LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 200,000 Max Cl/Cd: 66.29 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lds2-il-200000-n5.txt Download as CSV file: xf-lds2-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4807 0.08811 0.08425 -0.0420 1.0000 0.0201
-10.500 -0.4958 0.08038 0.07657 -0.0462 1.0000 0.0198
-10.250 -0.5455 0.06344 0.05958 -0.0590 1.0000 0.0192
-10.000 -0.5909 0.05509 0.05104 -0.0638 1.0000 0.0187
-9.750 -0.6203 0.05170 0.04753 -0.0612 1.0000 0.0187
-9.500 -0.6452 0.04822 0.04388 -0.0576 1.0000 0.0187
-9.250 -0.6661 0.04473 0.04015 -0.0535 1.0000 0.0186
-9.000 -0.6711 0.04163 0.03680 -0.0513 0.9973 0.0188
-8.750 -0.6567 0.03727 0.03197 -0.0529 0.9875 0.0192
-8.500 -0.6385 0.03364 0.02787 -0.0539 0.9788 0.0197
-8.250 -0.6166 0.03043 0.02412 -0.0548 0.9716 0.0207
-8.000 -0.5931 0.02772 0.02084 -0.0552 0.9638 0.0215
-7.750 -0.5653 0.02613 0.01912 -0.0562 0.9573 0.0220
-7.500 -0.5369 0.02476 0.01759 -0.0570 0.9503 0.0226
-7.250 -0.5070 0.02341 0.01605 -0.0580 0.9441 0.0232
-7.000 -0.4786 0.02215 0.01459 -0.0585 0.9363 0.0241
-6.750 -0.4468 0.02094 0.01317 -0.0595 0.9307 0.0252
-6.500 -0.4198 0.01996 0.01204 -0.0595 0.9217 0.0263
-6.250 -0.3894 0.01909 0.01115 -0.0604 0.9152 0.0275
-6.000 -0.3635 0.01833 0.01033 -0.0602 0.9059 0.0286
-5.750 -0.3348 0.01754 0.00944 -0.0604 0.8988 0.0299
-5.500 -0.3102 0.01690 0.00870 -0.0598 0.8893 0.0311
-5.250 -0.2845 0.01623 0.00803 -0.0596 0.8818 0.0329
-5.000 -0.2604 0.01575 0.00752 -0.0589 0.8724 0.0349
-4.750 -0.2352 0.01526 0.00695 -0.0584 0.8647 0.0371
-4.500 -0.2120 0.01473 0.00638 -0.0575 0.8560 0.0393
-4.250 -0.1868 0.01434 0.00593 -0.0570 0.8487 0.0427
-4.000 -0.1627 0.01397 0.00551 -0.0562 0.8402 0.0472
-3.750 -0.1374 0.01361 0.00509 -0.0557 0.8333 0.0530
-3.500 -0.1132 0.01326 0.00475 -0.0550 0.8252 0.0623
-3.250 -0.0882 0.01286 0.00440 -0.0544 0.8187 0.0836
-3.000 -0.0669 0.01217 0.00408 -0.0534 0.8108 0.1672
-2.750 -0.0478 0.01125 0.00381 -0.0522 0.8037 0.3363
-2.500 -0.0258 0.01085 0.00375 -0.0511 0.7966 0.4363
-2.250 -0.0016 0.01065 0.00370 -0.0502 0.7899 0.4943
-2.000 0.0227 0.01048 0.00366 -0.0493 0.7839 0.5506
-1.750 0.0449 0.01028 0.00370 -0.0479 0.7765 0.6134
-1.500 0.0697 0.01014 0.00365 -0.0470 0.7707 0.6533
-1.250 0.0956 0.01006 0.00361 -0.0464 0.7641 0.6741
-1.000 0.1220 0.01000 0.00355 -0.0459 0.7576 0.6934
-0.750 0.1485 0.00994 0.00349 -0.0454 0.7510 0.7150
-0.500 0.1745 0.00986 0.00348 -0.0448 0.7430 0.7389
-0.250 0.2016 0.00981 0.00344 -0.0443 0.7367 0.7664
0.000 0.2286 0.00976 0.00349 -0.0439 0.7295 0.7979
0.250 0.2588 0.00975 0.00352 -0.0440 0.7237 0.8316
0.500 0.2924 0.00977 0.00359 -0.0449 0.7181 0.8641
0.750 0.3294 0.00981 0.00365 -0.0466 0.7112 0.8916
1.000 0.3670 0.00987 0.00367 -0.0484 0.7041 0.9143
1.250 0.4045 0.00993 0.00373 -0.0503 0.6950 0.9326
1.500 0.4412 0.00999 0.00375 -0.0520 0.6862 0.9479
1.750 0.4769 0.01004 0.00373 -0.0534 0.6730 0.9612
2.000 0.5120 0.01009 0.00372 -0.0548 0.6570 0.9730
2.250 0.5489 0.01015 0.00374 -0.0567 0.6431 0.9826
2.500 0.5863 0.01021 0.00378 -0.0588 0.6288 0.9914
2.750 0.6238 0.01028 0.00378 -0.0609 0.6112 0.9996
3.000 0.6460 0.01037 0.00382 -0.0597 0.5948 1.0000
3.250 0.6670 0.01048 0.00390 -0.0583 0.5768 1.0000
3.500 0.6879 0.01061 0.00398 -0.0569 0.5565 1.0000
3.750 0.7083 0.01078 0.00406 -0.0554 0.5326 1.0000
4.000 0.7279 0.01098 0.00417 -0.0537 0.5020 1.0000
4.250 0.7460 0.01127 0.00430 -0.0518 0.4613 1.0000
4.500 0.7611 0.01173 0.00449 -0.0494 0.4111 1.0000
4.750 0.7753 0.01229 0.00478 -0.0469 0.3565 1.0000
5.000 0.7885 0.01294 0.00515 -0.0443 0.3065 1.0000
5.250 0.8035 0.01353 0.00554 -0.0421 0.2691 1.0000
5.750 0.8354 0.01463 0.00633 -0.0381 0.2082 1.0000
6.000 0.8522 0.01514 0.00674 -0.0363 0.1855 1.0000
6.250 0.8693 0.01565 0.00716 -0.0345 0.1669 1.0000
6.500 0.8865 0.01615 0.00759 -0.0328 0.1513 1.0000
6.750 0.9038 0.01665 0.00804 -0.0311 0.1378 1.0000
7.000 0.9210 0.01715 0.00851 -0.0294 0.1268 1.0000
7.250 0.9373 0.01769 0.00900 -0.0276 0.1174 1.0000
7.500 0.9546 0.01817 0.00949 -0.0259 0.1091 1.0000
7.750 0.9702 0.01874 0.01003 -0.0240 0.1025 1.0000
8.000 0.9866 0.01924 0.01058 -0.0223 0.0964 1.0000
8.250 0.9996 0.01985 0.01116 -0.0200 0.0915 1.0000
8.500 1.0140 0.02038 0.01174 -0.0179 0.0872 1.0000
8.750 1.0278 0.02096 0.01235 -0.0158 0.0828 1.0000
9.000 1.0395 0.02167 0.01306 -0.0136 0.0793 1.0000
9.250 1.0532 0.02234 0.01378 -0.0116 0.0763 1.0000
9.500 1.0673 0.02300 0.01452 -0.0099 0.0732 1.0000
9.750 1.0802 0.02375 0.01530 -0.0081 0.0703 1.0000
10.000 1.0909 0.02466 0.01622 -0.0061 0.0676 1.0000
10.250 1.1045 0.02546 0.01710 -0.0045 0.0653 1.0000
10.500 1.1177 0.02630 0.01802 -0.0030 0.0630 1.0000
10.750 1.1305 0.02717 0.01897 -0.0015 0.0608 1.0000
11.000 1.1417 0.02816 0.01999 0.0000 0.0587 1.0000
11.250 1.1505 0.02939 0.02123 0.0016 0.0569 1.0000
11.500 1.1634 0.03037 0.02234 0.0028 0.0552 1.0000
11.750 1.1753 0.03145 0.02352 0.0041 0.0535 1.0000
12.000 1.1863 0.03257 0.02474 0.0053 0.0517 1.0000
12.250 1.1964 0.03377 0.02601 0.0064 0.0502 1.0000
12.500 1.2045 0.03516 0.02744 0.0076 0.0487 1.0000
12.750 1.2123 0.03669 0.02902 0.0087 0.0475 1.0000
13.000 1.2221 0.03809 0.03057 0.0097 0.0463 1.0000
13.250 1.2306 0.03958 0.03221 0.0106 0.0449 1.0000
13.500 1.2381 0.04117 0.03392 0.0115 0.0437 1.0000
13.750 1.2444 0.04286 0.03570 0.0122 0.0424 1.0000
14.000 1.2498 0.04467 0.03761 0.0128 0.0414 1.0000
14.250 1.2539 0.04668 0.03967 0.0134 0.0406 1.0000
14.500 1.2571 0.04887 0.04194 0.0139 0.0397 1.0000
14.750 1.2605 0.05110 0.04437 0.0143 0.0388 1.0000
15.000 1.2623 0.05354 0.04699 0.0145 0.0379 1.0000
15.250 1.2631 0.05613 0.04974 0.0146 0.0369 1.0000
15.500 1.2629 0.05889 0.05264 0.0144 0.0361 1.0000
15.750 1.2620 0.06181 0.05568 0.0140 0.0353 1.0000
16.000 1.2605 0.06491 0.05889 0.0134 0.0347 1.0000
16.250 1.2579 0.06825 0.06233 0.0126 0.0341 1.0000
16.500 1.2548 0.07173 0.06588 0.0117 0.0335 1.0000
16.750 1.2485 0.07588 0.07019 0.0104 0.0330 1.0000
17.000 1.2389 0.08076 0.07530 0.0086 0.0325 1.0000
17.250 1.2268 0.08625 0.08102 0.0061 0.0319 1.0000
17.500 1.2136 0.09214 0.08711 0.0033 0.0314 1.0000
17.750 1.1983 0.09869 0.09385 0.0000 0.0311 1.0000
18.000 1.1807 0.10594 0.10130 -0.0040 0.0307 1.0000
18.250 1.1583 0.11448 0.11004 -0.0089 0.0305 1.0000
18.500 1.1268 0.12549 0.12127 -0.0156 0.0304 1.0000
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