LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.45 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lds2-il-1000000-n5.txt Download as CSV file: xf-lds2-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9590 0.06664 0.06410 -0.0536 1.0000 0.0082
-15.500 -0.9991 0.05566 0.05290 -0.0614 1.0000 0.0082
-15.250 -1.0251 0.04792 0.04498 -0.0670 1.0000 0.0081
-15.000 -1.0357 0.04302 0.03992 -0.0703 1.0000 0.0082
-14.750 -1.0464 0.03853 0.03527 -0.0730 1.0000 0.0082
-14.500 -1.0521 0.03519 0.03178 -0.0744 1.0000 0.0083
-14.250 -1.0573 0.03242 0.02887 -0.0746 1.0000 0.0083
-14.000 -1.0590 0.03039 0.02671 -0.0738 1.0000 0.0083
-13.750 -1.0614 0.02862 0.02481 -0.0720 1.0000 0.0084
-13.500 -1.0611 0.02731 0.02339 -0.0695 1.0000 0.0084
-13.250 -1.0611 0.02624 0.02221 -0.0662 1.0000 0.0085
-13.000 -1.0583 0.02526 0.02114 -0.0629 1.0000 0.0086
-12.750 -1.0505 0.02429 0.02005 -0.0604 1.0000 0.0086
-12.500 -1.0410 0.02340 0.01907 -0.0581 1.0000 0.0087
-12.250 -1.0308 0.02255 0.01812 -0.0557 1.0000 0.0087
-12.000 -1.0178 0.02144 0.01691 -0.0540 0.9993 0.0089
-11.750 -0.9935 0.02037 0.01574 -0.0545 0.9940 0.0091
-11.500 -0.9681 0.01959 0.01490 -0.0549 0.9885 0.0093
-11.250 -0.9400 0.01884 0.01408 -0.0557 0.9836 0.0094
-11.000 -0.9111 0.01821 0.01340 -0.0566 0.9775 0.0096
-10.750 -0.8781 0.01763 0.01275 -0.0583 0.9732 0.0098
-10.500 -0.8459 0.01699 0.01205 -0.0598 0.9655 0.0101
-10.250 -0.8119 0.01634 0.01132 -0.0617 0.9572 0.0104
-10.000 -0.7791 0.01565 0.01054 -0.0633 0.9460 0.0105
-9.500 -0.7247 0.01470 0.00937 -0.0637 0.9158 0.0110
-9.250 -0.7018 0.01425 0.00882 -0.0629 0.9015 0.0111
-9.000 -0.6786 0.01390 0.00837 -0.0622 0.8889 0.0112
-8.750 -0.6571 0.01338 0.00775 -0.0611 0.8770 0.0116
-8.500 -0.6342 0.01301 0.00732 -0.0603 0.8661 0.0119
-8.250 -0.6107 0.01267 0.00692 -0.0595 0.8557 0.0122
-8.000 -0.5866 0.01240 0.00658 -0.0589 0.8466 0.0125
-7.750 -0.5626 0.01209 0.00621 -0.0582 0.8369 0.0128
-7.500 -0.5381 0.01182 0.00588 -0.0575 0.8282 0.0132
-7.250 -0.5136 0.01154 0.00553 -0.0569 0.8196 0.0135
-7.000 -0.4886 0.01128 0.00521 -0.0564 0.8118 0.0139
-6.750 -0.4636 0.01105 0.00492 -0.0558 0.8036 0.0143
-6.500 -0.4390 0.01073 0.00457 -0.0552 0.7959 0.0149
-6.250 -0.4138 0.01050 0.00430 -0.0547 0.7879 0.0155
-6.000 -0.3880 0.01029 0.00405 -0.0543 0.7811 0.0161
-5.750 -0.3623 0.01009 0.00381 -0.0538 0.7739 0.0167
-5.500 -0.3363 0.00991 0.00357 -0.0534 0.7674 0.0172
-5.250 -0.3103 0.00970 0.00333 -0.0530 0.7602 0.0178
-5.000 -0.2846 0.00951 0.00311 -0.0526 0.7532 0.0189
-4.750 -0.2581 0.00934 0.00293 -0.0522 0.7465 0.0200
-4.500 -0.2316 0.00920 0.00275 -0.0519 0.7398 0.0211
-4.250 -0.2051 0.00903 0.00256 -0.0516 0.7340 0.0223
-4.000 -0.1785 0.00888 0.00240 -0.0513 0.7278 0.0240
-3.500 -0.1250 0.00862 0.00211 -0.0507 0.7153 0.0283
-3.250 -0.0982 0.00852 0.00199 -0.0504 0.7081 0.0312
-3.000 -0.0715 0.00839 0.00186 -0.0502 0.7012 0.0359
-2.750 -0.0447 0.00827 0.00175 -0.0499 0.6940 0.0419
-2.500 -0.0180 0.00815 0.00164 -0.0496 0.6876 0.0521
-2.250 0.0084 0.00797 0.00153 -0.0493 0.6808 0.0748
-2.000 0.0340 0.00773 0.00142 -0.0489 0.6741 0.1194
-1.750 0.0590 0.00738 0.00130 -0.0484 0.6684 0.1915
-1.500 0.0828 0.00692 0.00117 -0.0478 0.6623 0.2968
-1.250 0.1077 0.00663 0.00111 -0.0472 0.6565 0.3713
-1.000 0.1337 0.00645 0.00108 -0.0469 0.6493 0.4217
-0.750 0.1586 0.00626 0.00107 -0.0463 0.6417 0.4899
-0.500 0.1846 0.00611 0.00108 -0.0459 0.6348 0.5404
-0.250 0.2117 0.00608 0.00107 -0.0456 0.6283 0.5571
0.000 0.2392 0.00608 0.00107 -0.0455 0.6219 0.5695
0.500 0.2922 0.00612 0.00107 -0.0447 0.5937 0.5982
0.750 0.3189 0.00614 0.00109 -0.0444 0.5804 0.6111
1.000 0.3459 0.00615 0.00111 -0.0442 0.5704 0.6243
1.250 0.3723 0.00618 0.00113 -0.0438 0.5569 0.6402
1.500 0.3979 0.00623 0.00117 -0.0433 0.5376 0.6592
1.750 0.4230 0.00628 0.00122 -0.0427 0.5171 0.6835
2.000 0.4476 0.00632 0.00128 -0.0420 0.4945 0.7143
2.250 0.4709 0.00641 0.00136 -0.0411 0.4628 0.7477
2.500 0.4929 0.00657 0.00148 -0.0399 0.4253 0.7837
2.750 0.5144 0.00673 0.00162 -0.0385 0.3902 0.8247
3.000 0.5349 0.00699 0.00181 -0.0370 0.3387 0.8665
3.250 0.5576 0.00730 0.00203 -0.0360 0.2934 0.9088
3.500 0.5895 0.00758 0.00224 -0.0370 0.2624 0.9388
3.750 0.6254 0.00796 0.00246 -0.0391 0.2248 0.9567
4.000 0.6618 0.00831 0.00268 -0.0412 0.1947 0.9677
4.250 0.6954 0.00862 0.00288 -0.0427 0.1730 0.9749
4.500 0.7278 0.00892 0.00308 -0.0439 0.1530 0.9812
4.750 0.7583 0.00920 0.00328 -0.0447 0.1370 0.9868
5.000 0.7890 0.00948 0.00348 -0.0455 0.1234 0.9917
5.250 0.8193 0.00977 0.00370 -0.0463 0.1104 0.9962
5.500 0.8510 0.01004 0.00391 -0.0474 0.1001 0.9991
5.750 0.8770 0.01031 0.00414 -0.0472 0.0918 1.0000
6.000 0.8983 0.01052 0.00433 -0.0460 0.0863 1.0000
6.250 0.9186 0.01079 0.00455 -0.0446 0.0795 1.0000
6.500 0.9400 0.01100 0.00476 -0.0434 0.0756 1.0000
6.750 0.9609 0.01125 0.00499 -0.0421 0.0713 1.0000
7.000 0.9815 0.01152 0.00523 -0.0408 0.0669 1.0000
7.250 1.0028 0.01174 0.00546 -0.0396 0.0642 1.0000
7.500 1.0233 0.01202 0.00573 -0.0383 0.0605 1.0000
7.750 1.0433 0.01232 0.00600 -0.0369 0.0569 1.0000
8.000 1.0642 0.01256 0.00626 -0.0357 0.0551 1.0000
8.250 1.0844 0.01283 0.00654 -0.0343 0.0526 1.0000
8.500 1.1038 0.01316 0.00685 -0.0329 0.0498 1.0000
8.750 1.1231 0.01347 0.00717 -0.0315 0.0475 1.0000
9.000 1.1429 0.01375 0.00747 -0.0301 0.0460 1.0000
9.250 1.1619 0.01406 0.00780 -0.0287 0.0442 1.0000
9.500 1.1798 0.01442 0.00815 -0.0270 0.0423 1.0000
9.750 1.1953 0.01478 0.00852 -0.0249 0.0405 1.0000
10.000 1.2109 0.01512 0.00888 -0.0229 0.0394 1.0000
10.250 1.2270 0.01545 0.00926 -0.0209 0.0383 1.0000
10.500 1.2428 0.01583 0.00966 -0.0190 0.0369 1.0000
10.750 1.2582 0.01626 0.01010 -0.0172 0.0356 1.0000
11.000 1.2729 0.01675 0.01060 -0.0153 0.0341 1.0000
11.250 1.2880 0.01724 0.01112 -0.0136 0.0330 1.0000
11.500 1.3040 0.01770 0.01162 -0.0120 0.0321 1.0000
11.750 1.3192 0.01822 0.01218 -0.0104 0.0312 1.0000
12.000 1.3339 0.01879 0.01279 -0.0089 0.0300 1.0000
12.250 1.3479 0.01944 0.01345 -0.0073 0.0290 1.0000
12.500 1.3606 0.02019 0.01422 -0.0057 0.0276 1.0000
12.750 1.3753 0.02083 0.01493 -0.0044 0.0271 1.0000
13.000 1.3892 0.02154 0.01569 -0.0031 0.0264 1.0000
13.250 1.4026 0.02232 0.01651 -0.0019 0.0255 1.0000
13.500 1.4151 0.02318 0.01741 -0.0006 0.0246 1.0000
13.750 1.4267 0.02415 0.01841 0.0006 0.0237 1.0000
14.000 1.4379 0.02517 0.01948 0.0018 0.0227 1.0000
14.250 1.4500 0.02613 0.02050 0.0029 0.0220 1.0000
14.500 1.4611 0.02721 0.02163 0.0039 0.0213 1.0000
14.750 1.4714 0.02838 0.02285 0.0048 0.0206 1.0000
15.000 1.4804 0.02968 0.02419 0.0058 0.0196 1.0000
15.250 1.4880 0.03112 0.02568 0.0067 0.0188 1.0000
15.500 1.4965 0.03254 0.02717 0.0075 0.0185 1.0000
15.750 1.5050 0.03397 0.02868 0.0082 0.0178 1.0000
16.000 1.5118 0.03557 0.03035 0.0089 0.0173 1.0000
16.250 1.5177 0.03732 0.03216 0.0095 0.0167 1.0000
16.500 1.5224 0.03921 0.03410 0.0100 0.0161 1.0000
16.750 1.5259 0.04126 0.03623 0.0104 0.0157 1.0000
17.000 1.5276 0.04357 0.03861 0.0107 0.0152 1.0000
17.250 1.5309 0.04578 0.04090 0.0109 0.0149 1.0000
17.500 1.5330 0.04818 0.04340 0.0109 0.0146 1.0000
17.750 1.5336 0.05081 0.04611 0.0108 0.0142 1.0000
18.000 1.5333 0.05361 0.04900 0.0106 0.0138 1.0000
18.250 1.5312 0.05670 0.05218 0.0102 0.0135 1.0000
18.500 1.5268 0.06016 0.05571 0.0096 0.0129 1.0000
18.750 1.5219 0.06377 0.05943 0.0088 0.0128 1.0000
19.000 1.5138 0.06792 0.06367 0.0077 0.0125 1.0000
19.250 1.5041 0.07243 0.06830 0.0063 0.0123 1.0000
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