NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 50,000 Max Cl/Cd: 29.69 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca641112-il-50000.txt Download as CSV file: xf-naca641112-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4968 0.08565 0.07915 -0.0203 1.0000 0.1947
-9.250 -0.5517 0.07163 0.06521 -0.0309 1.0000 0.1599
-9.000 -0.6792 0.07460 0.06788 -0.0307 1.0000 0.1653
-8.750 -0.6963 0.06835 0.06148 -0.0325 1.0000 0.1528
-8.500 -0.7117 0.06296 0.05579 -0.0331 1.0000 0.1435
-8.250 -0.7365 0.05812 0.05011 -0.0323 1.0000 0.1337
-8.000 -0.7210 0.05353 0.04548 -0.0319 1.0000 0.1304
-7.750 -0.7137 0.04951 0.04110 -0.0308 1.0000 0.1271
-7.500 -0.7054 0.04579 0.03688 -0.0294 1.0000 0.1240
-7.250 -0.6925 0.04273 0.03342 -0.0280 1.0000 0.1244
-7.000 -0.6774 0.04010 0.03048 -0.0265 1.0000 0.1270
-6.750 -0.6610 0.03758 0.02760 -0.0249 1.0000 0.1291
-6.500 -0.6425 0.03523 0.02485 -0.0233 1.0000 0.1307
-6.250 -0.6234 0.03326 0.02245 -0.0216 1.0000 0.1337
-6.000 -0.6017 0.03114 0.02048 -0.0204 1.0000 0.1417
-5.750 -0.5794 0.02946 0.01863 -0.0189 1.0000 0.1498
-5.500 -0.5565 0.02790 0.01713 -0.0174 1.0000 0.1614
-5.250 -0.5372 0.02649 0.01584 -0.0154 1.0000 0.1789
-5.000 -0.5232 0.02502 0.01464 -0.0129 1.0000 0.2015
-4.750 -0.5166 0.02322 0.01333 -0.0098 1.0000 0.2458
-4.500 -0.5285 0.02068 0.01320 -0.0027 1.0000 0.5204
-4.250 -0.5361 0.02291 0.01570 0.0097 1.0000 0.6735
-4.000 -0.5306 0.02488 0.01758 0.0190 1.0000 0.7271
-3.750 -0.3104 0.03220 0.02362 0.0096 1.0000 0.8690
-3.500 -0.2486 0.03129 0.02236 0.0033 1.0000 0.8917
-3.250 -0.2201 0.03055 0.02143 0.0018 1.0000 0.9080
-3.000 -0.1958 0.02987 0.02062 0.0007 1.0000 0.9220
-2.750 -0.1739 0.02926 0.01990 -0.0003 1.0000 0.9346
-2.500 -0.1541 0.02873 0.01928 -0.0011 1.0000 0.9465
-2.250 -0.1333 0.02828 0.01872 -0.0022 1.0000 0.9581
-2.000 -0.1026 0.02774 0.01809 -0.0051 1.0000 0.9694
-1.750 -0.0705 0.02726 0.01752 -0.0085 1.0000 0.9802
-1.500 -0.0373 0.02684 0.01702 -0.0123 1.0000 0.9909
-1.250 -0.0075 0.02656 0.01668 -0.0157 1.0000 1.0000
-1.000 -0.0155 0.02666 0.01678 -0.0124 1.0000 1.0000
-0.750 -0.0232 0.02669 0.01681 -0.0093 1.0000 1.0000
-0.500 -0.0308 0.02667 0.01678 -0.0062 1.0000 1.0000
-0.250 -0.0385 0.02658 0.01668 -0.0031 1.0000 1.0000
0.000 -0.0465 0.02643 0.01651 0.0001 1.0000 1.0000
0.250 -0.0552 0.02619 0.01626 0.0034 1.0000 1.0000
0.500 -0.0646 0.02588 0.01593 0.0068 1.0000 1.0000
0.750 -0.0554 0.02585 0.01586 0.0071 0.9957 1.0000
1.000 -0.0321 0.02612 0.01610 0.0050 0.9870 1.0000
1.250 -0.0122 0.02642 0.01636 0.0037 0.9787 1.0000
1.500 0.0126 0.02695 0.01686 0.0017 0.9705 1.0000
1.750 0.0290 0.02728 0.01715 0.0013 0.9622 1.0000
2.000 0.0573 0.02801 0.01786 -0.0009 0.9540 1.0000
2.250 0.0846 0.02874 0.01857 -0.0028 0.9452 1.0000
2.500 0.1110 0.02951 0.01935 -0.0044 0.9365 1.0000
2.750 0.1483 0.03061 0.02048 -0.0079 0.9272 1.0000
3.000 0.1699 0.03133 0.02123 -0.0086 0.9173 1.0000
3.250 0.1983 0.03230 0.02227 -0.0103 0.9073 1.0000
3.500 0.2339 0.03345 0.02351 -0.0132 0.8964 1.0000
3.750 0.2625 0.03444 0.02460 -0.0148 0.8841 1.0000
4.000 0.2902 0.03544 0.02572 -0.0161 0.8705 1.0000
4.250 0.3232 0.03651 0.02696 -0.0181 0.8549 1.0000
4.500 0.3661 0.03760 0.02828 -0.0211 0.8367 1.0000
4.750 0.3906 0.03842 0.02928 -0.0213 0.8158 1.0000
5.000 0.4421 0.03898 0.03019 -0.0241 0.7890 1.0000
5.250 0.5212 0.03732 0.02912 -0.0266 0.7409 1.0000
5.500 0.6572 0.02550 0.01826 -0.0194 0.6325 1.0000
5.750 0.6580 0.02216 0.01375 -0.0056 0.3549 1.0000
6.000 0.6496 0.02538 0.01530 -0.0007 0.2297 1.0000
6.250 0.6645 0.02762 0.01703 0.0014 0.1892 1.0000
6.500 0.6934 0.02964 0.01872 0.0019 0.1629 1.0000
6.750 0.7293 0.03175 0.02081 0.0017 0.1468 1.0000
7.000 0.7626 0.03417 0.02310 0.0014 0.1348 1.0000
7.250 0.7902 0.03650 0.02588 0.0021 0.1297 1.0000
7.500 0.8161 0.03903 0.02854 0.0024 0.1236 1.0000
7.750 0.8387 0.04214 0.03187 0.0030 0.1196 1.0000
8.000 0.8574 0.04530 0.03553 0.0041 0.1190 1.0000
8.250 0.8739 0.04885 0.03948 0.0052 0.1193 1.0000
8.500 0.8871 0.05260 0.04362 0.0063 0.1197 1.0000
8.750 0.8959 0.05648 0.04789 0.0075 0.1200 1.0000
9.000 0.9031 0.06064 0.05238 0.0085 0.1204 1.0000
9.250 0.8793 0.06463 0.05721 0.0110 0.1256 1.0000
9.500 0.8626 0.06958 0.06250 0.0118 0.1297 1.0000
9.750 0.8539 0.07450 0.06757 0.0121 0.1326 1.0000
10.000 0.8027 0.08023 0.07352 0.0112 0.1402 1.0000
10.250 0.7796 0.08725 0.08056 0.0082 0.1471 1.0000
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Polar data table (+)
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