0555 0.9872 0.0121
-10.000 -0.7921 0.02379 0.01868 -0.0561 0.9804 0.0123
-9.750 -0.7637 0.02268 0.01742 -0.0573 0.9747 0.0126
-9.500 -0.7360 0.02144 0.01601 -0.0582 0.9677 0.0130
-9.250 -0.7061 0.02020 0.01459 -0.0595 0.9612 0.0133
-9.000 -0.6770 0.01917 0.01338 -0.0605 0.9524 0.0137
-8.750 -0.6460 0.01823 0.01228 -0.0617 0.9442 0.0140
-8.500 -0.6174 0.01729 0.01122 -0.0624 0.9337 0.0144
-8.250 -0.5902 0.01659 0.01044 -0.0627 0.9224 0.0147
-8.000 -0.5636 0.01610 0.00988 -0.0627 0.9112 0.0152
-7.750 -0.5386 0.01561 0.00930 -0.0624 0.8998 0.0156
-7.500 -0.5143 0.01521 0.00882 -0.0618 0.8888 0.0163
-7.250 -0.4906 0.01473 0.00823 -0.0611 0.8784 0.0168
-7.000 -0.4669 0.01430 0.00769 -0.0604 0.8684 0.0173
-6.750 -0.4441 0.01379 0.00710 -0.0595 0.8589 0.0177
-6.500 -0.4208 0.01334 0.00660 -0.0587 0.8498 0.0183
-6.250 -0.3967 0.01299 0.00619 -0.0580 0.8406 0.0189
-6.000 -0.3723 0.01268 0.00582 -0.0574 0.8326 0.0197
-5.750 -0.3476 0.01238 0.00545 -0.0567 0.8241 0.0207
-5.500 -0.3227 0.01211 0.00511 -0.0561 0.8164 0.0215
-5.250 -0.2985 0.01174 0.00471 -0.0555 0.8081 0.0226
-5.000 -0.2734 0.01148 0.00440 -0.0549 0.8009 0.0236
-4.750 -0.2479 0.01123 0.00411 -0.0544 0.7935 0.0249
-4.500 -0.2224 0.01100 0.00381 -0.0539 0.7866 0.0263
-4.250 -0.1970 0.01074 0.00355 -0.0534 0.7794 0.0283
-4.000 -0.1711 0.01056 0.00332 -0.0530 0.7721 0.0307
-3.750 -0.1452 0.01035 0.00308 -0.0525 0.7654 0.0335
-3.500 -0.1190 0.01017 0.00288 -0.0521 0.7586 0.0370
-3.250 -0.0930 0.00999 0.00269 -0.0517 0.7526 0.0426
-3.000 -0.0667 0.00980 0.00252 -0.0514 0.7461 0.0520
-2.750 -0.0409 0.00959 0.00235 -0.0509 0.7395 0.0706
-2.500 -0.0159 0.00925 0.00218 -0.0504 0.7332 0.1184
-2.250 0.0073 0.00872 0.00197 -0.0498 0.7264 0.2161
-2.000 0.0297 0.00816 0.00182 -0.0489 0.7201 0.3392
-1.750 0.0543 0.00787 0.00176 -0.0483 0.7125 0.4109
-1.500 0.0796 0.00771 0.00171 -0.0478 0.7053 0.4611
-1.250 0.1048 0.00753 0.00171 -0.0472 0.6981 0.5175
-1.000 0.1294 0.00736 0.00171 -0.0465 0.6919 0.5720
-0.750 0.1559 0.00730 0.00169 -0.0461 0.6866 0.5970
-0.500 0.1828 0.00725 0.00167 -0.0458 0.6805 0.6133
-0.250 0.2094 0.00723 0.00165 -0.0454 0.6740 0.6295
0.000 0.2362 0.00720 0.00165 -0.0451 0.6663 0.6450
0.250 0.2626 0.00718 0.00164 -0.0447 0.6590 0.6622
0.750 0.3149 0.00709 0.00167 -0.0437 0.6444 0.7068
1.000 0.3400 0.00705 0.00168 -0.0430 0.6320 0.7360
1.250 0.3644 0.00700 0.00171 -0.0421 0.6172 0.7704
1.500 0.3891 0.00695 0.00176 -0.0412 0.6056 0.8092
2.000 0.4433 0.00695 0.00190 -0.0405 0.5800 0.8863
2.250 0.4763 0.00705 0.00199 -0.0415 0.5620 0.9157
2.500 0.5132 0.00718 0.00208 -0.0434 0.5415 0.9362
2.750 0.5490 0.00735 0.00217 -0.0451 0.5185 0.9504
3.000 0.5825 0.00757 0.00228 -0.0464 0.4877 0.9620
3.250 0.6144 0.00792 0.00242 -0.0475 0.4403 0.9713
3.500 0.6449 0.00838 0.00264 -0.0483 0.3894 0.9790
3.750 0.6730 0.00895 0.00291 -0.0488 0.3248 0.9867
4.000 0.7033 0.00944 0.00318 -0.0497 0.2821 0.9932
4.250 0.7351 0.00989 0.00345 -0.0510 0.2422 0.9985
4.500 0.7593 0.01031 0.00370 -0.0506 0.2097 1.0000
4.750 0.7783 0.01065 0.00393 -0.0490 0.1884 1.0000
5.000 0.7976 0.01097 0.00417 -0.0474 0.1689 1.0000
5.250 0.8171 0.01130 0.00441 -0.0459 0.1522 1.0000
5.500 0.8368 0.01161 0.00466 -0.0444 0.1385 1.0000
5.750 0.8567 0.01192 0.00491 -0.0430 0.1264 1.0000
6.000 0.8763 0.01225 0.00518 -0.0415 0.1147 1.0000
6.250 0.8960 0.01257 0.00546 -0.0401 0.1054 1.0000
6.500 0.9161 0.01287 0.00574 -0.0387 0.0983 1.0000
6.750 0.9353 0.01322 0.00605 -0.0372 0.0911 1.0000
7.000 0.9554 0.01351 0.00634 -0.0358 0.0854 1.0000
7.250 0.9745 0.01387 0.00667 -0.0343 0.0797 1.0000
7.500 0.9942 0.01418 0.00699 -0.0329 0.0760 1.0000
7.750 1.0136 0.01451 0.00734 -0.0315 0.0721 1.0000
8.000 1.0317 0.01491 0.00772 -0.0298 0.0679 1.0000
8.250 1.0506 0.01525 0.00808 -0.0284 0.0651 1.0000
8.500 1.0690 0.01561 0.00846 -0.0268 0.0621 1.0000
8.750 1.0859 0.01602 0.00887 -0.0251 0.0592 1.0000
9.000 1.1003 0.01647 0.00932 -0.0228 0.0566 1.0000
9.250 1.1162 0.01683 0.00973 -0.0209 0.0549 1.0000
9.500 1.1316 0.01724 0.01018 -0.0189 0.0526 1.0000
9.750 1.1463 0.01771 0.01067 -0.0169 0.0505 1.0000
10.000 1.1599 0.01827 0.01123 -0.0149 0.0484 1.0000
10.250 1.1748 0.01878 0.01179 -0.0131 0.0469 1.0000
10.500 1.1900 0.01930 0.01237 -0.0114 0.0456 1.0000
10.750 1.2046 0.01987 0.01299 -0.0097 0.0441 1.0000
11.000 1.2184 0.02051 0.01366 -0.0081 0.0425 1.0000
11.250 1.2313 0.02123 0.01441 -0.0064 0.0410 1.0000
11.500 1.2431 0.02205 0.01526 -0.0047 0.0397 1.0000
11.750 1.2574 0.02273 0.01602 -0.0033 0.0385 1.0000
12.000 1.2707 0.02350 0.01686 -0.0019 0.0374 1.0000
12.250 1.2832 0.02434 0.01776 -0.0005 0.0363 1.0000
12.500 1.2947 0.02528 0.01874 0.0008 0.0351 1.0000
12.750 1.3051 0.02634 0.01984 0.0022 0.0341 1.0000
13.000 1.3152 0.02745 0.02100 0.0034 0.0329 1.0000
13.250 1.3261 0.02853 0.02217 0.0046 0.0322 1.0000
13.500 1.3365 0.02967 0.02340 0.0057 0.0315 1.0000
13.750 1.3467 0.03086 0.02466 0.0066 0.0304 1.0000
14.000 1.3561 0.03214 0.02600 0.0076 0.0294 1.0000
14.250 1.3632 0.03366 0.02759 0.0085 0.0288 1.0000
14.500 1.3682 0.03540 0.02937 0.0094 0.0279 1.0000
14.750 1.3755 0.03698 0.03105 0.0101 0.0272 1.0000
15.000 1.3829 0.03858 0.03276 0.0107 0.0264 1.0000
15.250 1.3881 0.04043 0.03471 0.0113 0.0259 1.0000
15.500 1.3937 0.04229 0.03666 0.0117 0.0251 1.0000
15.750 1.3983 0.04430 0.03873 0.0120 0.0243 1.0000
16.000 1.4007 0.04660 0.04110 0.0122 0.0237 1.0000
16.250 1.4001 0.04931 0.04388 0.0122 0.0229 1.0000
16.500 1.4016 0.05186 0.04655 0.0122 0.0225 1.0000
16.750 1.4025 0.05457 0.04939 0.0119 0.0221 1.0000
17.000 1.4033 0.05738 0.05231 0.0115 0.0215 1.0000
17.250 1.4018 0.06054 0.05558 0.0110 0.0210 1.0000
17.500 1.3997 0.06388 0.05902 0.0102 0.0203 1.0000
17.750 1.3955 0.06762 0.06287 0.0091 0.0199 1.0000
18.000 1.3895 0.07175 0.06710 0.0078 0.0196 1.0000
18.250 1.3808 0.07637 0.07182 0.0061 0.0192 1.0000
18.500 1.3696 0.08157 0.07713 0.0041 0.0189 1.0000
18.750 1.3581 0.08697 0.08266 0.0018 0.0186 1.0000
19.000 1.3458 0.09263 0.08847 -0.0008 0.0184 1.0000
19.250 1.3340 0.09835 0.09433 -0.0034 0.0180 1.0000
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