NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 100,000 Max Cl/Cd: 45.81 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632a015-il-100000.txt Download as CSV file: xf-naca632a015-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4574 0.09832 0.09332 -0.0351 1.0000 0.1273
-10.250 -0.4807 0.09221 0.08729 -0.0401 1.0000 0.1318
-10.000 -0.5319 0.08460 0.07972 -0.0469 1.0000 0.1331
-9.750 -0.5032 0.08214 0.07735 -0.0437 1.0000 0.1406
-9.500 -0.5249 0.07740 0.07264 -0.0454 1.0000 0.1444
-9.250 -0.5612 0.07315 0.06840 -0.0456 1.0000 0.1456
-9.000 -0.5948 0.07049 0.06574 -0.0423 1.0000 0.1463
-8.750 -0.6356 0.06858 0.06374 -0.0373 1.0000 0.1485
-6.000 -0.6458 0.04034 0.03246 -0.0036 0.9802 0.0858
-5.750 -0.6092 0.03789 0.02916 -0.0039 0.9725 0.0752
-5.500 -0.5725 0.03449 0.02563 -0.0057 0.9662 0.0730
-5.250 -0.5334 0.03232 0.02313 -0.0074 0.9595 0.0735
-5.000 -0.4947 0.03018 0.02077 -0.0094 0.9531 0.0768
-4.750 -0.4543 0.02832 0.01893 -0.0116 0.9464 0.0799
-4.500 -0.4060 0.02708 0.01752 -0.0151 0.9416 0.0874
-4.250 -0.3739 0.02539 0.01607 -0.0160 0.9333 0.0948
-4.000 -0.3332 0.02405 0.01486 -0.0185 0.9275 0.1070
-3.750 -0.3070 0.02332 0.01413 -0.0183 0.9180 0.1181
-3.500 -0.2756 0.02218 0.01303 -0.0193 0.9110 0.1320
-3.000 -0.2491 0.01879 0.01162 -0.0150 0.8933 0.5095
-2.750 -0.2448 0.01911 0.01250 -0.0086 0.8816 0.6611
-2.500 -0.2096 0.01986 0.01330 -0.0071 0.8762 0.7289
-2.250 -0.1898 0.02042 0.01383 -0.0043 0.8659 0.7563
-2.000 -0.1495 0.02094 0.01429 -0.0046 0.8605 0.7850
-1.750 -0.0850 0.02223 0.01556 -0.0074 0.8581 0.8168
-1.500 -0.0493 0.02303 0.01630 -0.0071 0.8485 0.8352
-1.250 -0.0002 0.02290 0.01604 -0.0107 0.8430 0.8420
-1.000 0.0328 0.02298 0.01604 -0.0118 0.8338 0.8492
-0.750 0.0661 0.02276 0.01572 -0.0128 0.8265 0.8578
-0.500 0.1083 0.02287 0.01575 -0.0154 0.8179 0.8633
-0.250 0.1333 0.02269 0.01550 -0.0150 0.8096 0.8737
0.000 0.1809 0.02278 0.01553 -0.0186 0.8010 0.8782
0.250 0.2245 0.02261 0.01529 -0.0213 0.7924 0.8847
0.500 0.2544 0.02257 0.01521 -0.0217 0.7811 0.8930
0.750 0.3070 0.02222 0.01477 -0.0256 0.7708 0.8975
1.000 0.3296 0.02204 0.01454 -0.0245 0.7581 0.9079
1.250 0.3759 0.02188 0.01435 -0.0278 0.7449 0.9129
1.500 0.4051 0.02175 0.01418 -0.0279 0.7342 0.9226
1.750 0.4498 0.02151 0.01389 -0.0309 0.7233 0.9283
2.000 0.4816 0.02148 0.01388 -0.0320 0.7108 0.9374
2.250 0.5207 0.02129 0.01367 -0.0341 0.6988 0.9446
2.500 0.5601 0.02099 0.01331 -0.0361 0.6881 0.9527
2.750 0.5973 0.02081 0.01316 -0.0381 0.6738 0.9606
3.000 0.6307 0.02065 0.01302 -0.0394 0.6598 0.9701
3.250 0.6738 0.02030 0.01267 -0.0425 0.6445 0.9772
3.500 0.7126 0.01997 0.01233 -0.0448 0.6284 0.9855
3.750 0.7528 0.01961 0.01197 -0.0475 0.6110 0.9936
4.000 0.7911 0.01918 0.01152 -0.0497 0.5919 1.0000
4.250 0.8060 0.01904 0.01134 -0.0476 0.5746 1.0000
4.500 0.8208 0.01889 0.01115 -0.0454 0.5564 1.0000
4.750 0.8338 0.01883 0.01106 -0.0429 0.5360 1.0000
5.000 0.8456 0.01883 0.01101 -0.0402 0.5137 1.0000
5.250 0.8584 0.01884 0.01091 -0.0376 0.4916 1.0000
5.500 0.8689 0.01898 0.01099 -0.0348 0.4686 1.0000
5.750 0.8791 0.01919 0.01111 -0.0318 0.4467 1.0000
6.000 0.8902 0.01945 0.01123 -0.0290 0.4270 1.0000
6.250 0.9017 0.01978 0.01141 -0.0263 0.4090 1.0000
6.500 0.9123 0.02017 0.01174 -0.0234 0.3917 1.0000
6.750 0.9248 0.02061 0.01208 -0.0209 0.3763 1.0000
7.000 0.9382 0.02110 0.01250 -0.0185 0.3621 1.0000
7.250 0.9516 0.02164 0.01302 -0.0161 0.3489 1.0000
7.500 0.9663 0.02224 0.01361 -0.0140 0.3368 1.0000
7.750 0.9828 0.02287 0.01418 -0.0123 0.3254 1.0000
8.000 1.0017 0.02352 0.01468 -0.0109 0.3138 1.0000
8.250 1.0136 0.02412 0.01537 -0.0084 0.3018 1.0000
8.500 1.0273 0.02478 0.01605 -0.0062 0.2901 1.0000
8.750 1.0434 0.02546 0.01667 -0.0045 0.2787 1.0000
9.000 1.0591 0.02612 0.01729 -0.0027 0.2676 1.0000
9.250 1.0705 0.02687 0.01818 -0.0003 0.2573 1.0000
9.500 1.0865 0.02767 0.01894 0.0014 0.2469 1.0000
9.750 1.1015 0.02840 0.01964 0.0032 0.2362 1.0000
10.000 1.1098 0.02924 0.02064 0.0060 0.2259 1.0000
10.250 1.1242 0.03015 0.02154 0.0078 0.2156 1.0000
10.500 1.1379 0.03096 0.02230 0.0097 0.2047 1.0000
10.750 1.1409 0.03193 0.02346 0.0131 0.1947 1.0000
11.000 1.1499 0.03286 0.02437 0.0155 0.1845 1.0000
11.250 1.1594 0.03360 0.02503 0.0178 0.1743 1.0000
11.500 1.1535 0.03462 0.02628 0.0223 0.1661 1.0000
11.750 1.1611 0.03547 0.02700 0.0247 0.1575 1.0000
12.000 1.1552 0.03655 0.02827 0.0287 0.1501 1.0000
12.250 1.1622 0.03769 0.02936 0.0307 0.1428 1.0000
12.500 1.1604 0.03907 0.03090 0.0334 0.1365 1.0000
12.750 1.1714 0.04038 0.03213 0.0347 0.1301 1.0000
13.000 1.1664 0.04221 0.03422 0.0372 0.1250 1.0000
13.250 1.1871 0.04332 0.03509 0.0375 0.1186 1.0000
13.500 1.1754 0.04565 0.03778 0.0400 0.1153 1.0000
13.750 1.1727 0.04770 0.04000 0.0415 0.1112 1.0000
14.000 1.1946 0.04907 0.04116 0.0417 0.1060 1.0000
14.250 1.1806 0.05205 0.04449 0.0434 0.1039 1.0000
14.500 1.1692 0.05519 0.04789 0.0445 0.1015 1.0000
14.750 1.1621 0.05816 0.05105 0.0451 0.0991 1.0000
15.000 1.1927 0.05933 0.05199 0.0453 0.0945 1.0000
15.250 1.1683 0.06349 0.05647 0.0458 0.0938 1.0000
15.500 1.1420 0.06837 0.06164 0.0455 0.0932 1.0000
15.750 1.1106 0.07425 0.06781 0.0442 0.0928 1.0000
16.000 1.0730 0.08150 0.07532 0.0417 0.0929 1.0000
16.250 1.0261 0.09097 0.08502 0.0374 0.0935 1.0000
16.500 0.9724 0.10312 0.09734 0.0313 0.0945 1.0000
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Polar data table (+)
Polar graphs
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