LNV109A (lnv109a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LNV109A (lnv109a-il) Reynolds number: 500,000 Max Cl/Cd: 113.73 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lnv109a-il-500000-n5.txt Download as CSV file: xf-lnv109a-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2255 0.08968 0.08515 0.0009 0.4304 0.0272
-7.000 -0.2200 0.08682 0.08229 -0.0004 0.4298 0.0275
-6.750 -0.2155 0.08393 0.07941 -0.0017 0.4292 0.0275
-6.500 -0.2127 0.08111 0.07661 -0.0029 0.4285 0.0275
-6.250 -0.2117 0.07841 0.07392 -0.0041 0.4278 0.0277
-6.000 -0.2047 0.07522 0.07073 -0.0068 0.4270 0.0277
-5.750 -0.1958 0.07170 0.06720 -0.0102 0.4264 0.0279
-5.500 -0.1933 0.06254 0.05798 -0.0210 0.4263 0.0288
-5.250 -0.1739 0.06054 0.05597 -0.0229 0.4257 0.0290
-4.750 -0.1373 0.02668 0.02086 -0.0522 0.4255 0.0324
-4.500 -0.1109 0.02475 0.01872 -0.0529 0.4247 0.0327
-4.250 -0.0838 0.02337 0.01718 -0.0532 0.4238 0.0329
-4.000 -0.0565 0.02205 0.01568 -0.0535 0.4229 0.0333
-3.750 -0.0292 0.02055 0.01395 -0.0537 0.4219 0.0337
-3.500 -0.0017 0.01914 0.01228 -0.0537 0.4210 0.0343
-3.250 0.0260 0.01787 0.01073 -0.0537 0.4201 0.0349
-3.000 0.0542 0.01685 0.00944 -0.0536 0.4191 0.0357
-2.750 0.0826 0.01614 0.00851 -0.0534 0.4182 0.0362
-2.500 0.1110 0.01569 0.00801 -0.0533 0.4171 0.0366
-2.250 0.1396 0.01536 0.00764 -0.0531 0.4160 0.0369
-2.000 0.1683 0.01507 0.00730 -0.0529 0.4149 0.0373
-1.750 0.1970 0.01477 0.00694 -0.0527 0.4138 0.0377
-1.500 0.2257 0.01448 0.00659 -0.0525 0.4129 0.0382
-1.250 0.2545 0.01420 0.00623 -0.0522 0.4120 0.0387
-1.000 0.2832 0.01394 0.00590 -0.0520 0.4110 0.0393
-0.750 0.3120 0.01376 0.00563 -0.0518 0.4098 0.0399
-0.500 0.3407 0.01358 0.00541 -0.0516 0.4087 0.0405
-0.250 0.3695 0.01338 0.00524 -0.0514 0.4078 0.0411
0.000 0.3983 0.01322 0.00510 -0.0512 0.4068 0.0417
0.250 0.4272 0.01307 0.00497 -0.0510 0.4058 0.0424
0.500 0.4560 0.01294 0.00484 -0.0508 0.4048 0.0431
0.750 0.4849 0.01281 0.00472 -0.0507 0.4037 0.0439
1.000 0.5138 0.01270 0.00460 -0.0505 0.4024 0.0446
1.250 0.5425 0.01256 0.00449 -0.0503 0.4011 0.0455
1.500 0.5714 0.01248 0.00443 -0.0501 0.3998 0.0466
1.750 0.6002 0.01241 0.00438 -0.0500 0.3986 0.0480
2.000 0.6290 0.01236 0.00433 -0.0498 0.3976 0.0493
2.250 0.6578 0.01228 0.00427 -0.0496 0.3965 0.0506
2.500 0.6865 0.01224 0.00425 -0.0495 0.3954 0.0522
2.750 0.7153 0.01222 0.00422 -0.0493 0.3942 0.0542
3.000 0.7439 0.01223 0.00424 -0.0492 0.3928 0.0565
3.250 0.7726 0.01223 0.00429 -0.0490 0.3917 0.0599
3.500 0.8014 0.01223 0.00435 -0.0489 0.3906 0.0639
3.750 0.8301 0.01224 0.00442 -0.0488 0.3892 0.0693
4.000 0.8587 0.01224 0.00449 -0.0487 0.3877 0.0786
4.250 0.8873 0.01222 0.00456 -0.0486 0.3861 0.0995
4.500 0.9157 0.01215 0.00466 -0.0485 0.3845 0.1532
4.750 0.9436 0.01193 0.00480 -0.0484 0.3831 0.3065
5.250 1.0052 0.01073 0.00499 -0.0494 0.3802 1.0000
5.500 1.0336 0.01082 0.00504 -0.0493 0.3787 1.0000
5.750 1.0618 0.01095 0.00513 -0.0491 0.3773 1.0000
6.000 1.0901 0.01108 0.00529 -0.0490 0.3756 1.0000
6.250 1.1184 0.01121 0.00545 -0.0489 0.3737 1.0000
6.500 1.1466 0.01134 0.00559 -0.0488 0.3717 1.0000
6.750 1.1748 0.01145 0.00572 -0.0487 0.3696 1.0000
7.000 1.2029 0.01155 0.00583 -0.0486 0.3676 1.0000
7.250 1.2310 0.01166 0.00593 -0.0485 0.3657 1.0000
7.500 1.2589 0.01177 0.00602 -0.0484 0.3638 1.0000
7.750 1.2867 0.01192 0.00619 -0.0483 0.3618 1.0000
8.000 1.3145 0.01209 0.00642 -0.0482 0.3594 1.0000
8.250 1.3421 0.01225 0.00662 -0.0482 0.3568 1.0000
8.500 1.3697 0.01240 0.00679 -0.0481 0.3542 1.0000
8.750 1.3972 0.01254 0.00695 -0.0480 0.3517 1.0000
9.000 1.4245 0.01270 0.00709 -0.0479 0.3492 1.0000
9.250 1.4516 0.01290 0.00735 -0.0478 0.3465 1.0000
9.500 1.4787 0.01310 0.00762 -0.0477 0.3429 1.0000
9.750 1.5055 0.01326 0.00777 -0.0476 0.3369 1.0000
10.000 1.5319 0.01347 0.00798 -0.0475 0.3269 1.0000
10.250 1.5573 0.01377 0.00826 -0.0474 0.3156 1.0000
10.500 1.5821 0.01417 0.00862 -0.0473 0.3060 1.0000
10.750 1.6071 0.01456 0.00903 -0.0471 0.2970 1.0000
11.000 1.6309 0.01506 0.00953 -0.0469 0.2879 1.0000
11.250 1.6533 0.01568 0.01013 -0.0467 0.2775 1.0000
11.500 1.6747 0.01639 0.01083 -0.0464 0.2656 1.0000
11.750 1.6941 0.01726 0.01169 -0.0461 0.2529 1.0000
12.000 1.7099 0.01843 0.01284 -0.0457 0.2387 1.0000
12.250 1.7210 0.01995 0.01434 -0.0452 0.2245 1.0000
12.500 1.7224 0.02224 0.01665 -0.0447 0.2109 1.0000
12.750 1.6945 0.02807 0.02265 -0.0465 0.2056 1.0000
13.000 1.6586 0.03440 0.02906 -0.0473 0.1994 1.0000
13.250 1.6272 0.04003 0.03474 -0.0476 0.1938 1.0000
13.500 1.5997 0.04525 0.03999 -0.0480 0.1864 1.0000
13.750 1.5767 0.05008 0.04483 -0.0483 0.1790 1.0000
14.000 1.5562 0.05483 0.04959 -0.0488 0.1711 1.0000
14.250 1.5400 0.05942 0.05416 -0.0494 0.1613 1.0000
14.500 1.5263 0.06384 0.05856 -0.0501 0.1518 1.0000
14.750 1.5136 0.06827 0.06297 -0.0508 0.1430 1.0000
15.000 1.5031 0.07252 0.06720 -0.0515 0.1340 1.0000
15.250 1.4950 0.07656 0.07122 -0.0522 0.1252 1.0000
15.500 1.4864 0.08075 0.07540 -0.0531 0.1173 1.0000
15.750 1.4788 0.08487 0.07950 -0.0539 0.1092 1.0000
16.000 1.4723 0.08895 0.08357 -0.0548 0.1022 1.0000
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Polar data table (+)
Polar graphs
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