BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il) Reynolds number: 500,000 Max Cl/Cd: 51.79 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacj-il-500000.txt Download as CSV file: xf-bacj-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6814 0.10236 0.09977 -0.0405 1.0000 0.0264
-13.000 -0.6795 0.10052 0.09796 -0.0407 1.0000 0.0267
-12.750 -0.8004 0.06821 0.06536 -0.0610 1.0000 0.0240
-12.500 -0.8583 0.05826 0.05515 -0.0651 1.0000 0.0232
-12.250 -0.8943 0.05308 0.04978 -0.0648 1.0000 0.0233
-12.000 -0.9900 0.04432 0.04041 -0.0596 1.0000 0.0223
-11.750 -0.9542 0.04641 0.04278 -0.0592 1.0000 0.0233
-11.500 -1.0120 0.04282 0.03888 -0.0511 1.0000 0.0227
-11.250 -1.0484 0.03874 0.03437 -0.0447 1.0000 0.0224
-11.000 -1.0446 0.03774 0.03331 -0.0420 1.0000 0.0227
-10.750 -1.0397 0.03663 0.03212 -0.0395 1.0000 0.0230
-10.500 -1.0367 0.03273 0.02775 -0.0383 0.9987 0.0227
-10.250 -1.0163 0.03097 0.02581 -0.0388 0.9971 0.0230
-10.000 -0.9949 0.02908 0.02370 -0.0393 0.9955 0.0233
-9.750 -0.9723 0.02761 0.02205 -0.0396 0.9935 0.0235
-9.500 -0.9478 0.02626 0.02053 -0.0401 0.9919 0.0241
-9.250 -0.9225 0.02506 0.01917 -0.0406 0.9908 0.0245
-9.000 -0.9017 0.02379 0.01774 -0.0400 0.9888 0.0249
-8.750 -0.8767 0.02311 0.01694 -0.0402 0.9871 0.0255
-8.500 -0.8503 0.02228 0.01597 -0.0405 0.9859 0.0259
-8.250 -0.8262 0.02072 0.01430 -0.0406 0.9850 0.0267
-8.000 -0.8057 0.01985 0.01340 -0.0398 0.9828 0.0273
-7.750 -0.7804 0.01917 0.01270 -0.0399 0.9810 0.0281
-7.500 -0.7528 0.01853 0.01202 -0.0404 0.9796 0.0291
-7.250 -0.7238 0.01797 0.01140 -0.0411 0.9787 0.0299
-7.000 -0.7029 0.01750 0.01088 -0.0401 0.9759 0.0309
-6.750 -0.6764 0.01690 0.01020 -0.0403 0.9741 0.0321
-6.500 -0.6491 0.01611 0.00941 -0.0408 0.9727 0.0337
-6.250 -0.6184 0.01571 0.00900 -0.0418 0.9718 0.0356
-6.000 -0.5995 0.01544 0.00869 -0.0401 0.9685 0.0381
-5.750 -0.5747 0.01485 0.00811 -0.0400 0.9666 0.0411
-5.500 -0.5452 0.01456 0.00781 -0.0406 0.9654 0.0445
-5.250 -0.5153 0.01416 0.00741 -0.0413 0.9644 0.0500
-5.000 -0.4959 0.01391 0.00715 -0.0398 0.9611 0.0555
-4.750 -0.4701 0.01352 0.00682 -0.0396 0.9589 0.0668
-4.500 -0.4421 0.01312 0.00658 -0.0400 0.9574 0.0910
-4.250 -0.4117 0.01279 0.00639 -0.0409 0.9563 0.1217
-4.000 -0.3881 0.01256 0.00626 -0.0403 0.9538 0.1469
-3.750 -0.3672 0.01234 0.00614 -0.0390 0.9506 0.1733
-3.500 -0.3407 0.01207 0.00602 -0.0390 0.9488 0.2092
-3.250 -0.3129 0.01168 0.00588 -0.0393 0.9474 0.2649
-2.750 -0.2792 0.01047 0.00560 -0.0355 0.9403 0.4964
-2.500 -0.2540 0.01021 0.00567 -0.0349 0.9381 0.5886
-2.250 -0.2234 0.01018 0.00573 -0.0353 0.9368 0.6283
-2.000 -0.1915 0.01022 0.00580 -0.0361 0.9358 0.6500
-1.750 -0.1739 0.01033 0.00591 -0.0338 0.9314 0.6647
-1.500 -0.1488 0.01041 0.00601 -0.0331 0.9285 0.6810
-1.250 -0.1175 0.01046 0.00605 -0.0337 0.9266 0.6956
-1.000 -0.0823 0.01042 0.00604 -0.0350 0.9253 0.7031
-0.750 -0.0488 0.01044 0.00604 -0.0362 0.9243 0.7109
-0.500 -0.0283 0.01046 0.00610 -0.0344 0.9186 0.7176
-0.250 0.0072 0.01031 0.00598 -0.0357 0.9154 0.7249
0.000 0.0488 0.01005 0.00573 -0.0382 0.9135 0.7308
0.250 0.0896 0.00983 0.00556 -0.0406 0.9122 0.7364
0.500 0.1332 0.00955 0.00530 -0.0436 0.9113 0.7452
0.750 0.1560 0.00938 0.00520 -0.0420 0.9033 0.7510
1.000 0.2343 0.00815 0.00402 -0.0516 0.8985 0.7551
1.250 0.2648 0.00776 0.00363 -0.0515 0.8857 0.7592
1.500 0.2984 0.00745 0.00331 -0.0521 0.8706 0.7627
1.750 0.3236 0.00726 0.00315 -0.0511 0.8489 0.7662
2.000 0.3698 0.00714 0.00287 -0.0545 0.7813 0.7686
2.250 0.3768 0.00784 0.00285 -0.0495 0.6221 0.7718
2.500 0.3624 0.00886 0.00308 -0.0405 0.4456 0.7758
2.750 0.3659 0.00988 0.00338 -0.0357 0.2771 0.7792
3.000 0.3758 0.01097 0.00372 -0.0325 0.1000 0.7819
3.250 0.3952 0.01152 0.00404 -0.0308 0.0582 0.7847
3.500 0.4176 0.01180 0.00433 -0.0297 0.0511 0.7879
3.750 0.4394 0.01215 0.00465 -0.0284 0.0462 0.7914
4.000 0.4612 0.01249 0.00498 -0.0271 0.0426 0.7947
4.250 0.4843 0.01273 0.00523 -0.0261 0.0402 0.7975
4.500 0.5057 0.01318 0.00568 -0.0249 0.0376 0.8003
4.750 0.5267 0.01374 0.00628 -0.0235 0.0361 0.8036
5.000 0.5498 0.01407 0.00665 -0.0225 0.0345 0.8071
5.250 0.5729 0.01436 0.00692 -0.0216 0.0324 0.8108
5.500 0.5955 0.01513 0.00767 -0.0207 0.0304 0.8140
5.750 0.6214 0.01599 0.00857 -0.0206 0.0300 0.8174
6.000 0.6461 0.01629 0.00896 -0.0199 0.0289 0.8210
6.250 0.6721 0.01687 0.00957 -0.0196 0.0274 0.8247
6.500 0.7013 0.01775 0.01051 -0.0200 0.0271 0.8280
6.750 0.7278 0.01830 0.01108 -0.0200 0.0259 0.8312
7.000 0.7572 0.01936 0.01217 -0.0206 0.0252 0.8346
7.250 0.7903 0.02118 0.01408 -0.0220 0.0248 0.8381
7.500 0.8178 0.02295 0.01606 -0.0221 0.0244 0.8421
7.750 0.8396 0.02337 0.01669 -0.0210 0.0236 0.8463
8.000 0.8647 0.02559 0.01919 -0.0206 0.0237 0.8501
8.250 0.8854 0.02740 0.02125 -0.0195 0.0236 0.8548
8.500 0.9010 0.02989 0.02410 -0.0175 0.0235 0.8595
8.750 0.9158 0.03249 0.02703 -0.0157 0.0236 0.8648
9.000 0.8043 0.03008 0.02641 0.0035 0.0329 0.8586
9.250 0.8057 0.03276 0.02926 0.0061 0.0321 0.8641
9.500 0.8010 0.03547 0.03209 0.0094 0.0318 0.8711
9.750 0.7893 0.03892 0.03575 0.0129 0.0317 0.8784
10.000 0.7843 0.04173 0.03869 0.0149 0.0314 0.8859
10.250 0.7811 0.04471 0.04179 0.0161 0.0311 0.8942
10.500 0.7676 0.04865 0.04589 0.0172 0.0309 0.9033
10.750 0.7461 0.05338 0.05079 0.0176 0.0309 0.9140
11.000 0.7307 0.05868 0.05624 0.0163 0.0307 0.9209
11.250 0.5777 0.08579 0.08362 0.0015 0.0320 0.9059
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