LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 100,000 Max Cl/Cd: 50.34 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lds2-il-100000-n5.txt Download as CSV file: xf-lds2-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4590 0.08934 0.08399 -0.0432 1.0000 0.0352
-10.000 -0.5323 0.06867 0.06319 -0.0601 1.0000 0.0313
-9.750 -0.5568 0.06428 0.05873 -0.0614 1.0000 0.0313
-9.500 -0.5773 0.06137 0.05577 -0.0595 1.0000 0.0313
-9.250 -0.5896 0.05867 0.05301 -0.0574 1.0000 0.0311
-9.000 -0.6081 0.05548 0.04965 -0.0546 1.0000 0.0312
-8.750 -0.6204 0.05266 0.04665 -0.0515 1.0000 0.0312
-8.500 -0.6308 0.05004 0.04385 -0.0480 1.0000 0.0312
-8.250 -0.6394 0.04762 0.04123 -0.0442 1.0000 0.0311
-8.000 -0.6448 0.04518 0.03852 -0.0408 0.9996 0.0312
-7.750 -0.6245 0.04114 0.03391 -0.0425 0.9913 0.0314
-7.500 -0.5996 0.03803 0.03050 -0.0441 0.9845 0.0319
-7.250 -0.5740 0.03585 0.02811 -0.0453 0.9771 0.0326
-7.000 -0.5459 0.03405 0.02609 -0.0466 0.9704 0.0342
-6.750 -0.5180 0.03191 0.02354 -0.0476 0.9636 0.0357
-6.500 -0.4893 0.02980 0.02101 -0.0483 0.9572 0.0367
-6.250 -0.4589 0.02792 0.01873 -0.0490 0.9509 0.0376
-6.000 -0.4246 0.02618 0.01689 -0.0507 0.9469 0.0390
-5.750 -0.3967 0.02515 0.01580 -0.0511 0.9392 0.0413
-5.500 -0.3636 0.02401 0.01451 -0.0523 0.9339 0.0439
-5.250 -0.3317 0.02290 0.01324 -0.0530 0.9282 0.0458
-5.000 -0.3046 0.02180 0.01221 -0.0532 0.9208 0.0480
-4.750 -0.2723 0.02097 0.01136 -0.0542 0.9157 0.0523
-4.500 -0.2475 0.02025 0.01057 -0.0537 0.9072 0.0561
-4.250 -0.2187 0.01948 0.00979 -0.0541 0.9011 0.0609
-4.000 -0.1930 0.01889 0.00915 -0.0538 0.8934 0.0682
-3.750 -0.1656 0.01830 0.00849 -0.0537 0.8864 0.0789
-3.500 -0.1396 0.01758 0.00790 -0.0535 0.8797 0.1014
-3.250 -0.1192 0.01642 0.00734 -0.0527 0.8715 0.2101
-3.000 -0.0986 0.01532 0.00719 -0.0516 0.8653 0.4301
-2.750 -0.0771 0.01509 0.00717 -0.0502 0.8569 0.5141
-2.500 -0.0511 0.01484 0.00713 -0.0493 0.8515 0.5883
-2.250 -0.0317 0.01470 0.00727 -0.0470 0.8433 0.6617
-2.000 -0.0057 0.01456 0.00725 -0.0458 0.8372 0.7121
-1.750 0.0234 0.01448 0.00713 -0.0457 0.8312 0.7354
-1.500 0.0516 0.01443 0.00707 -0.0455 0.8242 0.7583
-1.250 0.0840 0.01434 0.00694 -0.0459 0.8192 0.7833
-1.000 0.1134 0.01435 0.00695 -0.0459 0.8121 0.8102
-0.750 0.1476 0.01435 0.00693 -0.0468 0.8062 0.8381
-0.500 0.1865 0.01432 0.00686 -0.0485 0.8018 0.8654
-0.250 0.2235 0.01441 0.00693 -0.0502 0.7939 0.8911
0.000 0.2641 0.01442 0.00687 -0.0525 0.7879 0.9140
0.250 0.3052 0.01447 0.00687 -0.0550 0.7809 0.9339
0.500 0.3467 0.01450 0.00685 -0.0577 0.7740 0.9516
0.750 0.3893 0.01451 0.00679 -0.0607 0.7687 0.9672
1.000 0.4297 0.01460 0.00687 -0.0635 0.7610 0.9832
1.250 0.4738 0.01456 0.00680 -0.0669 0.7551 0.9961
1.500 0.4998 0.01465 0.00687 -0.0669 0.7460 1.0000
1.750 0.5226 0.01464 0.00679 -0.0657 0.7377 1.0000
2.000 0.5413 0.01473 0.00687 -0.0640 0.7259 1.0000
2.250 0.5619 0.01476 0.00687 -0.0624 0.7137 1.0000
2.500 0.5833 0.01475 0.00682 -0.0609 0.7003 1.0000
2.750 0.6049 0.01475 0.00677 -0.0594 0.6865 1.0000
3.000 0.6271 0.01477 0.00675 -0.0579 0.6732 1.0000
3.250 0.6480 0.01484 0.00683 -0.0564 0.6589 1.0000
3.500 0.6691 0.01491 0.00689 -0.0549 0.6435 1.0000
3.750 0.6904 0.01497 0.00693 -0.0533 0.6265 1.0000
4.000 0.7107 0.01507 0.00702 -0.0516 0.6072 1.0000
4.250 0.7308 0.01518 0.00714 -0.0499 0.5862 1.0000
4.500 0.7512 0.01529 0.00720 -0.0482 0.5627 1.0000
4.750 0.7702 0.01546 0.00734 -0.0463 0.5341 1.0000
5.000 0.7887 0.01568 0.00747 -0.0443 0.4986 1.0000
5.250 0.8055 0.01600 0.00762 -0.0420 0.4506 1.0000
5.500 0.8198 0.01652 0.00783 -0.0394 0.3969 1.0000
5.750 0.8318 0.01724 0.00822 -0.0367 0.3388 1.0000
6.000 0.8431 0.01806 0.00874 -0.0340 0.2937 1.0000
6.250 0.8561 0.01884 0.00933 -0.0316 0.2571 1.0000
6.500 0.8695 0.01961 0.00994 -0.0294 0.2266 1.0000
6.750 0.8832 0.02038 0.01056 -0.0273 0.2023 1.0000
7.000 0.8975 0.02112 0.01121 -0.0253 0.1826 1.0000
7.250 0.9116 0.02187 0.01190 -0.0232 0.1666 1.0000
7.500 0.9257 0.02262 0.01261 -0.0212 0.1535 1.0000
7.750 0.9393 0.02340 0.01334 -0.0192 0.1431 1.0000
8.000 0.9530 0.02417 0.01409 -0.0172 0.1335 1.0000
8.250 0.9664 0.02493 0.01488 -0.0152 0.1255 1.0000
8.500 0.9782 0.02576 0.01569 -0.0130 0.1188 1.0000
8.750 0.9919 0.02660 0.01656 -0.0111 0.1128 1.0000
9.000 1.0050 0.02746 0.01744 -0.0092 0.1071 1.0000
9.250 1.0176 0.02844 0.01841 -0.0074 0.1024 1.0000
9.500 1.0327 0.02935 0.01942 -0.0059 0.0975 1.0000
9.750 1.0462 0.03032 0.02043 -0.0043 0.0935 1.0000
10.000 1.0597 0.03145 0.02153 -0.0029 0.0899 1.0000
10.250 1.0751 0.03246 0.02271 -0.0016 0.0860 1.0000
10.500 1.0893 0.03355 0.02388 -0.0002 0.0827 1.0000
10.750 1.1029 0.03470 0.02506 0.0010 0.0800 1.0000
11.000 1.1176 0.03601 0.02642 0.0022 0.0773 1.0000
11.250 1.1309 0.03727 0.02788 0.0034 0.0743 1.0000
11.500 1.1433 0.03858 0.02934 0.0047 0.0716 1.0000
11.750 1.1550 0.03993 0.03075 0.0058 0.0695 1.0000
12.000 1.1677 0.04136 0.03218 0.0068 0.0675 1.0000
12.250 1.1773 0.04307 0.03411 0.0081 0.0655 1.0000
12.500 1.1839 0.04487 0.03617 0.0094 0.0633 1.0000
12.750 1.1904 0.04672 0.03822 0.0106 0.0616 1.0000
13.000 1.1958 0.04858 0.04022 0.0117 0.0600 1.0000
13.250 1.2017 0.05041 0.04213 0.0126 0.0585 1.0000
13.500 1.2096 0.05227 0.04402 0.0134 0.0572 1.0000
13.750 1.2076 0.05496 0.04695 0.0143 0.0559 1.0000
14.000 1.2007 0.05810 0.05040 0.0150 0.0548 1.0000
14.250 1.1926 0.06154 0.05412 0.0154 0.0538 1.0000
14.500 1.1822 0.06533 0.05817 0.0154 0.0529 1.0000
14.750 1.1699 0.06948 0.06255 0.0149 0.0522 1.0000
15.000 1.1556 0.07402 0.06732 0.0139 0.0514 1.0000
15.250 1.1378 0.07933 0.07285 0.0123 0.0510 1.0000
15.500 1.1160 0.08558 0.07932 0.0097 0.0506 1.0000
15.750 1.0837 0.09414 0.08813 0.0053 0.0505 1.0000
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