NACA 64-110 AIRFOIL (n64110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-110 AIRFOIL (n64110-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.15 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64110-il-1000000-n5.txt Download as CSV file: xf-n64110-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-110 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1001 0.06646 0.06441 -0.0235 1.0000 0.0042
-15.250 -1.1346 0.05664 0.05438 -0.0302 1.0000 0.0042
-15.000 -1.1592 0.04973 0.04729 -0.0341 1.0000 0.0042
-14.750 -1.1725 0.04509 0.04249 -0.0361 1.0000 0.0042
-14.500 -1.1735 0.04231 0.03963 -0.0370 1.0000 0.0043
-14.250 -1.1887 0.03820 0.03531 -0.0375 1.0000 0.0043
-14.000 -1.1957 0.03532 0.03227 -0.0372 1.0000 0.0043
-13.750 -1.1910 0.03374 0.03061 -0.0365 1.0000 0.0045
-13.500 -1.1928 0.03174 0.02848 -0.0352 1.0000 0.0045
-13.250 -1.1909 0.03023 0.02685 -0.0335 1.0000 0.0046
-13.000 -1.1889 0.02886 0.02536 -0.0312 1.0000 0.0047
-12.750 -1.1817 0.02755 0.02392 -0.0294 1.0000 0.0048
-12.500 -1.1700 0.02631 0.02254 -0.0281 1.0000 0.0050
-12.250 -1.1560 0.02516 0.02126 -0.0270 1.0000 0.0051
-12.000 -1.1399 0.02415 0.02013 -0.0261 1.0000 0.0053
-11.750 -1.1241 0.02297 0.01881 -0.0252 1.0000 0.0054
-11.500 -1.1059 0.02201 0.01772 -0.0244 1.0000 0.0056
-11.250 -1.0867 0.02112 0.01671 -0.0237 1.0000 0.0057
-11.000 -1.0673 0.02017 0.01565 -0.0230 1.0000 0.0058
-10.750 -1.0476 0.01922 0.01459 -0.0223 1.0000 0.0061
-10.500 -1.0249 0.01870 0.01404 -0.0220 1.0000 0.0064
-10.250 -1.0016 0.01823 0.01352 -0.0217 1.0000 0.0067
-10.000 -0.9782 0.01775 0.01298 -0.0213 1.0000 0.0069
-9.750 -0.9549 0.01722 0.01240 -0.0210 1.0000 0.0073
-9.500 -0.9315 0.01666 0.01177 -0.0206 1.0000 0.0076
-9.250 -0.9081 0.01608 0.01111 -0.0202 1.0000 0.0079
-9.000 -0.8844 0.01553 0.01049 -0.0199 1.0000 0.0082
-8.750 -0.8603 0.01502 0.00991 -0.0195 1.0000 0.0083
-8.500 -0.8360 0.01457 0.00938 -0.0192 1.0000 0.0085
-8.250 -0.8053 0.01360 0.00832 -0.0206 0.9786 0.0091
-7.750 -0.7442 0.01287 0.00751 -0.0225 0.9463 0.0101
-7.500 -0.7192 0.01253 0.00710 -0.0221 0.9302 0.0106
-7.250 -0.6949 0.01217 0.00664 -0.0216 0.9156 0.0110
-7.000 -0.6704 0.01182 0.00620 -0.0211 0.9022 0.0113
-6.750 -0.6454 0.01150 0.00580 -0.0207 0.8896 0.0117
-6.250 -0.5947 0.01085 0.00498 -0.0200 0.8659 0.0124
-6.000 -0.5692 0.01044 0.00447 -0.0197 0.8550 0.0131
-5.750 -0.5432 0.01014 0.00412 -0.0195 0.8446 0.0137
-5.250 -0.4900 0.00966 0.00353 -0.0192 0.8242 0.0152
-5.000 -0.4631 0.00946 0.00327 -0.0192 0.8149 0.0161
-4.500 -0.4089 0.00903 0.00275 -0.0191 0.7963 0.0189
-4.250 -0.3816 0.00884 0.00254 -0.0191 0.7876 0.0213
-4.000 -0.3541 0.00869 0.00235 -0.0191 0.7781 0.0234
-3.750 -0.3265 0.00855 0.00216 -0.0191 0.7690 0.0256
-3.500 -0.2990 0.00839 0.00199 -0.0191 0.7602 0.0300
-3.250 -0.2712 0.00826 0.00184 -0.0192 0.7514 0.0335
-3.000 -0.2435 0.00811 0.00168 -0.0192 0.7432 0.0421
-2.750 -0.2161 0.00789 0.00153 -0.0193 0.7346 0.0659
-2.500 -0.1891 0.00751 0.00136 -0.0194 0.7262 0.1263
-2.250 -0.1624 0.00709 0.00118 -0.0195 0.7175 0.2061
-2.000 -0.1361 0.00650 0.00097 -0.0196 0.7089 0.3235
-1.750 -0.1096 0.00600 0.00083 -0.0198 0.7011 0.4335
-1.500 -0.0819 0.00579 0.00077 -0.0199 0.6932 0.4875
-1.250 -0.0544 0.00560 0.00074 -0.0199 0.6860 0.5449
-1.000 -0.0267 0.00544 0.00073 -0.0200 0.6783 0.5928
-0.750 0.0015 0.00538 0.00072 -0.0201 0.6709 0.6188
-0.500 0.0299 0.00537 0.00071 -0.0202 0.6629 0.6302
-0.250 0.0583 0.00536 0.00071 -0.0203 0.6557 0.6398
0.000 0.0869 0.00537 0.00071 -0.0205 0.6484 0.6474
0.250 0.1154 0.00537 0.00071 -0.0206 0.6416 0.6547
0.500 0.1438 0.00539 0.00073 -0.0207 0.6327 0.6621
0.750 0.1722 0.00541 0.00075 -0.0209 0.6226 0.6704
1.000 0.2004 0.00545 0.00077 -0.0209 0.6068 0.6782
1.250 0.2283 0.00554 0.00080 -0.0210 0.5821 0.6863
1.500 0.2556 0.00569 0.00084 -0.0209 0.5444 0.6938
1.750 0.2830 0.00587 0.00089 -0.0209 0.5018 0.7020
2.000 0.3098 0.00613 0.00098 -0.0209 0.4454 0.7100
2.500 0.3597 0.00735 0.00142 -0.0206 0.2277 0.7277
2.750 0.3850 0.00792 0.00167 -0.0204 0.1363 0.7363
3.000 0.4113 0.00831 0.00189 -0.0204 0.0823 0.7452
3.250 0.4379 0.00861 0.00208 -0.0203 0.0501 0.7536
3.750 0.4924 0.00898 0.00243 -0.0203 0.0324 0.7718
4.000 0.5194 0.00917 0.00264 -0.0202 0.0272 0.7811
4.250 0.5467 0.00932 0.00283 -0.0202 0.0248 0.7908
4.500 0.5737 0.00949 0.00303 -0.0201 0.0220 0.8002
4.750 0.6003 0.00973 0.00328 -0.0200 0.0185 0.8095
5.000 0.6271 0.00992 0.00353 -0.0199 0.0172 0.8198
5.250 0.6536 0.01013 0.00378 -0.0197 0.0158 0.8299
5.500 0.6798 0.01038 0.00406 -0.0195 0.0145 0.8403
5.750 0.7055 0.01069 0.00442 -0.0192 0.0133 0.8513
6.000 0.7309 0.01100 0.00482 -0.0189 0.0128 0.8632
6.250 0.7562 0.01128 0.00517 -0.0185 0.0124 0.8755
6.500 0.7810 0.01157 0.00554 -0.0180 0.0120 0.8888
6.750 0.8054 0.01186 0.00591 -0.0175 0.0116 0.9028
7.000 0.8292 0.01218 0.00631 -0.0168 0.0111 0.9182
7.250 0.8523 0.01251 0.00671 -0.0160 0.0107 0.9354
7.500 0.8757 0.01285 0.00713 -0.0153 0.0104 0.9578
7.750 0.9059 0.01334 0.00767 -0.0162 0.0100 1.0000
8.000 0.9297 0.01392 0.00830 -0.0158 0.0095 1.0000
8.250 0.9519 0.01474 0.00920 -0.0152 0.0090 1.0000
8.500 0.9760 0.01524 0.00977 -0.0149 0.0089 1.0000
8.750 1.0000 0.01575 0.01033 -0.0145 0.0088 1.0000
9.000 1.0234 0.01631 0.01096 -0.0141 0.0086 1.0000
9.250 1.0465 0.01689 0.01161 -0.0136 0.0083 1.0000
9.500 1.0693 0.01749 0.01228 -0.0131 0.0081 1.0000
9.750 1.0922 0.01802 0.01287 -0.0127 0.0078 1.0000
10.000 1.1151 0.01851 0.01343 -0.0122 0.0074 1.0000
10.250 1.1374 0.01906 0.01403 -0.0117 0.0072 1.0000
10.500 1.1595 0.01959 0.01461 -0.0112 0.0069 1.0000
10.750 1.1807 0.02019 0.01525 -0.0106 0.0067 1.0000
11.000 1.1998 0.02103 0.01617 -0.0098 0.0064 1.0000
11.250 1.2149 0.02230 0.01757 -0.0085 0.0061 1.0000
11.500 1.2332 0.02309 0.01846 -0.0076 0.0061 1.0000
11.750 1.2509 0.02387 0.01934 -0.0066 0.0059 1.0000
12.000 1.2661 0.02486 0.02046 -0.0053 0.0058 1.0000
12.250 1.2789 0.02593 0.02166 -0.0038 0.0057 1.0000
12.500 1.2894 0.02684 0.02267 -0.0019 0.0055 1.0000
12.750 1.2959 0.02799 0.02394 0.0004 0.0054 1.0000
13.000 1.3028 0.02913 0.02519 0.0023 0.0052 1.0000
13.250 1.3098 0.03032 0.02647 0.0040 0.0051 1.0000
13.500 1.3142 0.03179 0.02806 0.0056 0.0050 1.0000
13.750 1.3205 0.03318 0.02954 0.0067 0.0048 1.0000
14.000 1.3240 0.03490 0.03137 0.0078 0.0048 1.0000
14.250 1.3254 0.03694 0.03352 0.0086 0.0047 1.0000
14.500 1.3380 0.03790 0.03449 0.0089 0.0045 1.0000
14.750 1.3342 0.04067 0.03741 0.0093 0.0044 1.0000
15.000 1.3342 0.04319 0.04003 0.0093 0.0044 1.0000
15.250 1.3334 0.04595 0.04289 0.0089 0.0042 1.0000
15.500 1.3222 0.05020 0.04730 0.0079 0.0042 1.0000
15.750 1.3118 0.05466 0.05190 0.0063 0.0041 1.0000
16.000 1.2928 0.06074 0.05816 0.0035 0.0041 1.0000
16.250 1.2722 0.06768 0.06527 -0.0002 0.0041 1.0000
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