BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il) Reynolds number: 200,000 Max Cl/Cd: 31.09 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacj-il-200000.txt Download as CSV file: xf-bacj-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6199 0.09158 0.08779 -0.0405 1.0000 0.0822
-10.000 -0.6234 0.08823 0.08445 -0.0402 1.0000 0.0831
-9.750 -0.6287 0.08494 0.08119 -0.0402 1.0000 0.0845
-9.500 -0.8861 0.05284 0.04789 -0.0400 1.0000 0.0474
-9.250 -0.8799 0.05078 0.04582 -0.0382 1.0000 0.0481
-9.000 -0.8885 0.04631 0.04089 -0.0348 1.0000 0.0451
-8.750 -0.8892 0.04371 0.03789 -0.0320 1.0000 0.0457
-8.500 -0.8855 0.04000 0.03390 -0.0299 1.0000 0.0452
-8.250 -0.8785 0.03670 0.03026 -0.0278 1.0000 0.0449
-8.000 -0.8674 0.03397 0.02718 -0.0260 1.0000 0.0447
-7.750 -0.8535 0.03161 0.02447 -0.0243 1.0000 0.0449
-7.500 -0.8372 0.02961 0.02213 -0.0228 1.0000 0.0453
-7.250 -0.8191 0.02809 0.02034 -0.0214 1.0000 0.0457
-7.000 -0.8003 0.02650 0.01848 -0.0200 1.0000 0.0466
-6.750 -0.7808 0.02460 0.01652 -0.0190 1.0000 0.0479
-6.500 -0.7609 0.02368 0.01558 -0.0179 1.0000 0.0496
-6.250 -0.7406 0.02288 0.01471 -0.0168 1.0000 0.0518
-6.000 -0.7198 0.02203 0.01374 -0.0156 1.0000 0.0545
-5.750 -0.6989 0.02134 0.01293 -0.0144 1.0000 0.0558
-5.500 -0.6800 0.01997 0.01163 -0.0130 1.0000 0.0585
-5.250 -0.6599 0.01937 0.01104 -0.0119 1.0000 0.0623
-5.000 -0.6391 0.01889 0.01048 -0.0107 1.0000 0.0673
-4.750 -0.6203 0.01799 0.00968 -0.0094 1.0000 0.0732
-4.500 -0.6003 0.01741 0.00909 -0.0081 1.0000 0.0819
-4.250 -0.5800 0.01697 0.00866 -0.0070 1.0000 0.0938
-4.000 -0.5612 0.01626 0.00814 -0.0057 1.0000 0.1146
-3.750 -0.5421 0.01571 0.00778 -0.0044 1.0000 0.1493
-3.500 -0.5229 0.01524 0.00751 -0.0031 1.0000 0.1949
-3.250 -0.5048 0.01472 0.00726 -0.0018 1.0000 0.2450
-3.000 -0.4885 0.01407 0.00702 -0.0001 1.0000 0.3262
-2.750 -0.4798 0.01315 0.00715 0.0034 1.0000 0.5298
-2.500 -0.4638 0.01325 0.00758 0.0061 1.0000 0.6292
-2.250 -0.4452 0.01350 0.00787 0.0082 1.0000 0.6701
-2.000 -0.4260 0.01377 0.00811 0.0101 1.0000 0.6962
-1.750 -0.3979 0.01433 0.00868 0.0103 0.9976 0.7180
-1.500 -0.3653 0.01506 0.00943 0.0097 0.9931 0.7397
-1.250 -0.3332 0.01565 0.01001 0.0091 0.9884 0.7559
-1.000 -0.3010 0.01611 0.01044 0.0083 0.9844 0.7670
-0.750 -0.2712 0.01645 0.01074 0.0078 0.9798 0.7781
-0.500 -0.2426 0.01672 0.01104 0.0078 0.9750 0.7879
-0.250 -0.2116 0.01705 0.01135 0.0072 0.9703 0.7988
0.000 -0.1834 0.01726 0.01157 0.0071 0.9658 0.8078
0.250 -0.1562 0.01743 0.01175 0.0073 0.9612 0.8164
0.500 -0.1271 0.01770 0.01205 0.0072 0.9566 0.8295
0.750 -0.1018 0.01778 0.01217 0.0077 0.9504 0.8398
1.000 -0.0658 0.01798 0.01238 0.0060 0.9462 0.8463
1.250 -0.0361 0.01793 0.01237 0.0056 0.9382 0.8524
1.500 0.0019 0.01791 0.01237 0.0036 0.9293 0.8575
1.750 0.0540 0.01787 0.01238 -0.0010 0.9233 0.8606
2.000 0.0897 0.01756 0.01214 -0.0024 0.9128 0.8641
2.250 0.1294 0.01722 0.01186 -0.0043 0.9024 0.8678
2.500 0.2212 0.01537 0.01013 -0.0145 0.8836 0.8678
2.750 0.2719 0.01401 0.00886 -0.0173 0.8651 0.8704
3.000 0.3123 0.01269 0.00763 -0.0179 0.8418 0.8737
3.250 0.3461 0.01164 0.00667 -0.0175 0.8013 0.8767
3.500 0.3866 0.01353 0.00575 -0.0191 0.2086 0.8782
3.750 0.3940 0.01475 0.00628 -0.0154 0.0907 0.8844
4.000 0.4114 0.01531 0.00679 -0.0134 0.0781 0.8897
4.250 0.4321 0.01570 0.00719 -0.0119 0.0713 0.8952
4.500 0.4520 0.01649 0.00791 -0.0106 0.0653 0.9007
4.750 0.4787 0.01709 0.00856 -0.0104 0.0619 0.9056
5.000 0.5068 0.01778 0.00925 -0.0107 0.0582 0.9111
5.250 0.5433 0.01935 0.01072 -0.0128 0.0540 0.9157
5.500 0.5784 0.02019 0.01169 -0.0142 0.0517 0.9211
5.750 0.6158 0.02145 0.01306 -0.0162 0.0509 0.9261
6.000 0.6516 0.02264 0.01436 -0.0178 0.0484 0.9318
6.250 0.6868 0.02409 0.01581 -0.0198 0.0459 0.9381
6.500 0.7245 0.02623 0.01815 -0.0220 0.0454 0.9445
6.750 0.7627 0.02903 0.02126 -0.0243 0.0452 0.9507
7.000 0.7936 0.03349 0.02675 -0.0239 0.0512 0.9612
7.250 0.7240 0.02329 0.01855 -0.0049 0.0990 0.9474
7.500 0.7343 0.03082 0.02596 -0.0063 0.0950 0.9518
7.750 0.7584 0.03129 0.02702 -0.0057 0.0844 1.0000
8.000 0.7699 0.03426 0.03001 -0.0047 0.0827 1.0000
8.250 0.8370 0.05558 0.05119 -0.0112 0.0746 1.0000
8.500 0.8413 0.05818 0.05394 -0.0092 0.0713 1.0000
8.750 0.8498 0.06076 0.05656 -0.0079 0.0695 1.0000
9.000 0.8585 0.06366 0.05947 -0.0069 0.0685 1.0000
9.250 0.8706 0.07354 0.06909 -0.0091 0.0662 1.0000
9.500 0.8586 0.07573 0.07154 -0.0057 0.0660 1.0000
9.750 0.8412 0.07772 0.07376 -0.0022 0.0657 1.0000
10.000 0.7960 0.08004 0.07636 0.0022 0.0649 1.0000
10.250 0.7589 0.08555 0.08204 0.0008 0.0639 1.0000
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Polar data table (+)
Polar graphs
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