J5012 12% (j5012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 50,000 Max Cl/Cd: 28.95 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-j5012-il-50000.txt Download as CSV file: xf-j5012-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6897 0.08916 0.08163 -0.0339 1.0000 0.1528
-10.500 -0.6930 0.08371 0.07619 -0.0349 1.0000 0.1514
-10.250 -0.7849 0.07433 0.06671 -0.0364 1.0000 0.1380
-10.000 -0.8024 0.07008 0.06239 -0.0343 1.0000 0.1374
-9.750 -0.8205 0.06594 0.05810 -0.0318 1.0000 0.1369
-9.500 -0.8359 0.06199 0.05393 -0.0289 1.0000 0.1366
-9.250 -0.8488 0.05820 0.04986 -0.0256 1.0000 0.1366
-9.000 -0.8599 0.05460 0.04588 -0.0219 1.0000 0.1371
-8.750 -0.8663 0.05121 0.04205 -0.0181 1.0000 0.1380
-8.500 -0.8615 0.04777 0.03838 -0.0155 1.0000 0.1400
-8.250 -0.8466 0.04532 0.03593 -0.0138 1.0000 0.1457
-8.000 -0.8438 0.04270 0.03284 -0.0103 1.0000 0.1509
-7.750 -0.8316 0.04006 0.03001 -0.0081 1.0000 0.1570
-7.500 -0.8197 0.03789 0.02754 -0.0055 1.0000 0.1655
-7.250 -0.8031 0.03581 0.02543 -0.0036 1.0000 0.1765
-7.000 -0.7868 0.03379 0.02329 -0.0016 1.0000 0.1892
-6.750 -0.7699 0.03202 0.02147 0.0004 1.0000 0.2057
-6.500 -0.7535 0.03033 0.01964 0.0026 1.0000 0.2262
-6.250 -0.7349 0.02875 0.01829 0.0044 1.0000 0.2523
-6.000 -0.7194 0.02731 0.01700 0.0069 1.0000 0.2858
-5.750 -0.7043 0.02594 0.01597 0.0095 1.0000 0.3282
-5.500 -0.6924 0.02472 0.01508 0.0128 1.0000 0.3818
-5.250 -0.6816 0.02375 0.01454 0.0167 1.0000 0.4440
-5.000 -0.6698 0.02313 0.01435 0.0208 1.0000 0.5097
-4.750 -0.6561 0.02287 0.01441 0.0251 1.0000 0.5736
-4.500 -0.6398 0.02293 0.01467 0.0294 1.0000 0.6324
-4.250 -0.6177 0.02339 0.01521 0.0331 1.0000 0.6854
-4.000 -0.5892 0.02419 0.01599 0.0362 1.0000 0.7330
-3.750 -0.5459 0.02546 0.01712 0.0371 1.0000 0.7761
-3.500 -0.4974 0.02663 0.01803 0.0365 1.0000 0.8159
-3.250 -0.3909 0.02844 0.01936 0.0261 1.0000 0.8509
-3.000 -0.3041 0.02893 0.01949 0.0168 1.0000 0.8822
-2.750 -0.2355 0.02876 0.01906 0.0094 1.0000 0.9115
-2.500 -0.1677 0.02824 0.01832 0.0014 1.0000 0.9391
-2.250 -0.0941 0.02727 0.01715 -0.0085 1.0000 0.9645
-2.000 -0.0217 0.02602 0.01574 -0.0187 1.0000 0.9891
-1.750 0.0168 0.02506 0.01472 -0.0232 1.0000 1.0000
-1.500 0.0197 0.02462 0.01430 -0.0209 1.0000 1.0000
-1.250 0.0208 0.02427 0.01397 -0.0182 1.0000 1.0000
-1.000 0.0198 0.02399 0.01371 -0.0151 1.0000 1.0000
-0.750 0.0169 0.02379 0.01353 -0.0117 1.0000 1.0000
-0.500 0.0123 0.02365 0.01341 -0.0079 1.0000 1.0000
-0.250 0.0065 0.02357 0.01334 -0.0040 1.0000 1.0000
0.000 0.0000 0.02355 0.01331 0.0000 1.0000 1.0000
0.250 -0.0065 0.02357 0.01334 0.0040 1.0000 1.0000
0.500 -0.0123 0.02365 0.01340 0.0079 1.0000 1.0000
0.750 -0.0169 0.02378 0.01352 0.0117 1.0000 1.0000
1.000 -0.0198 0.02398 0.01371 0.0151 1.0000 1.0000
1.250 -0.0208 0.02426 0.01396 0.0182 1.0000 1.0000
1.500 -0.0197 0.02462 0.01429 0.0208 1.0000 1.0000
1.750 -0.0168 0.02505 0.01471 0.0232 1.0000 1.0000
2.000 0.0213 0.02600 0.01573 0.0188 0.9892 1.0000
2.250 0.0936 0.02726 0.01714 0.0085 0.9647 1.0000
2.500 0.1677 0.02823 0.01831 -0.0014 0.9394 1.0000
2.750 0.2355 0.02875 0.01905 -0.0094 0.9115 1.0000
3.000 0.3041 0.02892 0.01948 -0.0168 0.8822 1.0000
3.250 0.3908 0.02843 0.01937 -0.0261 0.8509 1.0000
3.500 0.4975 0.02662 0.01803 -0.0365 0.8161 1.0000
3.750 0.5456 0.02547 0.01713 -0.0371 0.7762 1.0000
4.000 0.5892 0.02419 0.01599 -0.0362 0.7331 1.0000
4.250 0.6177 0.02339 0.01521 -0.0332 0.6855 1.0000
4.500 0.6397 0.02293 0.01467 -0.0294 0.6327 1.0000
4.750 0.6561 0.02286 0.01440 -0.0251 0.5736 1.0000
5.000 0.6697 0.02313 0.01434 -0.0208 0.5097 1.0000
5.250 0.6815 0.02375 0.01453 -0.0166 0.4439 1.0000
5.500 0.6923 0.02472 0.01508 -0.0128 0.3818 1.0000
5.750 0.7044 0.02594 0.01597 -0.0095 0.3284 1.0000
6.000 0.7195 0.02731 0.01699 -0.0069 0.2860 1.0000
6.250 0.7349 0.02875 0.01829 -0.0044 0.2523 1.0000
6.500 0.7535 0.03033 0.01965 -0.0026 0.2262 1.0000
6.750 0.7699 0.03201 0.02146 -0.0004 0.2058 1.0000
7.000 0.7867 0.03378 0.02328 0.0016 0.1890 1.0000
7.250 0.8031 0.03580 0.02542 0.0036 0.1764 1.0000
7.500 0.8195 0.03789 0.02754 0.0055 0.1654 1.0000
7.750 0.8317 0.04005 0.03000 0.0081 0.1569 1.0000
8.000 0.8434 0.04271 0.03286 0.0104 0.1507 1.0000
8.250 0.8465 0.04533 0.03594 0.0138 0.1456 1.0000
8.500 0.8613 0.04776 0.03838 0.0155 0.1400 1.0000
8.750 0.8661 0.05122 0.04206 0.0182 0.1379 1.0000
9.000 0.8595 0.05462 0.04591 0.0219 0.1370 1.0000
9.250 0.8489 0.05822 0.04988 0.0256 0.1366 1.0000
9.500 0.8341 0.06201 0.05397 0.0290 0.1364 1.0000
9.750 0.8174 0.06598 0.05815 0.0320 0.1367 1.0000
10.000 0.8001 0.07009 0.06240 0.0344 0.1373 1.0000
10.250 0.7836 0.07433 0.06671 0.0364 0.1380 1.0000
10.500 0.6367 0.09173 0.08412 0.0262 0.1625 1.0000
10.750 0.6035 0.10251 0.09477 0.0193 0.1783 1.0000
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Polar data table (+)
Polar graphs
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