BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 50,000 Max Cl/Cd: 28.29 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacnlf-il-50000-n5.txt Download as CSV file: xf-bacnlf-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5467 0.09858 0.09143 -0.0395 1.0014 0.0392
-9.500 -0.5520 0.09357 0.08648 -0.0418 1.0014 0.0383
-9.250 -0.5611 0.08846 0.08143 -0.0442 1.0014 0.0373
-9.000 -0.5747 0.08382 0.07684 -0.0460 1.0014 0.0365
-8.750 -0.5930 0.07989 0.07295 -0.0464 1.0014 0.0357
-8.500 -0.6127 0.07639 0.06945 -0.0455 1.0014 0.0349
-8.250 -0.6294 0.07261 0.06559 -0.0445 1.0014 0.0340
-8.000 -0.6436 0.06876 0.06154 -0.0430 1.0014 0.0329
-6.500 -0.6300 0.04902 0.03969 -0.0326 1.0014 0.0310
-6.250 -0.6171 0.04577 0.03604 -0.0312 1.0014 0.0310
-5.750 -0.5852 0.03920 0.02879 -0.0289 1.0014 0.0322
-5.500 -0.5668 0.03686 0.02626 -0.0280 1.0014 0.0351
-5.250 -0.5455 0.03473 0.02379 -0.0268 1.0014 0.0381
-5.000 -0.5217 0.03259 0.02121 -0.0254 1.0014 0.0402
-4.750 -0.4972 0.03080 0.01909 -0.0237 1.0014 0.0424
-4.500 -0.4760 0.02913 0.01742 -0.0223 1.0014 0.0493
-4.250 -0.4545 0.02786 0.01586 -0.0204 1.0014 0.0555
-4.000 -0.4353 0.02636 0.01434 -0.0191 1.0014 0.0644
-3.750 -0.4144 0.02504 0.01289 -0.0182 1.0014 0.0814
-3.500 -0.3921 0.02300 0.01126 -0.0184 1.0014 0.1345
-3.250 -0.3869 0.02083 0.01174 -0.0135 1.0014 0.6490
-3.000 -0.3886 0.02178 0.01290 -0.0036 1.0014 0.7506
-2.750 -0.3946 0.02249 0.01370 0.0079 1.0014 0.8192
-2.500 -0.3790 0.02238 0.01330 0.0114 1.0014 0.8443
-2.250 -0.3557 0.02209 0.01267 0.0119 1.0014 0.8534
-2.000 -0.3321 0.02182 0.01210 0.0122 1.0014 0.8623
-1.750 -0.3083 0.02156 0.01153 0.0122 1.0014 0.8716
-1.500 -0.2839 0.02134 0.01109 0.0123 1.0014 0.8800
-1.250 -0.2592 0.02115 0.01071 0.0122 1.0014 0.8890
-1.000 -0.2343 0.02099 0.01037 0.0120 1.0014 0.8988
-0.750 -0.2080 0.02087 0.01007 0.0116 1.0014 0.9080
-0.500 -0.1810 0.02078 0.00987 0.0109 1.0014 0.9183
-0.250 -0.1528 0.02073 0.00973 0.0100 1.0014 0.9294
0.000 -0.1230 0.02072 0.00965 0.0086 1.0014 0.9416
0.250 -0.0914 0.02075 0.00960 0.0068 1.0014 0.9550
0.500 -0.0596 0.02078 0.00961 0.0047 1.0014 0.9713
0.750 -0.0350 0.02069 0.00953 0.0038 1.0014 0.9986
1.000 -0.0149 0.02073 0.00954 0.0036 1.0014 0.9986
1.250 0.0080 0.02087 0.00966 0.0029 1.0014 0.9986
1.500 0.0324 0.02109 0.00987 0.0021 1.0014 0.9986
1.750 0.0617 0.02142 0.01022 0.0003 0.9993 0.9986
2.000 0.1005 0.02193 0.01077 -0.0033 0.9931 0.9986
2.250 0.1402 0.02249 0.01140 -0.0069 0.9866 0.9986
2.500 0.1768 0.02296 0.01200 -0.0099 0.9788 0.9986
2.750 0.2175 0.02356 0.01273 -0.0136 0.9722 0.9986
3.000 0.2539 0.02402 0.01336 -0.0164 0.9624 0.9986
3.250 0.2932 0.02449 0.01409 -0.0195 0.9514 0.9986
3.500 0.3334 0.02490 0.01477 -0.0227 0.9389 0.9986
3.750 0.3735 0.02524 0.01542 -0.0256 0.9251 0.9986
4.000 0.4206 0.02534 0.01596 -0.0293 0.9072 0.9986
4.250 0.4781 0.02379 0.01494 -0.0319 0.8564 0.9986
4.500 0.5186 0.02175 0.01334 -0.0302 0.7860 0.9986
4.750 0.5819 0.02057 0.01083 -0.0296 0.3756 0.9986
5.000 0.5868 0.02323 0.01205 -0.0266 0.1785 0.9986
5.250 0.6051 0.02510 0.01355 -0.0254 0.1265 0.9986
5.500 0.6280 0.02676 0.01516 -0.0247 0.0976 0.9986
5.750 0.6561 0.02856 0.01697 -0.0248 0.0754 0.9986
6.000 0.6900 0.03063 0.01922 -0.0253 0.0583 0.9986
6.250 0.7234 0.03307 0.02188 -0.0259 0.0484 0.9986
6.500 0.7509 0.03523 0.02427 -0.0259 0.0412 0.9986
6.750 0.7786 0.03849 0.02782 -0.0257 0.0387 0.9986
7.000 0.8019 0.04159 0.03156 -0.0245 0.0365 0.9986
7.250 0.8197 0.04473 0.03525 -0.0228 0.0342 0.9986
7.500 0.8338 0.04783 0.03881 -0.0210 0.0322 0.9986
7.750 0.8446 0.05110 0.04250 -0.0191 0.0311 0.9986
8.000 0.8516 0.05480 0.04663 -0.0168 0.0308 0.9986
8.250 0.8548 0.05869 0.05094 -0.0144 0.0307 0.9986
8.500 0.8539 0.06272 0.05535 -0.0120 0.0308 0.9986
8.750 0.8490 0.06685 0.05980 -0.0096 0.0310 0.9986
9.000 0.8404 0.07100 0.06423 -0.0075 0.0313 0.9986
9.250 0.8274 0.07505 0.06849 -0.0055 0.0316 0.9986
9.500 0.8112 0.07922 0.07281 -0.0041 0.0320 0.9986
9.750 0.7939 0.08388 0.07758 -0.0040 0.0324 0.9986
10.000 0.7770 0.08922 0.08300 -0.0056 0.0328 0.9986
10.250 0.7625 0.09532 0.08914 -0.0089 0.0334 0.9986
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Polar data table (+)
Polar graphs
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