J5012 12% (j5012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 500,000 Max Cl/Cd: 59.94 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-j5012-il-500000.txt Download as CSV file: xf-j5012-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: J5012 12%
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9440 0.09733 0.09422 -0.0294 1.0000 0.0178
-16.500 -0.9784 0.08662 0.08331 -0.0361 1.0000 0.0178
-16.250 -1.0017 0.07858 0.07506 -0.0411 1.0000 0.0176
-16.000 -1.0233 0.07146 0.06776 -0.0452 1.0000 0.0176
-15.750 -1.0382 0.06582 0.06193 -0.0483 1.0000 0.0175
-15.500 -1.0542 0.06043 0.05640 -0.0507 1.0000 0.0177
-15.250 -1.0657 0.05598 0.05183 -0.0523 1.0000 0.0179
-15.000 -1.0749 0.05202 0.04771 -0.0535 1.0000 0.0180
-14.750 -1.0818 0.04856 0.04413 -0.0541 1.0000 0.0181
-14.500 -1.0845 0.04580 0.04127 -0.0543 1.0000 0.0183
-14.250 -1.0859 0.04337 0.03876 -0.0542 1.0000 0.0186
-14.000 -1.0885 0.04085 0.03610 -0.0536 1.0000 0.0187
-13.750 -1.0894 0.03866 0.03379 -0.0527 1.0000 0.0190
-13.500 -1.0887 0.03678 0.03179 -0.0515 1.0000 0.0193
-13.250 -1.0861 0.03516 0.03005 -0.0501 1.0000 0.0196
-13.000 -1.0830 0.03370 0.02847 -0.0484 1.0000 0.0201
-12.750 -1.0798 0.03209 0.02673 -0.0464 1.0000 0.0203
-12.500 -1.0749 0.03079 0.02530 -0.0443 1.0000 0.0207
-12.250 -1.0692 0.02956 0.02393 -0.0420 1.0000 0.0210
-12.000 -1.0624 0.02840 0.02265 -0.0396 1.0000 0.0212
-11.750 -1.0547 0.02749 0.02162 -0.0371 1.0000 0.0215
-11.500 -1.0512 0.02548 0.01949 -0.0342 1.0000 0.0220
-11.250 -1.0455 0.02431 0.01826 -0.0312 1.0000 0.0226
-11.000 -1.0384 0.02351 0.01742 -0.0281 1.0000 0.0231
-10.750 -1.0310 0.02289 0.01676 -0.0249 1.0000 0.0236
-10.500 -1.0235 0.02230 0.01613 -0.0215 1.0000 0.0243
-10.250 -1.0137 0.02162 0.01538 -0.0186 1.0000 0.0249
-10.000 -1.0026 0.02098 0.01467 -0.0158 1.0000 0.0256
-9.750 -0.9910 0.02037 0.01399 -0.0130 1.0000 0.0262
-9.500 -0.9789 0.01983 0.01337 -0.0102 1.0000 0.0266
-9.250 -0.9742 0.01876 0.01223 -0.0063 1.0000 0.0275
-9.000 -0.9660 0.01802 0.01148 -0.0029 1.0000 0.0285
-8.750 -0.9543 0.01751 0.01095 -0.0001 1.0000 0.0294
-8.500 -0.9421 0.01704 0.01044 0.0027 1.0000 0.0305
-8.250 -0.9284 0.01666 0.01001 0.0053 1.0000 0.0320
-8.000 -0.9153 0.01622 0.00951 0.0080 1.0000 0.0333
-7.750 -0.9057 0.01554 0.00882 0.0112 1.0000 0.0356
-7.500 -0.8914 0.01517 0.00843 0.0136 1.0000 0.0379
-7.250 -0.8756 0.01488 0.00810 0.0158 1.0000 0.0403
-7.000 -0.8548 0.01427 0.00750 0.0168 0.9990 0.0451
-6.750 -0.8209 0.01386 0.00707 0.0152 0.9964 0.0509
-6.500 -0.7866 0.01345 0.00669 0.0135 0.9941 0.0588
-6.250 -0.7554 0.01298 0.00627 0.0124 0.9909 0.0688
-6.000 -0.7226 0.01256 0.00590 0.0110 0.9876 0.0810
-5.750 -0.6881 0.01216 0.00557 0.0093 0.9850 0.0975
-5.500 -0.6528 0.01172 0.00526 0.0074 0.9830 0.1221
-5.250 -0.6247 0.01127 0.00494 0.0070 0.9782 0.1510
-5.000 -0.5930 0.01077 0.00465 0.0058 0.9745 0.1903
-4.750 -0.5589 0.01029 0.00438 0.0041 0.9719 0.2357
-4.500 -0.5232 0.00984 0.00413 0.0021 0.9700 0.2844
-4.250 -0.4977 0.00944 0.00390 0.0025 0.9637 0.3263
-4.000 -0.4648 0.00902 0.00368 0.0012 0.9601 0.3745
-3.750 -0.4293 0.00862 0.00346 -0.0006 0.9577 0.4236
-3.500 -0.3920 0.00826 0.00327 -0.0027 0.9559 0.4672
-3.250 -0.3654 0.00798 0.00312 -0.0024 0.9494 0.5052
-3.000 -0.3335 0.00766 0.00295 -0.0033 0.9449 0.5461
-2.750 -0.2989 0.00737 0.00279 -0.0046 0.9415 0.5844
-2.500 -0.2733 0.00716 0.00268 -0.0040 0.9337 0.6155
-2.250 -0.2424 0.00694 0.00254 -0.0044 0.9277 0.6451
-2.000 -0.2151 0.00677 0.00245 -0.0041 0.9197 0.6715
-1.750 -0.1865 0.00660 0.00235 -0.0040 0.9116 0.6970
-1.500 -0.1605 0.00648 0.00229 -0.0033 0.9016 0.7205
-1.250 -0.1317 0.00637 0.00222 -0.0032 0.8927 0.7420
-1.000 -0.1060 0.00628 0.00218 -0.0024 0.8811 0.7619
-0.750 -0.0800 0.00622 0.00214 -0.0017 0.8691 0.7806
-0.500 -0.0533 0.00618 0.00212 -0.0012 0.8568 0.7977
-0.250 -0.0266 0.00615 0.00209 -0.0006 0.8437 0.8141
0.000 0.0000 0.00614 0.00209 0.0000 0.8296 0.8296
0.250 0.0265 0.00615 0.00209 0.0006 0.8141 0.8438
0.500 0.0533 0.00618 0.00212 0.0012 0.7979 0.8568
0.750 0.0800 0.00622 0.00214 0.0017 0.7804 0.8691
1.000 0.1060 0.00628 0.00218 0.0024 0.7619 0.8811
1.250 0.1316 0.00637 0.00222 0.0032 0.7419 0.8928
1.500 0.1605 0.00648 0.00229 0.0033 0.7205 0.9017
1.750 0.1865 0.00660 0.00235 0.0040 0.6970 0.9116
2.000 0.2152 0.00677 0.00245 0.0041 0.6721 0.9196
2.250 0.2424 0.00694 0.00254 0.0044 0.6454 0.9276
2.500 0.2733 0.00716 0.00268 0.0040 0.6154 0.9337
2.750 0.2989 0.00737 0.00279 0.0046 0.5843 0.9415
3.000 0.3335 0.00766 0.00294 0.0033 0.5461 0.9449
3.250 0.3653 0.00798 0.00311 0.0024 0.5051 0.9493
3.500 0.3919 0.00826 0.00327 0.0027 0.4672 0.9559
3.750 0.4292 0.00862 0.00346 0.0006 0.4228 0.9577
4.000 0.4648 0.00902 0.00368 -0.0012 0.3747 0.9601
4.250 0.4976 0.00944 0.00390 -0.0024 0.3260 0.9637
4.500 0.5231 0.00984 0.00413 -0.0021 0.2837 0.9700
4.750 0.5588 0.01030 0.00438 -0.0041 0.2348 0.9718
5.000 0.5929 0.01077 0.00465 -0.0058 0.1903 0.9745
5.250 0.6246 0.01126 0.00494 -0.0070 0.1513 0.9782
5.500 0.6528 0.01172 0.00526 -0.0074 0.1223 0.9829
5.750 0.6881 0.01216 0.00556 -0.0093 0.0978 0.9850
6.000 0.7227 0.01256 0.00590 -0.0111 0.0812 0.9876
6.250 0.7554 0.01298 0.00627 -0.0124 0.0688 0.9909
6.500 0.7867 0.01345 0.00669 -0.0135 0.0588 0.9941
6.750 0.8209 0.01387 0.00707 -0.0152 0.0506 0.9964
7.000 0.8548 0.01426 0.00749 -0.0168 0.0449 0.9990
7.250 0.8757 0.01487 0.00809 -0.0159 0.0402 1.0000
7.500 0.8914 0.01517 0.00843 -0.0136 0.0379 1.0000
7.750 0.9057 0.01554 0.00883 -0.0112 0.0356 1.0000
8.000 0.9136 0.01634 0.00962 -0.0077 0.0330 1.0000
8.250 0.9284 0.01666 0.01001 -0.0053 0.0319 1.0000
8.500 0.9418 0.01706 0.01046 -0.0027 0.0306 1.0000
8.750 0.9543 0.01751 0.01095 0.0001 0.0294 1.0000
9.000 0.9657 0.01803 0.01149 0.0030 0.0284 1.0000
9.250 0.9736 0.01880 0.01228 0.0064 0.0274 1.0000
9.500 0.9789 0.01983 0.01337 0.0103 0.0265 1.0000
9.750 0.9912 0.02036 0.01398 0.0130 0.0261 1.0000
10.000 1.0025 0.02099 0.01468 0.0158 0.0255 1.0000
10.250 1.0137 0.02162 0.01538 0.0186 0.0248 1.0000
10.500 1.0242 0.02221 0.01603 0.0214 0.0241 1.0000
10.750 1.0309 0.02292 0.01679 0.0249 0.0236 1.0000
11.000 1.0381 0.02359 0.01750 0.0282 0.0231 1.0000
11.250 1.0455 0.02435 0.01830 0.0312 0.0226 1.0000
11.500 1.0519 0.02545 0.01947 0.0341 0.0222 1.0000
11.750 1.0555 0.02746 0.02159 0.0370 0.0215 1.0000
12.000 1.0627 0.02853 0.02277 0.0395 0.0213 1.0000
12.250 1.0695 0.02961 0.02399 0.0419 0.0211 1.0000
12.500 1.0753 0.03081 0.02532 0.0442 0.0207 1.0000
12.750 1.0798 0.03224 0.02689 0.0464 0.0204 1.0000
13.000 1.0836 0.03370 0.02848 0.0483 0.0201 1.0000
13.250 1.0868 0.03519 0.03009 0.0500 0.0197 1.0000
13.500 1.0879 0.03704 0.03207 0.0515 0.0194 1.0000
13.750 1.0874 0.03913 0.03430 0.0527 0.0192 1.0000
14.000 1.0873 0.04117 0.03646 0.0536 0.0189 1.0000
14.250 1.0870 0.04334 0.03872 0.0540 0.0186 1.0000
14.500 1.0840 0.04602 0.04152 0.0542 0.0184 1.0000
14.750 1.0805 0.04889 0.04450 0.0539 0.0182 1.0000
15.000 1.0729 0.05247 0.04822 0.0532 0.0181 1.0000
15.250 1.0670 0.05599 0.05184 0.0521 0.0179 1.0000
15.500 1.0551 0.06054 0.05654 0.0504 0.0178 1.0000
15.750 1.0411 0.06566 0.06179 0.0481 0.0176 1.0000
16.000 1.0252 0.07147 0.06778 0.0449 0.0177 1.0000
16.250 1.0037 0.07854 0.07502 0.0409 0.0176 1.0000
16.500 0.9794 0.08674 0.08343 0.0357 0.0177 1.0000
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Polar data table (+)
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