BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.3 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacj-il-1000000.txt Download as CSV file: xf-bacj-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9938 0.07292 0.07027 -0.0617 1.0000 0.0146
-15.750 -0.9968 0.06883 0.06614 -0.0641 1.0000 0.0149
-15.500 -1.0231 0.06123 0.05837 -0.0683 1.0000 0.0149
-15.250 -1.0565 0.05376 0.05067 -0.0714 1.0000 0.0148
-15.000 -1.0564 0.05142 0.04829 -0.0719 1.0000 0.0150
-14.750 -1.0817 0.04627 0.04293 -0.0725 1.0000 0.0148
-14.500 -1.0910 0.04343 0.03999 -0.0719 1.0000 0.0149
-14.250 -1.1048 0.04038 0.03679 -0.0707 1.0000 0.0149
-14.000 -1.1131 0.03818 0.03450 -0.0690 1.0000 0.0150
-13.750 -1.1117 0.03719 0.03349 -0.0674 1.0000 0.0154
-13.500 -1.1257 0.03482 0.03098 -0.0645 1.0000 0.0152
-13.250 -1.1297 0.03370 0.02980 -0.0619 1.0000 0.0154
-13.000 -1.1294 0.03177 0.02773 -0.0609 0.9993 0.0155
-12.750 -1.1154 0.03026 0.02611 -0.0620 0.9978 0.0157
-12.500 -1.1024 0.02862 0.02432 -0.0628 0.9961 0.0158
-12.250 -1.0896 0.02755 0.02313 -0.0621 0.9937 0.0162
-12.000 -1.0716 0.02612 0.02158 -0.0624 0.9920 0.0162
-11.750 -1.0478 0.02520 0.02055 -0.0633 0.9910 0.0166
-11.500 -1.0293 0.02408 0.01933 -0.0631 0.9889 0.0167
-11.250 -1.0087 0.02280 0.01792 -0.0632 0.9871 0.0169
-11.000 -0.9826 0.02215 0.01717 -0.0639 0.9861 0.0171
-10.750 -0.9560 0.02141 0.01635 -0.0647 0.9854 0.0172
-10.500 -0.9385 0.02024 0.01507 -0.0639 0.9829 0.0173
-10.250 -0.9198 0.01882 0.01354 -0.0635 0.9808 0.0176
-10.000 -0.8964 0.01770 0.01235 -0.0638 0.9797 0.0182
-9.750 -0.8692 0.01700 0.01159 -0.0645 0.9790 0.0183
-9.500 -0.8486 0.01652 0.01109 -0.0636 0.9764 0.0189
-9.250 -0.8231 0.01603 0.01057 -0.0638 0.9749 0.0193
-9.000 -0.7959 0.01550 0.00999 -0.0642 0.9739 0.0200
-8.750 -0.7674 0.01508 0.00953 -0.0649 0.9731 0.0203
-8.500 -0.7378 0.01465 0.00906 -0.0658 0.9725 0.0209
-8.250 -0.7081 0.01417 0.00852 -0.0667 0.9720 0.0215
-8.000 -0.6935 0.01355 0.00786 -0.0644 0.9677 0.0222
-7.750 -0.6662 0.01312 0.00743 -0.0647 0.9665 0.0233
-7.500 -0.6375 0.01277 0.00706 -0.0653 0.9657 0.0243
-7.250 -0.6081 0.01242 0.00668 -0.0660 0.9651 0.0250
-7.000 -0.5776 0.01217 0.00640 -0.0668 0.9646 0.0259
-6.750 -0.5596 0.01177 0.00598 -0.0650 0.9613 0.0276
-6.500 -0.5332 0.01143 0.00564 -0.0650 0.9596 0.0294
-6.250 -0.5038 0.01115 0.00535 -0.0656 0.9586 0.0313
-6.000 -0.4744 0.01077 0.00498 -0.0661 0.9578 0.0353
-5.750 -0.4432 0.01050 0.00471 -0.0671 0.9572 0.0383
-5.500 -0.4124 0.01016 0.00441 -0.0680 0.9567 0.0446
-5.250 -0.3814 0.00985 0.00415 -0.0689 0.9563 0.0527
-5.000 -0.3505 0.00953 0.00390 -0.0698 0.9559 0.0659
-4.750 -0.3397 0.00939 0.00381 -0.0662 0.9505 0.0798
-4.500 -0.3122 0.00906 0.00362 -0.0664 0.9493 0.1045
-4.250 -0.2821 0.00880 0.00344 -0.0671 0.9485 0.1256
-4.000 -0.2514 0.00852 0.00327 -0.0679 0.9478 0.1490
-3.750 -0.2201 0.00827 0.00311 -0.0688 0.9473 0.1730
-3.500 -0.1884 0.00797 0.00294 -0.0699 0.9467 0.2077
-3.250 -0.1573 0.00759 0.00277 -0.0709 0.9462 0.2594
-3.000 -0.1493 0.00741 0.00271 -0.0666 0.9403 0.2973
-2.750 -0.1243 0.00673 0.00245 -0.0663 0.9385 0.4132
-2.500 -0.0980 0.00620 0.00230 -0.0663 0.9374 0.5225
-2.250 -0.0670 0.00595 0.00225 -0.0670 0.9366 0.5834
-2.000 -0.0318 0.00584 0.00220 -0.0686 0.9360 0.6107
-1.750 -0.0137 0.00577 0.00216 -0.0662 0.9308 0.6272
-1.500 0.0136 0.00574 0.00218 -0.0660 0.9286 0.6458
-1.250 0.0521 0.00562 0.00206 -0.0682 0.9266 0.6593
-1.000 0.0912 0.00550 0.00196 -0.0706 0.9249 0.6665
-0.750 0.1184 0.00544 0.00191 -0.0702 0.9205 0.6733
-0.500 0.1458 0.00535 0.00183 -0.0699 0.9151 0.6800
-0.250 0.1810 0.00521 0.00170 -0.0712 0.9086 0.6859
0.000 0.2133 0.00509 0.00155 -0.0719 0.8974 0.6914
0.250 0.2332 0.00504 0.00147 -0.0698 0.8839 0.6958
0.500 0.2568 0.00499 0.00145 -0.0686 0.8724 0.7012
0.750 0.2812 0.00499 0.00142 -0.0675 0.8546 0.7064
1.000 0.3048 0.00506 0.00137 -0.0663 0.8191 0.7118
1.250 0.3212 0.00524 0.00136 -0.0634 0.7586 0.7173
1.500 0.3165 0.00578 0.00146 -0.0559 0.6477 0.7211
1.750 0.3147 0.00647 0.00165 -0.0493 0.5230 0.7260
2.000 0.3180 0.00743 0.00192 -0.0443 0.3472 0.7295
2.500 0.3514 0.00860 0.00232 -0.0399 0.1417 0.7358
2.750 0.3701 0.00917 0.00256 -0.0381 0.0630 0.7394
3.000 0.3925 0.00948 0.00277 -0.0370 0.0441 0.7429
3.250 0.4162 0.00969 0.00294 -0.0360 0.0397 0.7453
3.500 0.4406 0.00990 0.00315 -0.0353 0.0359 0.7483
3.750 0.4651 0.01007 0.00333 -0.0346 0.0331 0.7512
4.000 0.4889 0.01033 0.00359 -0.0337 0.0311 0.7539
4.250 0.5124 0.01063 0.00391 -0.0327 0.0297 0.7567
4.500 0.5372 0.01078 0.00406 -0.0321 0.0281 0.7594
4.750 0.5611 0.01103 0.00430 -0.0313 0.0270 0.7619
5.000 0.5855 0.01132 0.00459 -0.0306 0.0255 0.7647
5.250 0.6087 0.01172 0.00504 -0.0297 0.0243 0.7675
5.500 0.6335 0.01193 0.00528 -0.0291 0.0230 0.7702
5.750 0.6566 0.01230 0.00568 -0.0281 0.0231 0.7732
6.000 0.6808 0.01256 0.00593 -0.0274 0.0218 0.7763
6.250 0.7023 0.01312 0.00648 -0.0263 0.0203 0.7795
6.500 0.7257 0.01371 0.00714 -0.0255 0.0202 0.7828
6.750 0.7505 0.01397 0.00745 -0.0250 0.0194 0.7861
7.000 0.7744 0.01441 0.00792 -0.0242 0.0190 0.7893
7.250 0.7976 0.01494 0.00849 -0.0234 0.0187 0.7929
7.500 0.8210 0.01543 0.00903 -0.0227 0.0181 0.7960
7.750 0.8474 0.01571 0.00934 -0.0226 0.0176 0.7995
8.000 0.8721 0.01634 0.01003 -0.0222 0.0172 0.8028
8.250 0.8965 0.01694 0.01069 -0.0218 0.0171 0.8063
8.500 0.9223 0.01877 0.01261 -0.0221 0.0161 0.8093
8.750 0.9470 0.01951 0.01343 -0.0217 0.0161 0.8127
9.000 0.9729 0.02052 0.01458 -0.0218 0.0160 0.8163
9.250 0.9964 0.02129 0.01546 -0.0213 0.0159 0.8203
9.500 1.0184 0.02219 0.01650 -0.0205 0.0157 0.8243
9.750 1.0392 0.02373 0.01822 -0.0196 0.0156 0.8282
10.000 1.0610 0.02498 0.01967 -0.0190 0.0154 0.8324
10.250 1.0807 0.02602 0.02086 -0.0181 0.0151 0.8375
10.500 1.0950 0.02785 0.02293 -0.0163 0.0150 0.8427
10.750 1.1105 0.02974 0.02507 -0.0151 0.0148 0.8480
11.000 1.1263 0.03112 0.02665 -0.0139 0.0145 0.8536
11.250 1.0924 0.03943 0.03581 -0.0069 0.0150 0.8608
11.500 1.0333 0.04924 0.04637 0.0005 0.0147 0.8725
11.750 0.9592 0.06153 0.05926 0.0031 0.0149 0.8820
12.000 0.9165 0.07156 0.06962 -0.0014 0.0152 0.8928
12.250 0.8503 0.09607 0.09441 -0.0227 0.0160 0.9012
12.500 1.0847 0.05869 0.05653 -0.0083 0.0136 0.9473
12.750 0.7673 0.13504 0.13338 -0.0447 0.0176 0.9109
13.000 0.7781 0.14138 0.13979 -0.0507 0.0174 0.9235
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