BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 200,000 Max Cl/Cd: 52.96 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacnlf-il-200000-n5.txt Download as CSV file: xf-bacnlf-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING HSNLF AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5409 0.09366 0.09002 -0.0389 1.0014 0.0121
-9.750 -0.5469 0.08891 0.08532 -0.0407 1.0014 0.0118
-9.500 -0.5555 0.08347 0.07992 -0.0434 1.0014 0.0115
-9.250 -0.5693 0.07753 0.07401 -0.0468 1.0014 0.0113
-9.000 -0.5885 0.07308 0.06956 -0.0479 1.0014 0.0113
-8.750 -0.6126 0.07005 0.06652 -0.0465 1.0014 0.0113
-8.500 -0.6376 0.06776 0.06420 -0.0433 1.0014 0.0113
-8.250 -0.6547 0.06467 0.06104 -0.0409 1.0014 0.0111
-8.000 -0.6680 0.06134 0.05761 -0.0385 1.0014 0.0108
-7.750 -0.6777 0.05765 0.05376 -0.0362 1.0014 0.0103
-7.250 -0.6531 0.04461 0.03978 -0.0382 0.9958 0.0081
-7.000 -0.6389 0.04046 0.03528 -0.0387 0.9930 0.0079
-6.750 -0.6202 0.03654 0.03095 -0.0391 0.9904 0.0078
-6.500 -0.5979 0.03291 0.02687 -0.0396 0.9882 0.0076
-6.250 -0.5731 0.02966 0.02316 -0.0401 0.9867 0.0074
-6.000 -0.5464 0.02683 0.01988 -0.0404 0.9855 0.0073
-5.750 -0.5229 0.02455 0.01724 -0.0397 0.9833 0.0073
-5.500 -0.4972 0.02259 0.01497 -0.0395 0.9813 0.0073
-5.250 -0.4706 0.02093 0.01307 -0.0393 0.9795 0.0074
-5.000 -0.4435 0.01952 0.01146 -0.0394 0.9779 0.0076
-4.750 -0.4153 0.01833 0.01012 -0.0399 0.9762 0.0079
-4.500 -0.3860 0.01725 0.00892 -0.0407 0.9747 0.0085
-4.250 -0.3554 0.01639 0.00796 -0.0419 0.9734 0.0100
-4.000 -0.3256 0.01571 0.00714 -0.0427 0.9717 0.0141
-3.750 -0.2999 0.01514 0.00653 -0.0427 0.9686 0.0258
-3.500 -0.2713 0.01448 0.00602 -0.0436 0.9662 0.0650
-3.250 -0.2438 0.01209 0.00535 -0.0460 0.9654 0.4446
-3.000 -0.2155 0.01184 0.00561 -0.0462 0.9634 0.6044
-2.750 -0.1858 0.01209 0.00593 -0.0463 0.9614 0.6656
-2.500 -0.1544 0.01229 0.00609 -0.0468 0.9599 0.6923
-2.250 -0.1294 0.01232 0.00604 -0.0464 0.9563 0.6996
-2.000 -0.1001 0.01231 0.00591 -0.0470 0.9534 0.7047
-1.750 -0.0691 0.01228 0.00581 -0.0479 0.9510 0.7082
-1.500 -0.0367 0.01226 0.00573 -0.0491 0.9492 0.7122
-1.250 -0.0026 0.01225 0.00565 -0.0507 0.9476 0.7166
-1.000 0.0248 0.01223 0.00560 -0.0508 0.9434 0.7203
-0.750 0.0542 0.01220 0.00556 -0.0513 0.9395 0.7239
-0.500 0.0869 0.01217 0.00551 -0.0526 0.9370 0.7279
-0.250 0.1209 0.01216 0.00548 -0.0542 0.9351 0.7323
0.000 0.1551 0.01212 0.00549 -0.0557 0.9337 0.7356
0.250 0.1766 0.01218 0.00558 -0.0546 0.9278 0.7395
0.500 0.2074 0.01218 0.00561 -0.0555 0.9246 0.7439
0.750 0.2405 0.01214 0.00564 -0.0568 0.9224 0.7479
1.000 0.2752 0.01207 0.00564 -0.0583 0.9204 0.7517
1.250 0.2988 0.01208 0.00574 -0.0575 0.9131 0.7561
1.500 0.3319 0.01196 0.00570 -0.0587 0.9091 0.7607
1.750 0.3623 0.01180 0.00565 -0.0590 0.9026 0.7648
2.000 0.3951 0.01150 0.00546 -0.0597 0.8945 0.7695
2.250 0.4239 0.01093 0.00500 -0.0590 0.8737 0.7743
2.500 0.4546 0.01032 0.00447 -0.0585 0.8408 0.7786
2.750 0.4860 0.01005 0.00426 -0.0586 0.8093 0.7839
3.000 0.5217 0.00985 0.00387 -0.0593 0.7179 0.7891
3.250 0.5376 0.01069 0.00388 -0.0563 0.5368 0.7944
3.500 0.5471 0.01193 0.00433 -0.0529 0.3629 0.8012
3.750 0.5601 0.01311 0.00486 -0.0505 0.2084 0.8078
4.250 0.5996 0.01458 0.00586 -0.0481 0.0793 0.8239
4.500 0.6214 0.01511 0.00632 -0.0471 0.0534 0.8329
4.750 0.6435 0.01559 0.00677 -0.0462 0.0336 0.8436
5.000 0.6649 0.01614 0.00739 -0.0450 0.0213 0.8559
5.250 0.6852 0.01686 0.00822 -0.0435 0.0156 0.8713
5.500 0.7052 0.01752 0.00904 -0.0419 0.0135 0.8906
5.750 0.7241 0.01846 0.01016 -0.0401 0.0123 0.9189
6.000 0.7490 0.01962 0.01151 -0.0397 0.0117 0.9986
6.250 0.7722 0.02096 0.01300 -0.0389 0.0113 0.9986
6.500 0.7963 0.02240 0.01460 -0.0384 0.0107 0.9986
6.750 0.8205 0.02354 0.01591 -0.0379 0.0095 0.9986
7.000 0.8435 0.02462 0.01713 -0.0374 0.0085 0.9986
7.500 0.8858 0.02864 0.02172 -0.0355 0.0079 0.9986
7.750 0.9022 0.03167 0.02517 -0.0338 0.0077 0.9986
8.000 0.9138 0.03521 0.02919 -0.0314 0.0076 0.9986
8.250 0.9224 0.03870 0.03317 -0.0287 0.0075 0.9986
8.500 0.9262 0.04253 0.03745 -0.0256 0.0075 0.9986
8.750 0.9251 0.04660 0.04193 -0.0223 0.0076 0.9986
9.250 0.9141 0.05454 0.05054 -0.0156 0.0077 0.9986
9.500 0.9021 0.05851 0.05477 -0.0120 0.0077 0.9986
9.750 0.8846 0.06370 0.06021 -0.0088 0.0079 0.9986
10.000 0.8607 0.07005 0.06678 -0.0070 0.0082 0.9986
10.250 0.8302 0.07843 0.07535 -0.0083 0.0085 0.9986
10.500 0.8064 0.08731 0.08433 -0.0134 0.0087 0.9986
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Polar data table (+)
Polar graphs
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