LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.48 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lds2-il-1000000.txt Download as CSV file: xf-lds2-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3483 0.11868 0.11700 -0.0308 1.0000 0.0166
-12.500 -0.8106 0.04351 0.04099 -0.0707 1.0000 0.0118
-12.250 -0.8563 0.03676 0.03386 -0.0719 1.0000 0.0117
-12.000 -0.8362 0.03723 0.03443 -0.0711 1.0000 0.0119
-11.750 -0.8748 0.03343 0.03032 -0.0655 1.0000 0.0118
-11.500 -0.8795 0.03190 0.02867 -0.0619 1.0000 0.0119
-11.250 -0.8866 0.02973 0.02630 -0.0580 1.0000 0.0119
-11.000 -0.8847 0.02846 0.02492 -0.0547 1.0000 0.0120
-10.750 -0.8814 0.02752 0.02389 -0.0513 1.0000 0.0121
-10.500 -0.8553 0.02566 0.02184 -0.0529 0.9974 0.0123
-10.250 -0.8269 0.02429 0.02033 -0.0544 0.9942 0.0126
-10.000 -0.8023 0.02249 0.01832 -0.0552 0.9896 0.0127
-9.750 -0.7734 0.02119 0.01686 -0.0565 0.9860 0.0132
-9.500 -0.7458 0.01992 0.01542 -0.0573 0.9811 0.0135
-9.250 -0.7160 0.01885 0.01420 -0.0584 0.9763 0.0138
-9.000 -0.6814 0.01837 0.01361 -0.0602 0.9728 0.0141
-8.750 -0.6552 0.01630 0.01134 -0.0609 0.9646 0.0146
-8.500 -0.6233 0.01549 0.01048 -0.0623 0.9571 0.0150
-8.250 -0.5919 0.01486 0.00979 -0.0634 0.9475 0.0154
-8.000 -0.5642 0.01439 0.00924 -0.0636 0.9350 0.0158
-7.750 -0.5392 0.01382 0.00858 -0.0632 0.9220 0.0162
-7.500 -0.5148 0.01340 0.00806 -0.0625 0.9097 0.0167
-7.250 -0.4909 0.01298 0.00754 -0.0618 0.8984 0.0171
-7.000 -0.4665 0.01270 0.00717 -0.0611 0.8875 0.0175
-6.750 -0.4464 0.01185 0.00623 -0.0597 0.8769 0.0181
-6.250 -0.3981 0.01122 0.00552 -0.0583 0.8576 0.0194
-6.000 -0.3733 0.01097 0.00520 -0.0577 0.8491 0.0203
-5.750 -0.3481 0.01071 0.00490 -0.0571 0.8404 0.0210
-5.500 -0.3227 0.01051 0.00463 -0.0565 0.8324 0.0214
-5.250 -0.3002 0.00994 0.00401 -0.0555 0.8238 0.0227
-5.000 -0.2749 0.00972 0.00375 -0.0550 0.8161 0.0236
-4.750 -0.2489 0.00952 0.00351 -0.0545 0.8080 0.0249
-4.500 -0.2226 0.00940 0.00334 -0.0541 0.8009 0.0260
-4.250 -0.1978 0.00903 0.00295 -0.0535 0.7934 0.0281
-4.000 -0.1717 0.00888 0.00275 -0.0531 0.7863 0.0300
-3.750 -0.1454 0.00867 0.00252 -0.0527 0.7792 0.0324
-3.500 -0.1193 0.00849 0.00232 -0.0522 0.7719 0.0363
-3.250 -0.0930 0.00831 0.00214 -0.0519 0.7646 0.0420
-3.000 -0.0668 0.00813 0.00197 -0.0514 0.7570 0.0522
-2.750 -0.0415 0.00784 0.00180 -0.0509 0.7500 0.0866
-2.500 -0.0185 0.00727 0.00159 -0.0502 0.7427 0.1907
-2.250 0.0030 0.00662 0.00141 -0.0492 0.7358 0.3321
-2.000 0.0275 0.00628 0.00134 -0.0486 0.7288 0.4157
-1.750 0.0533 0.00614 0.00130 -0.0481 0.7224 0.4623
-1.500 0.0801 0.00602 0.00127 -0.0478 0.7161 0.4995
-1.250 0.1067 0.00595 0.00125 -0.0475 0.7095 0.5274
-1.000 0.1335 0.00590 0.00123 -0.0472 0.7027 0.5516
-0.750 0.1595 0.00578 0.00123 -0.0467 0.6954 0.5909
-0.500 0.1850 0.00569 0.00122 -0.0461 0.6887 0.6312
-0.250 0.2120 0.00562 0.00122 -0.0458 0.6823 0.6529
0.000 0.2384 0.00558 0.00121 -0.0454 0.6756 0.6745
0.250 0.2647 0.00552 0.00121 -0.0450 0.6665 0.7010
0.500 0.2900 0.00547 0.00121 -0.0443 0.6557 0.7315
0.750 0.3155 0.00540 0.00122 -0.0437 0.6461 0.7645
1.000 0.3405 0.00533 0.00125 -0.0429 0.6386 0.8018
1.250 0.3653 0.00525 0.00129 -0.0421 0.6295 0.8448
1.500 0.3912 0.00520 0.00135 -0.0414 0.6188 0.8867
1.750 0.4207 0.00523 0.00141 -0.0416 0.6079 0.9225
2.000 0.4553 0.00531 0.00149 -0.0429 0.5961 0.9465
2.250 0.4917 0.00540 0.00156 -0.0447 0.5837 0.9606
2.500 0.5291 0.00551 0.00163 -0.0467 0.5699 0.9686
2.750 0.5638 0.00564 0.00171 -0.0482 0.5535 0.9751
3.000 0.5992 0.00580 0.00179 -0.0498 0.5331 0.9798
3.250 0.6323 0.00599 0.00189 -0.0510 0.5080 0.9851
3.500 0.6676 0.00627 0.00200 -0.0528 0.4669 0.9883
3.750 0.6997 0.00670 0.00218 -0.0540 0.4109 0.9925
4.000 0.7323 0.00722 0.00241 -0.0554 0.3454 0.9960
4.250 0.7655 0.00776 0.00267 -0.0570 0.2878 0.9989
4.500 0.7915 0.00817 0.00289 -0.0570 0.2474 1.0000
4.750 0.8097 0.00852 0.00309 -0.0552 0.2168 1.0000
5.000 0.8280 0.00888 0.00331 -0.0535 0.1901 1.0000
5.250 0.8471 0.00919 0.00352 -0.0518 0.1684 1.0000
5.500 0.8664 0.00949 0.00373 -0.0502 0.1512 1.0000
5.750 0.8861 0.00979 0.00396 -0.0487 0.1358 1.0000
6.000 0.9057 0.01009 0.00419 -0.0472 0.1219 1.0000
6.250 0.9257 0.01038 0.00442 -0.0457 0.1103 1.0000
6.500 0.9458 0.01067 0.00467 -0.0443 0.1012 1.0000
6.750 0.9656 0.01098 0.00492 -0.0428 0.0929 1.0000
7.000 0.9865 0.01123 0.00517 -0.0415 0.0871 1.0000
7.250 1.0061 0.01156 0.00545 -0.0400 0.0806 1.0000
7.500 1.0269 0.01183 0.00573 -0.0387 0.0762 1.0000
7.750 1.0469 0.01212 0.00601 -0.0373 0.0721 1.0000
8.000 1.0653 0.01251 0.00637 -0.0357 0.0670 1.0000
8.250 1.0864 0.01274 0.00662 -0.0345 0.0648 1.0000
8.500 1.1059 0.01305 0.00693 -0.0331 0.0617 1.0000
8.750 1.1235 0.01346 0.00732 -0.0313 0.0580 1.0000
9.000 1.1426 0.01378 0.00767 -0.0299 0.0559 1.0000
9.250 1.1620 0.01407 0.00799 -0.0285 0.0540 1.0000
9.500 1.1797 0.01443 0.00835 -0.0268 0.0519 1.0000
9.750 1.1938 0.01485 0.00877 -0.0244 0.0497 1.0000
10.000 1.2059 0.01534 0.00929 -0.0218 0.0475 1.0000
10.250 1.2229 0.01564 0.00964 -0.0200 0.0465 1.0000
10.500 1.2394 0.01600 0.01003 -0.0182 0.0451 1.0000
10.750 1.2547 0.01644 0.01048 -0.0164 0.0436 1.0000
11.000 1.2685 0.01699 0.01103 -0.0144 0.0418 1.0000
11.250 1.2784 0.01776 0.01185 -0.0120 0.0399 1.0000
11.500 1.2960 0.01815 0.01229 -0.0107 0.0391 1.0000
11.750 1.3116 0.01867 0.01285 -0.0092 0.0382 1.0000
12.000 1.3269 0.01922 0.01344 -0.0078 0.0370 1.0000
12.250 1.3411 0.01987 0.01411 -0.0063 0.0358 1.0000
12.500 1.3519 0.02075 0.01500 -0.0045 0.0342 1.0000
12.750 1.3611 0.02177 0.01609 -0.0027 0.0331 1.0000
13.000 1.3764 0.02243 0.01680 -0.0016 0.0325 1.0000
13.250 1.3908 0.02316 0.01760 -0.0005 0.0316 1.0000
13.500 1.4041 0.02398 0.01846 0.0006 0.0308 1.0000
13.750 1.4160 0.02495 0.01946 0.0018 0.0297 1.0000
14.000 1.4255 0.02612 0.02065 0.0030 0.0286 1.0000
14.250 1.4315 0.02760 0.02220 0.0043 0.0275 1.0000
14.500 1.4442 0.02859 0.02326 0.0052 0.0270 1.0000
14.750 1.4559 0.02969 0.02442 0.0060 0.0263 1.0000
15.000 1.4674 0.03082 0.02560 0.0067 0.0254 1.0000
15.250 1.4764 0.03218 0.02700 0.0075 0.0246 1.0000
15.500 1.4819 0.03389 0.02877 0.0083 0.0240 1.0000
15.750 1.4818 0.03614 0.03108 0.0092 0.0230 1.0000
16.000 1.4888 0.03780 0.03283 0.0097 0.0226 1.0000
16.250 1.4971 0.03938 0.03449 0.0101 0.0221 1.0000
16.500 1.5039 0.04112 0.03630 0.0105 0.0215 1.0000
16.750 1.5085 0.04313 0.03840 0.0108 0.0210 1.0000
17.000 1.5119 0.04533 0.04066 0.0109 0.0205 1.0000
17.250 1.5129 0.04785 0.04324 0.0110 0.0199 1.0000
17.500 1.5101 0.05087 0.04633 0.0109 0.0194 1.0000
17.750 1.5027 0.05456 0.05011 0.0105 0.0189 1.0000
18.000 1.5001 0.05777 0.05343 0.0100 0.0186 1.0000
18.250 1.5006 0.06067 0.05643 0.0095 0.0183 1.0000
18.500 1.5012 0.06360 0.05946 0.0088 0.0178 1.0000
18.750 1.4939 0.06767 0.06364 0.0078 0.0176 1.0000
19.000 1.4884 0.07161 0.06768 0.0066 0.0173 1.0000
19.250 1.4799 0.07605 0.07222 0.0052 0.0170 1.0000
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