LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 500,000 Max Cl/Cd: 97.73 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lds2-il-500000.txt Download as CSV file: xf-lds2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4725 0.10189 0.09944 -0.0373 1.0000 0.0262
-11.250 -0.4701 0.09871 0.09626 -0.0379 1.0000 0.0264
-11.000 -0.4686 0.09528 0.09285 -0.0389 1.0000 0.0266
-10.750 -0.4633 0.09306 0.09065 -0.0391 1.0000 0.0270
-10.500 -0.4632 0.08932 0.08693 -0.0405 1.0000 0.0273
-10.250 -0.4649 0.08526 0.08289 -0.0423 1.0000 0.0277
-10.000 -0.4090 0.06251 0.06030 -0.0541 1.0000 0.0309
-9.750 -0.4295 0.05546 0.05323 -0.0578 1.0000 0.0306
-9.500 -0.4498 0.05015 0.04791 -0.0605 1.0000 0.0300
-9.250 -0.4781 0.04570 0.04342 -0.0621 1.0000 0.0293
-9.000 -0.5143 0.04325 0.04095 -0.0586 1.0000 0.0292
-8.750 -0.5279 0.03732 0.03475 -0.0612 0.9906 0.0299
-8.500 -0.5335 0.03167 0.02828 -0.0636 0.9784 0.0314
-8.250 -0.6015 0.02757 0.02267 -0.0588 0.9755 0.0213
-8.000 -0.5752 0.02484 0.01954 -0.0598 0.9704 0.0215
-7.750 -0.5487 0.02177 0.01616 -0.0606 0.9646 0.0216
-7.500 -0.5166 0.01981 0.01409 -0.0623 0.9608 0.0223
-7.250 -0.4885 0.01868 0.01285 -0.0627 0.9520 0.0228
-7.000 -0.4555 0.01771 0.01180 -0.0641 0.9465 0.0236
-6.750 -0.4287 0.01700 0.01098 -0.0640 0.9361 0.0246
-6.500 -0.4006 0.01627 0.01010 -0.0640 0.9270 0.0255
-6.250 -0.3739 0.01573 0.00941 -0.0637 0.9172 0.0260
-6.000 -0.3519 0.01433 0.00798 -0.0627 0.9070 0.0270
-5.750 -0.3270 0.01377 0.00738 -0.0622 0.8980 0.0280
-5.500 -0.3035 0.01329 0.00685 -0.0613 0.8877 0.0291
-5.250 -0.2788 0.01292 0.00641 -0.0605 0.8788 0.0305
-5.000 -0.2548 0.01249 0.00590 -0.0597 0.8699 0.0317
-4.750 -0.2329 0.01184 0.00523 -0.0586 0.8613 0.0334
-4.500 -0.2084 0.01150 0.00485 -0.0578 0.8530 0.0354
-4.250 -0.1836 0.01121 0.00450 -0.0571 0.8447 0.0373
-4.000 -0.1601 0.01076 0.00400 -0.0562 0.8367 0.0406
-3.750 -0.1348 0.01051 0.00372 -0.0557 0.8290 0.0445
-3.500 -0.1100 0.01017 0.00335 -0.0550 0.8215 0.0503
-3.250 -0.0847 0.00988 0.00306 -0.0544 0.8144 0.0606
-3.000 -0.0615 0.00934 0.00275 -0.0535 0.8068 0.1147
-2.750 -0.0442 0.00819 0.00242 -0.0521 0.7998 0.3362
-2.500 -0.0218 0.00775 0.00234 -0.0511 0.7921 0.4429
-2.250 0.0036 0.00760 0.00229 -0.0505 0.7858 0.4975
-2.000 0.0290 0.00748 0.00225 -0.0498 0.7781 0.5348
-1.750 0.0550 0.00740 0.00220 -0.0493 0.7709 0.5643
-1.500 0.0808 0.00731 0.00217 -0.0487 0.7632 0.5914
-1.250 0.1060 0.00720 0.00214 -0.0480 0.7564 0.6291
-1.000 0.1305 0.00707 0.00216 -0.0471 0.7503 0.6738
-0.750 0.1560 0.00697 0.00214 -0.0465 0.7437 0.7037
-0.500 0.1822 0.00691 0.00212 -0.0460 0.7380 0.7316
-0.250 0.2075 0.00681 0.00213 -0.0452 0.7308 0.7631
0.000 0.2330 0.00672 0.00212 -0.0445 0.7238 0.7982
0.250 0.2589 0.00665 0.00216 -0.0438 0.7169 0.8373
0.500 0.2869 0.00660 0.00221 -0.0435 0.7100 0.8776
0.750 0.3195 0.00664 0.00227 -0.0442 0.7030 0.9110
1.000 0.3565 0.00668 0.00229 -0.0459 0.6920 0.9342
1.250 0.3946 0.00674 0.00233 -0.0478 0.6804 0.9503
1.500 0.4320 0.00684 0.00238 -0.0497 0.6721 0.9623
1.750 0.4703 0.00692 0.00243 -0.0518 0.6609 0.9707
2.000 0.5098 0.00700 0.00247 -0.0542 0.6491 0.9770
2.250 0.5467 0.00709 0.00251 -0.0561 0.6372 0.9843
2.500 0.5879 0.00716 0.00254 -0.0590 0.6252 0.9888
2.750 0.6265 0.00724 0.00258 -0.0613 0.6112 0.9942
3.000 0.6675 0.00729 0.00260 -0.0642 0.5954 0.9987
3.250 0.6952 0.00737 0.00262 -0.0643 0.5779 1.0000
3.500 0.7165 0.00745 0.00267 -0.0630 0.5600 1.0000
3.750 0.7374 0.00757 0.00273 -0.0616 0.5385 1.0000
4.000 0.7574 0.00775 0.00282 -0.0600 0.5115 1.0000
4.250 0.7756 0.00802 0.00293 -0.0581 0.4708 1.0000
4.500 0.7914 0.00845 0.00311 -0.0558 0.4188 1.0000
4.750 0.8062 0.00899 0.00339 -0.0535 0.3616 1.0000
5.000 0.8199 0.00963 0.00372 -0.0509 0.3032 1.0000
5.250 0.8359 0.01016 0.00405 -0.0488 0.2622 1.0000
5.500 0.8526 0.01065 0.00436 -0.0468 0.2258 1.0000
5.750 0.8698 0.01113 0.00468 -0.0449 0.1960 1.0000
6.000 0.8872 0.01159 0.00501 -0.0431 0.1712 1.0000
6.250 0.9053 0.01202 0.00534 -0.0414 0.1519 1.0000
6.500 0.9234 0.01244 0.00568 -0.0397 0.1359 1.0000
6.750 0.9417 0.01285 0.00603 -0.0380 0.1227 1.0000
7.000 0.9599 0.01325 0.00639 -0.0363 0.1121 1.0000
7.250 0.9771 0.01372 0.00680 -0.0344 0.1032 1.0000
7.500 0.9961 0.01408 0.00716 -0.0329 0.0969 1.0000
7.750 1.0120 0.01461 0.00765 -0.0309 0.0904 1.0000
8.000 1.0314 0.01493 0.00801 -0.0295 0.0859 1.0000
8.250 1.0478 0.01541 0.00846 -0.0276 0.0812 1.0000
8.500 1.0630 0.01594 0.00900 -0.0255 0.0772 1.0000
8.750 1.0797 0.01630 0.00942 -0.0236 0.0741 1.0000
9.000 1.0937 0.01675 0.00988 -0.0213 0.0711 1.0000
9.250 1.1021 0.01750 0.01060 -0.0182 0.0675 1.0000
9.500 1.1180 0.01792 0.01109 -0.0163 0.0655 1.0000
9.750 1.1335 0.01839 0.01161 -0.0145 0.0632 1.0000
10.000 1.1483 0.01891 0.01216 -0.0127 0.0608 1.0000
10.250 1.1593 0.01968 0.01293 -0.0105 0.0584 1.0000
10.500 1.1681 0.02064 0.01393 -0.0081 0.0564 1.0000
10.750 1.1839 0.02119 0.01457 -0.0066 0.0551 1.0000
11.000 1.1983 0.02185 0.01529 -0.0051 0.0533 1.0000
11.250 1.2122 0.02255 0.01603 -0.0036 0.0516 1.0000
11.500 1.2238 0.02343 0.01693 -0.0020 0.0499 1.0000
11.750 1.2289 0.02486 0.01837 0.0002 0.0479 1.0000
12.000 1.2421 0.02571 0.01932 0.0015 0.0470 1.0000
12.250 1.2554 0.02656 0.02026 0.0027 0.0458 1.0000
12.500 1.2678 0.02749 0.02126 0.0038 0.0444 1.0000
12.750 1.2793 0.02850 0.02233 0.0050 0.0432 1.0000
13.000 1.2895 0.02964 0.02350 0.0061 0.0419 1.0000
13.250 1.2946 0.03128 0.02516 0.0076 0.0406 1.0000
13.500 1.3008 0.03291 0.02688 0.0089 0.0396 1.0000
13.750 1.3118 0.03406 0.02815 0.0097 0.0387 1.0000
14.000 1.3215 0.03536 0.02954 0.0105 0.0376 1.0000
14.250 1.3291 0.03689 0.03116 0.0114 0.0368 1.0000
14.500 1.3365 0.03844 0.03278 0.0120 0.0358 1.0000
14.750 1.3428 0.04013 0.03452 0.0126 0.0349 1.0000
15.000 1.3444 0.04232 0.03674 0.0133 0.0339 1.0000
15.250 1.3447 0.04473 0.03925 0.0142 0.0331 1.0000
15.500 1.3502 0.04667 0.04133 0.0144 0.0325 1.0000
15.750 1.3543 0.04880 0.04358 0.0144 0.0317 1.0000
16.000 1.3576 0.05107 0.04596 0.0144 0.0310 1.0000
16.250 1.3600 0.05353 0.04850 0.0142 0.0301 1.0000
16.500 1.3614 0.05618 0.05122 0.0139 0.0295 1.0000
16.750 1.3616 0.05903 0.05415 0.0135 0.0290 1.0000
17.000 1.3587 0.06229 0.05746 0.0130 0.0283 1.0000
17.250 1.3507 0.06623 0.06150 0.0125 0.0276 1.0000
17.500 1.3487 0.06978 0.06521 0.0112 0.0271 1.0000
17.750 1.3440 0.07374 0.06932 0.0099 0.0267 1.0000
18.000 1.3387 0.07792 0.07363 0.0083 0.0263 1.0000
18.250 1.3324 0.08240 0.07825 0.0065 0.0257 1.0000
18.500 1.3248 0.08715 0.08312 0.0044 0.0253 1.0000
18.750 1.3176 0.09199 0.08806 0.0022 0.0249 1.0000
19.000 1.3086 0.09721 0.09340 -0.0003 0.0245 1.0000
19.250 1.3014 0.10230 0.09855 -0.0030 0.0240 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LDS-2 AIRFOIL (lds2-il)