BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il) Reynolds number: 50,000 Max Cl/Cd: 20.88 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacj-il-50000.txt Download as CSV file: xf-bacj-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING AIRFOIL J
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5030 0.10229 0.09459 -0.0087 1.0000 0.3799
-8.250 -0.7270 0.07475 0.06725 -0.0352 1.0000 0.1585
-8.000 -0.7265 0.07044 0.06291 -0.0340 1.0000 0.1557
-7.750 -0.7720 0.06350 0.05521 -0.0330 1.0000 0.1428
-7.500 -0.7672 0.05932 0.05083 -0.0316 1.0000 0.1418
-7.250 -0.7609 0.05533 0.04663 -0.0303 1.0000 0.1407
-7.000 -0.7545 0.05135 0.04234 -0.0289 1.0000 0.1395
-6.750 -0.7454 0.04770 0.03830 -0.0275 1.0000 0.1387
-6.500 -0.7336 0.04439 0.03452 -0.0261 1.0000 0.1395
-6.250 -0.7202 0.04156 0.03104 -0.0246 1.0000 0.1423
-6.000 -0.7021 0.03887 0.02842 -0.0236 1.0000 0.1485
-5.750 -0.6827 0.03657 0.02579 -0.0224 1.0000 0.1531
-5.500 -0.6624 0.03453 0.02315 -0.0211 1.0000 0.1599
-5.250 -0.6412 0.03257 0.02132 -0.0201 1.0000 0.1708
-5.000 -0.6187 0.03073 0.01935 -0.0190 1.0000 0.1842
-4.750 -0.5961 0.02910 0.01773 -0.0177 1.0000 0.2040
-4.500 -0.5733 0.02752 0.01613 -0.0163 1.0000 0.2326
-4.250 -0.5528 0.02583 0.01483 -0.0145 1.0000 0.2739
-4.000 -0.5362 0.02391 0.01351 -0.0125 1.0000 0.3445
-3.750 -0.5285 0.02203 0.01328 -0.0076 1.0000 0.4930
-3.500 -0.5295 0.02364 0.01560 0.0033 1.0000 0.6785
-3.250 -0.5284 0.02522 0.01711 0.0133 1.0000 0.7490
-3.000 -0.5233 0.02605 0.01781 0.0219 1.0000 0.8009
-2.750 -0.5099 0.02637 0.01796 0.0285 1.0000 0.8481
-2.500 -0.4583 0.02691 0.01814 0.0281 1.0000 0.8990
-2.250 -0.2366 0.02847 0.01867 -0.0046 1.0000 0.9646
-2.000 -0.1070 0.02796 0.01769 -0.0255 1.0000 1.0000
-1.750 -0.0998 0.02752 0.01720 -0.0233 1.0000 1.0000
-1.500 -0.0927 0.02711 0.01676 -0.0210 1.0000 1.0000
-1.250 -0.0858 0.02673 0.01634 -0.0187 1.0000 1.0000
-1.000 -0.0791 0.02638 0.01596 -0.0163 1.0000 1.0000
-0.750 -0.0726 0.02604 0.01561 -0.0138 1.0000 1.0000
-0.500 -0.0665 0.02572 0.01528 -0.0112 1.0000 1.0000
-0.250 -0.0607 0.02540 0.01496 -0.0086 1.0000 1.0000
0.000 -0.0553 0.02510 0.01466 -0.0059 1.0000 1.0000
0.250 -0.0506 0.02480 0.01437 -0.0031 1.0000 1.0000
0.500 -0.0463 0.02449 0.01409 -0.0002 1.0000 1.0000
0.750 -0.0427 0.02419 0.01381 0.0028 1.0000 1.0000
1.000 -0.0394 0.02388 0.01352 0.0058 1.0000 1.0000
1.250 -0.0356 0.02358 0.01324 0.0088 1.0000 1.0000
1.500 -0.0302 0.02333 0.01303 0.0114 1.0000 1.0000
1.750 -0.0216 0.02320 0.01292 0.0135 1.0000 1.0000
2.000 -0.0086 0.02320 0.01295 0.0149 1.0000 1.0000
2.250 0.0075 0.02332 0.01311 0.0157 1.0000 1.0000
2.500 0.0256 0.02355 0.01338 0.0161 1.0000 1.0000
2.750 0.0450 0.02385 0.01374 0.0163 1.0000 1.0000
3.000 0.0650 0.02422 0.01419 0.0163 1.0000 1.0000
3.250 0.0855 0.02467 0.01473 0.0163 1.0000 1.0000
3.500 0.1060 0.02518 0.01536 0.0162 1.0000 1.0000
3.750 0.1264 0.02575 0.01606 0.0160 1.0000 1.0000
4.000 0.1465 0.02640 0.01686 0.0158 1.0000 1.0000
4.250 0.1660 0.02713 0.01776 0.0155 1.0000 1.0000
4.500 0.1850 0.02796 0.01879 0.0152 1.0000 1.0000
4.750 0.5829 0.02815 0.01665 -0.0275 0.1561 1.0000
5.000 0.6434 0.03081 0.01924 -0.0330 0.1441 1.0000
5.250 0.6714 0.03251 0.02128 -0.0326 0.1397 1.0000
5.500 0.6943 0.03429 0.02328 -0.0315 0.1343 1.0000
5.750 0.7176 0.03631 0.02545 -0.0307 0.1314 1.0000
6.000 0.7387 0.03876 0.02822 -0.0293 0.1310 1.0000
6.250 0.7551 0.04129 0.03124 -0.0270 0.1324 1.0000
6.500 0.7688 0.04407 0.03451 -0.0245 0.1347 1.0000
6.750 0.7810 0.04694 0.03775 -0.0221 0.1350 1.0000
7.000 0.7900 0.05020 0.04146 -0.0195 0.1377 1.0000
7.250 0.7998 0.05386 0.04540 -0.0174 0.1417 1.0000
7.500 0.7995 0.05783 0.04997 -0.0142 0.1526 1.0000
7.750 0.7947 0.06290 0.05554 -0.0116 0.1702 1.0000
8.000 0.7887 0.07108 0.06419 -0.0117 0.2155 1.0000
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Polar data table (+)
Polar graphs
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