NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 500,000 Max Cl/Cd: 56.01 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca641112-il-500000-n5.txt Download as CSV file: xf-naca641112-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9048 0.08288 0.08025 -0.0194 1.0000 0.0102
-14.500 -0.9684 0.06652 0.06352 -0.0302 1.0000 0.0100
-14.250 -0.9946 0.05901 0.05579 -0.0345 1.0000 0.0099
-14.000 -1.0029 0.05473 0.05137 -0.0367 1.0000 0.0101
-13.750 -1.0198 0.04959 0.04602 -0.0387 1.0000 0.0101
-13.500 -1.0255 0.04624 0.04253 -0.0396 1.0000 0.0103
-13.250 -1.0320 0.04298 0.03909 -0.0401 1.0000 0.0104
-13.000 -1.0355 0.04020 0.03615 -0.0401 1.0000 0.0106
-12.750 -1.0401 0.03742 0.03317 -0.0396 1.0000 0.0107
-12.500 -1.0419 0.03501 0.03057 -0.0387 1.0000 0.0109
-12.250 -1.0406 0.03301 0.02839 -0.0376 1.0000 0.0111
-12.000 -1.0372 0.03129 0.02649 -0.0362 1.0000 0.0113
-11.750 -1.0329 0.02963 0.02465 -0.0345 1.0000 0.0114
-11.500 -1.0263 0.02827 0.02314 -0.0327 1.0000 0.0116
-11.250 -1.0175 0.02708 0.02179 -0.0308 1.0000 0.0118
-11.000 -1.0069 0.02565 0.02021 -0.0293 1.0000 0.0121
-10.750 -0.9929 0.02448 0.01894 -0.0282 1.0000 0.0123
-10.500 -0.9756 0.02372 0.01813 -0.0273 1.0000 0.0127
-10.250 -0.9569 0.02305 0.01741 -0.0265 1.0000 0.0130
-10.000 -0.9382 0.02221 0.01649 -0.0257 1.0000 0.0133
-9.750 -0.9190 0.02135 0.01554 -0.0249 1.0000 0.0136
-9.500 -0.8992 0.02053 0.01463 -0.0242 1.0000 0.0140
-9.250 -0.8791 0.01971 0.01371 -0.0234 1.0000 0.0143
-9.000 -0.8587 0.01893 0.01285 -0.0227 1.0000 0.0147
-8.750 -0.8335 0.01822 0.01205 -0.0229 0.9862 0.0151
-8.500 -0.8007 0.01753 0.01126 -0.0246 0.9664 0.0156
-8.250 -0.7724 0.01655 0.01021 -0.0256 0.9493 0.0162
-8.000 -0.7476 0.01597 0.00956 -0.0255 0.9326 0.0167
-7.750 -0.7250 0.01548 0.00900 -0.0248 0.9171 0.0172
-7.500 -0.7027 0.01502 0.00846 -0.0240 0.9030 0.0178
-7.250 -0.6800 0.01458 0.00792 -0.0233 0.8902 0.0184
-7.000 -0.6568 0.01415 0.00741 -0.0226 0.8783 0.0191
-6.750 -0.6331 0.01376 0.00692 -0.0221 0.8673 0.0198
-6.500 -0.6096 0.01331 0.00639 -0.0215 0.8569 0.0208
-6.250 -0.5853 0.01290 0.00594 -0.0210 0.8466 0.0222
-6.000 -0.5602 0.01258 0.00557 -0.0207 0.8370 0.0236
-5.500 -0.5091 0.01199 0.00483 -0.0201 0.8184 0.0266
-5.250 -0.4837 0.01163 0.00443 -0.0199 0.8098 0.0294
-5.000 -0.4574 0.01138 0.00413 -0.0197 0.8008 0.0321
-4.750 -0.4309 0.01114 0.00384 -0.0196 0.7928 0.0351
-4.500 -0.4045 0.01087 0.00356 -0.0194 0.7842 0.0410
-4.250 -0.3779 0.01061 0.00330 -0.0194 0.7759 0.0500
-4.000 -0.3516 0.01031 0.00304 -0.0193 0.7675 0.0691
-3.750 -0.3256 0.00991 0.00278 -0.0192 0.7595 0.1066
-3.500 -0.3004 0.00936 0.00247 -0.0191 0.7518 0.1749
-3.250 -0.2756 0.00866 0.00215 -0.0191 0.7442 0.2738
-3.000 -0.2512 0.00793 0.00184 -0.0190 0.7367 0.3914
-2.750 -0.2248 0.00757 0.00173 -0.0190 0.7290 0.4707
-2.500 -0.1973 0.00744 0.00165 -0.0190 0.7213 0.5044
-2.250 -0.1696 0.00731 0.00160 -0.0190 0.7137 0.5390
-2.000 -0.1424 0.00720 0.00160 -0.0189 0.7064 0.5797
-1.750 -0.1144 0.00715 0.00158 -0.0189 0.6996 0.6027
-1.500 -0.0860 0.00713 0.00154 -0.0190 0.6926 0.6120
-1.250 -0.0575 0.00711 0.00150 -0.0191 0.6861 0.6199
-1.000 -0.0290 0.00710 0.00147 -0.0193 0.6793 0.6272
-0.750 -0.0004 0.00710 0.00144 -0.0194 0.6728 0.6334
-0.500 0.0281 0.00709 0.00143 -0.0196 0.6657 0.6397
-0.250 0.0567 0.00711 0.00141 -0.0197 0.6594 0.6459
0.000 0.0853 0.00710 0.00142 -0.0199 0.6531 0.6517
0.250 0.1139 0.00711 0.00142 -0.0200 0.6471 0.6582
0.500 0.1424 0.00712 0.00144 -0.0202 0.6415 0.6644
0.750 0.1710 0.00713 0.00147 -0.0203 0.6354 0.6715
1.250 0.2280 0.00717 0.00155 -0.0206 0.6229 0.6854
1.500 0.2564 0.00722 0.00159 -0.0207 0.6156 0.6924
1.750 0.2848 0.00723 0.00165 -0.0208 0.6076 0.6993
2.000 0.3131 0.00729 0.00171 -0.0209 0.5997 0.7067
2.250 0.3408 0.00734 0.00176 -0.0208 0.5826 0.7137
2.500 0.3679 0.00746 0.00179 -0.0207 0.5493 0.7217
2.750 0.3948 0.00759 0.00187 -0.0206 0.5172 0.7294
3.000 0.4215 0.00780 0.00195 -0.0204 0.4785 0.7376
3.250 0.4481 0.00800 0.00208 -0.0203 0.4392 0.7451
3.500 0.4718 0.00861 0.00233 -0.0199 0.3451 0.7532
3.750 0.4939 0.00943 0.00274 -0.0194 0.2386 0.7609
4.000 0.5170 0.01015 0.00312 -0.0190 0.1558 0.7693
4.250 0.5410 0.01069 0.00347 -0.0186 0.1028 0.7778
4.500 0.5655 0.01117 0.00381 -0.0183 0.0659 0.7866
4.750 0.5905 0.01154 0.00412 -0.0180 0.0475 0.7956
5.000 0.6161 0.01183 0.00442 -0.0177 0.0395 0.8042
5.250 0.6416 0.01213 0.00474 -0.0174 0.0346 0.8135
5.500 0.6668 0.01240 0.00507 -0.0170 0.0311 0.8228
5.750 0.6912 0.01277 0.00546 -0.0166 0.0275 0.8325
6.000 0.7162 0.01304 0.00580 -0.0162 0.0258 0.8430
6.250 0.7404 0.01335 0.00619 -0.0157 0.0239 0.8533
6.500 0.7638 0.01373 0.00660 -0.0150 0.0222 0.8643
6.750 0.7862 0.01417 0.00712 -0.0142 0.0208 0.8765
7.000 0.8087 0.01453 0.00756 -0.0134 0.0198 0.8896
7.250 0.8302 0.01492 0.00804 -0.0123 0.0189 0.9042
7.750 0.8716 0.01573 0.00900 -0.0101 0.0173 0.9414
8.000 0.8976 0.01635 0.00968 -0.0103 0.0166 0.9690
8.250 0.9220 0.01710 0.01049 -0.0104 0.0160 1.0000
8.500 0.9441 0.01767 0.01111 -0.0098 0.0155 1.0000
8.750 0.9652 0.01830 0.01181 -0.0091 0.0151 1.0000
9.000 0.9857 0.01899 0.01255 -0.0083 0.0147 1.0000
9.250 1.0055 0.01969 0.01331 -0.0075 0.0143 1.0000
9.500 1.0246 0.02044 0.01414 -0.0066 0.0140 1.0000
9.750 1.0429 0.02121 0.01497 -0.0056 0.0136 1.0000
10.000 1.0607 0.02199 0.01581 -0.0046 0.0134 1.0000
10.250 1.0768 0.02280 0.01668 -0.0033 0.0131 1.0000
10.500 1.0906 0.02364 0.01757 -0.0017 0.0128 1.0000
10.750 1.1017 0.02473 0.01873 0.0001 0.0126 1.0000
11.000 1.1119 0.02599 0.02010 0.0018 0.0123 1.0000
11.250 1.1240 0.02702 0.02124 0.0033 0.0121 1.0000
11.500 1.1354 0.02815 0.02250 0.0047 0.0119 1.0000
11.750 1.1451 0.02948 0.02396 0.0061 0.0117 1.0000
12.000 1.1538 0.03091 0.02554 0.0074 0.0115 1.0000
12.250 1.1614 0.03247 0.02723 0.0086 0.0114 1.0000
12.500 1.1673 0.03420 0.02912 0.0097 0.0112 1.0000
12.750 1.1730 0.03594 0.03099 0.0107 0.0109 1.0000
13.000 1.1762 0.03800 0.03320 0.0116 0.0108 1.0000
13.250 1.1788 0.04011 0.03547 0.0122 0.0106 1.0000
13.500 1.1807 0.04235 0.03785 0.0126 0.0105 1.0000
13.750 1.1821 0.04469 0.04031 0.0127 0.0103 1.0000
14.000 1.1821 0.04730 0.04304 0.0126 0.0102 1.0000
14.250 1.1814 0.05009 0.04595 0.0122 0.0100 1.0000
14.500 1.1796 0.05312 0.04909 0.0116 0.0099 1.0000
14.750 1.1723 0.05706 0.05319 0.0105 0.0099 1.0000
15.000 1.1710 0.06028 0.05648 0.0093 0.0097 1.0000
15.250 1.1579 0.06547 0.06186 0.0072 0.0097 1.0000
15.500 1.1493 0.07025 0.06676 0.0048 0.0096 1.0000
15.750 1.1336 0.07664 0.07331 0.0015 0.0095 1.0000
16.000 1.1151 0.08404 0.08090 -0.0028 0.0096 1.0000
16.250 1.0937 0.09273 0.08978 -0.0081 0.0095 1.0000
16.500 1.0510 0.10734 0.10469 -0.0174 0.0096 1.0000
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