LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 200,000 Max Cl/Cd: 72.69 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lds2-il-200000.txt Download as CSV file: xf-lds2-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4336 0.08963 0.08596 -0.0409 1.0000 0.0621
-9.500 -0.4464 0.08388 0.08029 -0.0454 1.0000 0.0644
-9.250 -0.4732 0.07563 0.07210 -0.0538 1.0000 0.0651
-9.000 -0.5104 0.07106 0.06749 -0.0558 1.0000 0.0654
-8.750 -0.5460 0.06850 0.06485 -0.0532 1.0000 0.0657
-8.500 -0.5809 0.06719 0.06339 -0.0484 1.0000 0.0661
-8.250 -0.6065 0.06637 0.06245 -0.0429 1.0000 0.0663
-8.000 -0.6233 0.06511 0.06101 -0.0389 0.9994 0.0664
-7.750 -0.6031 0.05682 0.05300 -0.0417 0.9971 0.0685
-7.500 -0.5752 0.05372 0.04993 -0.0444 0.9929 0.0710
-7.000 -0.5339 0.04525 0.04079 -0.0508 0.9783 0.0821
-6.750 -0.5029 0.04258 0.03802 -0.0534 0.9742 0.0874
-6.500 -0.4826 0.03523 0.02894 -0.0515 0.9641 0.0553
-6.250 -0.4527 0.02841 0.02142 -0.0524 0.9611 0.0454
-6.000 -0.4262 0.02588 0.01862 -0.0524 0.9538 0.0452
-5.750 -0.3897 0.02430 0.01671 -0.0541 0.9498 0.0458
-5.500 -0.3518 0.02163 0.01399 -0.0566 0.9476 0.0480
-5.250 -0.3198 0.02039 0.01265 -0.0574 0.9415 0.0496
-5.000 -0.2847 0.01921 0.01140 -0.0587 0.9365 0.0512
-4.750 -0.2466 0.01825 0.01034 -0.0606 0.9330 0.0542
-4.500 -0.2175 0.01708 0.00920 -0.0609 0.9264 0.0579
-4.250 -0.1876 0.01628 0.00843 -0.0613 0.9198 0.0619
-4.000 -0.1544 0.01547 0.00759 -0.0622 0.9153 0.0677
-3.750 -0.1330 0.01490 0.00706 -0.0610 0.9059 0.0759
-3.500 -0.1043 0.01419 0.00635 -0.0611 0.9002 0.0908
-3.250 -0.0895 0.01288 0.00573 -0.0590 0.8905 0.2179
-3.000 -0.0747 0.01167 0.00565 -0.0566 0.8837 0.5051
-2.750 -0.0538 0.01157 0.00567 -0.0550 0.8750 0.5636
-2.500 -0.0277 0.01142 0.00559 -0.0542 0.8690 0.6065
-2.250 -0.0041 0.01134 0.00558 -0.0530 0.8614 0.6413
-2.000 0.0202 0.01123 0.00555 -0.0518 0.8544 0.6812
-1.750 0.0434 0.01112 0.00561 -0.0501 0.8486 0.7327
-1.500 0.0655 0.01106 0.00569 -0.0484 0.8407 0.7722
-1.250 0.0938 0.01094 0.00559 -0.0479 0.8353 0.8009
-1.000 0.1190 0.01091 0.00562 -0.0470 0.8270 0.8300
-0.750 0.1506 0.01085 0.00557 -0.0471 0.8207 0.8596
-0.500 0.1861 0.01089 0.00561 -0.0481 0.8144 0.8886
-0.250 0.2255 0.01097 0.00567 -0.0501 0.8079 0.9150
0.000 0.2716 0.01104 0.00567 -0.0534 0.8033 0.9342
0.250 0.3177 0.01118 0.00576 -0.0570 0.7971 0.9501
0.500 0.3651 0.01124 0.00578 -0.0609 0.7907 0.9632
0.750 0.4129 0.01125 0.00569 -0.0648 0.7844 0.9750
1.000 0.4608 0.01122 0.00565 -0.0690 0.7753 0.9863
1.250 0.5102 0.01110 0.00546 -0.0734 0.7666 0.9963
1.500 0.5408 0.01094 0.00522 -0.0740 0.7546 1.0000
1.750 0.5587 0.01088 0.00513 -0.0721 0.7421 1.0000
2.000 0.5788 0.01087 0.00507 -0.0706 0.7317 1.0000
2.250 0.6008 0.01086 0.00500 -0.0693 0.7223 1.0000
2.500 0.6207 0.01087 0.00501 -0.0677 0.7102 1.0000
2.750 0.6418 0.01088 0.00498 -0.0662 0.6982 1.0000
3.000 0.6639 0.01089 0.00494 -0.0648 0.6865 1.0000
3.250 0.6860 0.01090 0.00492 -0.0634 0.6741 1.0000
3.500 0.7070 0.01093 0.00496 -0.0619 0.6602 1.0000
3.750 0.7283 0.01097 0.00499 -0.0604 0.6453 1.0000
4.000 0.7496 0.01101 0.00502 -0.0589 0.6292 1.0000
4.250 0.7709 0.01107 0.00504 -0.0573 0.6113 1.0000
4.500 0.7913 0.01115 0.00511 -0.0557 0.5902 1.0000
4.750 0.8112 0.01126 0.00517 -0.0539 0.5654 1.0000
5.000 0.8301 0.01142 0.00527 -0.0519 0.5344 1.0000
5.250 0.8473 0.01166 0.00539 -0.0497 0.4916 1.0000
5.500 0.8602 0.01214 0.00556 -0.0467 0.4298 1.0000
5.750 0.8692 0.01290 0.00593 -0.0432 0.3596 1.0000
6.000 0.8767 0.01382 0.00646 -0.0397 0.2983 1.0000
6.250 0.8868 0.01469 0.00704 -0.0368 0.2515 1.0000
6.500 0.8987 0.01549 0.00762 -0.0341 0.2151 1.0000
6.750 0.9106 0.01630 0.00824 -0.0316 0.1895 1.0000
7.000 0.9245 0.01703 0.00888 -0.0293 0.1701 1.0000
7.250 0.9383 0.01776 0.00953 -0.0270 0.1553 1.0000
7.500 0.9518 0.01854 0.01020 -0.0248 0.1435 1.0000
7.750 0.9667 0.01922 0.01085 -0.0228 0.1337 1.0000
8.000 0.9818 0.01993 0.01158 -0.0208 0.1256 1.0000
8.250 0.9950 0.02072 0.01229 -0.0186 0.1187 1.0000
8.500 1.0103 0.02142 0.01304 -0.0167 0.1125 1.0000
8.750 1.0249 0.02214 0.01375 -0.0147 0.1071 1.0000
9.000 1.0418 0.02319 0.01476 -0.0133 0.1024 1.0000
9.250 1.0580 0.02388 0.01554 -0.0116 0.0978 1.0000
9.500 1.0741 0.02468 0.01633 -0.0101 0.0937 1.0000
9.750 1.0958 0.02594 0.01756 -0.0096 0.0897 1.0000
10.000 1.1120 0.02672 0.01849 -0.0080 0.0864 1.0000
10.250 1.1282 0.02755 0.01938 -0.0066 0.0830 1.0000
10.500 1.1483 0.02867 0.02044 -0.0059 0.0797 1.0000
10.750 1.1698 0.03007 0.02196 -0.0054 0.0770 1.0000
11.000 1.1836 0.03103 0.02310 -0.0037 0.0744 1.0000
11.250 1.1976 0.03202 0.02419 -0.0021 0.0718 1.0000
11.500 1.2134 0.03305 0.02523 -0.0010 0.0695 1.0000
11.750 1.2402 0.03537 0.02760 -0.0017 0.0668 1.0000
12.000 1.2464 0.03646 0.02892 0.0009 0.0653 1.0000
12.250 1.2539 0.03777 0.03044 0.0030 0.0635 1.0000
12.500 1.2621 0.03919 0.03203 0.0048 0.0618 1.0000
12.750 1.2700 0.04050 0.03343 0.0065 0.0601 1.0000
13.000 1.2814 0.04195 0.03492 0.0076 0.0586 1.0000
13.250 1.2957 0.04519 0.03826 0.0080 0.0567 1.0000
13.500 1.2896 0.04696 0.04030 0.0106 0.0560 1.0000
13.750 1.2819 0.04918 0.04279 0.0129 0.0551 1.0000
14.000 1.2740 0.05169 0.04557 0.0147 0.0541 1.0000
14.250 1.2655 0.05451 0.04862 0.0161 0.0533 1.0000
14.500 1.2556 0.05763 0.05195 0.0171 0.0524 1.0000
14.750 1.2456 0.06092 0.05544 0.0177 0.0518 1.0000
15.000 1.2379 0.06411 0.05877 0.0180 0.0510 1.0000
15.250 1.2274 0.06765 0.06247 0.0178 0.0503 1.0000
15.500 1.2169 0.07140 0.06635 0.0173 0.0497 1.0000
15.750 1.2031 0.07580 0.07089 0.0163 0.0492 1.0000
16.000 1.1689 0.08325 0.07863 0.0135 0.0494 1.0000
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