LNV109A (lnv109a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LNV109A (lnv109a-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.57 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lnv109a-il-1000000-n5.txt Download as CSV file: xf-lnv109a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LNV109A
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3364 0.11718 0.11336 0.0140 0.4235 0.0197
-10.000 -0.3265 0.11467 0.11085 0.0127 0.4230 0.0198
-8.000 -0.5068 0.02265 0.01762 -0.0570 0.4232 0.0279
-7.750 -0.4836 0.02011 0.01473 -0.0575 0.4226 0.0282
-7.500 -0.4578 0.01883 0.01323 -0.0576 0.4218 0.0284
-7.250 -0.4310 0.01793 0.01217 -0.0574 0.4209 0.0286
-7.000 -0.4036 0.01724 0.01135 -0.0572 0.4199 0.0288
-6.750 -0.3767 0.01638 0.01036 -0.0571 0.4190 0.0290
-6.500 -0.3489 0.01585 0.00975 -0.0569 0.4182 0.0292
-6.250 -0.3209 0.01543 0.00927 -0.0566 0.4174 0.0294
-6.000 -0.2927 0.01507 0.00885 -0.0563 0.4165 0.0296
-5.750 -0.2643 0.01473 0.00846 -0.0561 0.4157 0.0298
-5.500 -0.2359 0.01441 0.00807 -0.0558 0.4148 0.0300
-5.250 -0.2075 0.01409 0.00769 -0.0556 0.4139 0.0302
-5.000 -0.1790 0.01377 0.00731 -0.0553 0.4129 0.0304
-4.750 -0.1505 0.01346 0.00692 -0.0550 0.4117 0.0307
-4.500 -0.1219 0.01316 0.00656 -0.0548 0.4103 0.0310
-4.250 -0.0934 0.01289 0.00621 -0.0545 0.4090 0.0312
-4.000 -0.0647 0.01259 0.00586 -0.0543 0.4086 0.0315
-3.750 -0.0359 0.01232 0.00553 -0.0540 0.4081 0.0318
-3.500 -0.0071 0.01206 0.00522 -0.0538 0.4076 0.0320
-3.250 0.0219 0.01186 0.00497 -0.0535 0.4070 0.0323
-3.000 0.0507 0.01160 0.00468 -0.0533 0.4063 0.0326
-2.750 0.0796 0.01135 0.00442 -0.0530 0.4055 0.0329
-2.500 0.1085 0.01117 0.00423 -0.0528 0.4045 0.0332
-2.250 0.1375 0.01101 0.00406 -0.0526 0.4036 0.0335
-2.000 0.1666 0.01087 0.00390 -0.0524 0.4027 0.0338
-1.750 0.1956 0.01072 0.00375 -0.0521 0.4018 0.0342
-1.500 0.2247 0.01059 0.00359 -0.0519 0.4009 0.0346
-1.250 0.2538 0.01045 0.00344 -0.0517 0.3999 0.0350
-1.000 0.2828 0.01032 0.00329 -0.0515 0.3988 0.0354
-0.750 0.3119 0.01021 0.00315 -0.0513 0.3976 0.0358
-0.500 0.3410 0.01011 0.00304 -0.0511 0.3966 0.0361
-0.250 0.3700 0.00999 0.00291 -0.0509 0.3955 0.0367
0.000 0.3990 0.00992 0.00284 -0.0507 0.3944 0.0373
0.250 0.4280 0.00987 0.00279 -0.0505 0.3929 0.0378
0.500 0.4571 0.00980 0.00273 -0.0503 0.3921 0.0383
0.750 0.4863 0.00973 0.00267 -0.0502 0.3913 0.0389
1.000 0.5154 0.00966 0.00262 -0.0500 0.3904 0.0396
1.250 0.5445 0.00961 0.00257 -0.0498 0.3895 0.0402
1.500 0.5736 0.00954 0.00252 -0.0497 0.3885 0.0409
1.750 0.6027 0.00949 0.00250 -0.0495 0.3874 0.0418
2.000 0.6318 0.00945 0.00248 -0.0494 0.3861 0.0428
2.250 0.6609 0.00942 0.00246 -0.0493 0.3847 0.0441
2.500 0.6900 0.00939 0.00245 -0.0491 0.3833 0.0453
2.750 0.7190 0.00937 0.00244 -0.0490 0.3821 0.0469
3.000 0.7480 0.00936 0.00244 -0.0489 0.3807 0.0486
3.250 0.7769 0.00936 0.00245 -0.0488 0.3792 0.0505
3.500 0.8058 0.00937 0.00248 -0.0487 0.3775 0.0531
3.750 0.8348 0.00937 0.00252 -0.0486 0.3764 0.0564
4.000 0.8637 0.00937 0.00257 -0.0485 0.3753 0.0615
4.250 0.8926 0.00937 0.00262 -0.0484 0.3739 0.0696
4.500 0.9215 0.00936 0.00268 -0.0483 0.3722 0.0834
4.750 0.9503 0.00934 0.00274 -0.0482 0.3704 0.1123
5.000 0.9789 0.00927 0.00283 -0.0481 0.3687 0.1789
5.250 1.0071 0.00912 0.00294 -0.0481 0.3668 0.3100
5.750 1.0676 0.00800 0.00321 -0.0490 0.3627 1.0000
6.000 1.0963 0.00808 0.00330 -0.0490 0.3612 1.0000
6.250 1.1249 0.00817 0.00340 -0.0489 0.3593 1.0000
6.500 1.1534 0.00826 0.00350 -0.0488 0.3571 1.0000
6.750 1.1819 0.00837 0.00359 -0.0487 0.3547 1.0000
7.000 1.2102 0.00848 0.00369 -0.0486 0.3522 1.0000
7.250 1.2384 0.00861 0.00381 -0.0486 0.3496 1.0000
7.500 1.2667 0.00873 0.00394 -0.0485 0.3474 1.0000
7.750 1.2949 0.00885 0.00407 -0.0485 0.3452 1.0000
8.000 1.3231 0.00897 0.00421 -0.0484 0.3425 1.0000
8.250 1.3511 0.00911 0.00435 -0.0484 0.3394 1.0000
8.500 1.3789 0.00927 0.00451 -0.0483 0.3362 1.0000
8.750 1.4067 0.00944 0.00468 -0.0482 0.3331 1.0000
9.000 1.4344 0.00959 0.00485 -0.0482 0.3273 1.0000
9.250 1.4612 0.00988 0.00508 -0.0481 0.3155 1.0000
9.500 1.4872 0.01028 0.00541 -0.0481 0.2997 1.0000
9.750 1.5131 0.01068 0.00576 -0.0480 0.2876 1.0000
10.000 1.5387 0.01112 0.00616 -0.0479 0.2762 1.0000
10.250 1.5637 0.01162 0.00661 -0.0478 0.2641 1.0000
10.500 1.5882 0.01217 0.00711 -0.0476 0.2511 1.0000
10.750 1.6116 0.01283 0.00772 -0.0475 0.2369 1.0000
11.000 1.6337 0.01361 0.00844 -0.0473 0.2209 1.0000
11.250 1.6542 0.01454 0.00929 -0.0470 0.2034 1.0000
11.500 1.6727 0.01562 0.01029 -0.0466 0.1862 1.0000
11.750 1.6881 0.01693 0.01153 -0.0462 0.1691 1.0000
12.000 1.6996 0.01850 0.01304 -0.0456 0.1519 1.0000
12.250 1.7017 0.02084 0.01534 -0.0451 0.1356 1.0000
12.500 1.6765 0.02730 0.02200 -0.0482 0.1314 1.0000
12.750 1.6406 0.03381 0.02863 -0.0491 0.1282 1.0000
13.000 1.6137 0.03921 0.03411 -0.0497 0.1251 1.0000
13.250 1.5895 0.04430 0.03925 -0.0503 0.1215 1.0000
13.500 1.5676 0.04911 0.04410 -0.0507 0.1155 1.0000
13.750 1.5512 0.05342 0.04842 -0.0511 0.1098 1.0000
14.000 1.5364 0.05780 0.05281 -0.0516 0.1029 1.0000
14.250 1.5299 0.06130 0.05631 -0.0519 0.0975 1.0000
14.750 1.5156 0.06862 0.06363 -0.0526 0.0863 1.0000
15.000 1.5113 0.07196 0.06696 -0.0528 0.0813 1.0000
15.250 1.5063 0.07550 0.07052 -0.0533 0.0766 1.0000
15.500 1.5029 0.07884 0.07387 -0.0536 0.0723 1.0000
15.750 1.5007 0.08207 0.07709 -0.0540 0.0679 1.0000
16.000 1.4970 0.08559 0.08063 -0.0545 0.0641 1.0000
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Polar data table (+)
Polar graphs
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