NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.5 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001064-il-1000000.txt Download as CSV file: xf-naca001064-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.1225 0.09487 0.09270 -0.0112 1.0000 0.0094
-16.750 -1.1644 0.08148 0.07912 -0.0188 1.0000 0.0092
-16.500 -1.1898 0.07143 0.06890 -0.0254 1.0000 0.0091
-16.250 -1.2122 0.06267 0.05997 -0.0314 1.0000 0.0090
-16.000 -1.2353 0.05494 0.05204 -0.0362 1.0000 0.0090
-15.750 -1.2589 0.04825 0.04514 -0.0395 1.0000 0.0091
-15.500 -1.2801 0.04285 0.03952 -0.0408 1.0000 0.0092
-15.250 -1.2964 0.03865 0.03513 -0.0406 1.0000 0.0093
-15.000 -1.3045 0.03568 0.03201 -0.0396 1.0000 0.0095
-14.750 -1.3057 0.03355 0.02976 -0.0382 1.0000 0.0097
-14.500 -1.3022 0.03193 0.02806 -0.0367 1.0000 0.0099
-14.250 -1.2966 0.03055 0.02658 -0.0351 1.0000 0.0101
-14.000 -1.2889 0.02938 0.02532 -0.0333 1.0000 0.0103
-13.750 -1.2811 0.02824 0.02409 -0.0314 1.0000 0.0105
-13.500 -1.2723 0.02721 0.02294 -0.0294 1.0000 0.0108
-13.250 -1.2630 0.02622 0.02185 -0.0272 1.0000 0.0110
-13.000 -1.2528 0.02530 0.02082 -0.0250 1.0000 0.0113
-12.750 -1.2400 0.02447 0.01988 -0.0230 1.0000 0.0115
-12.500 -1.2241 0.02374 0.01904 -0.0216 1.0000 0.0117
-12.250 -1.2160 0.02220 0.01734 -0.0191 1.0000 0.0122
-12.000 -1.2010 0.02131 0.01639 -0.0175 1.0000 0.0127
-11.750 -1.1818 0.02081 0.01584 -0.0163 1.0000 0.0131
-11.500 -1.1621 0.02036 0.01535 -0.0153 1.0000 0.0136
-11.250 -1.1424 0.01990 0.01485 -0.0141 1.0000 0.0141
-11.000 -1.1224 0.01950 0.01438 -0.0130 1.0000 0.0146
-10.750 -1.1020 0.01917 0.01398 -0.0118 1.0000 0.0150
-10.500 -1.0878 0.01823 0.01295 -0.0097 1.0000 0.0157
-10.250 -1.0709 0.01766 0.01234 -0.0079 1.0000 0.0163
-10.000 -1.0513 0.01739 0.01206 -0.0066 1.0000 0.0169
-9.750 -1.0320 0.01711 0.01176 -0.0051 1.0000 0.0175
-9.500 -1.0133 0.01681 0.01142 -0.0035 1.0000 0.0182
-9.250 -0.9946 0.01652 0.01108 -0.0018 1.0000 0.0188
-9.000 -0.9752 0.01635 0.01086 -0.0003 1.0000 0.0192
-8.750 -0.9623 0.01543 0.00986 0.0023 1.0000 0.0202
-8.500 -0.9444 0.01511 0.00954 0.0040 1.0000 0.0210
-8.250 -0.9255 0.01488 0.00931 0.0056 1.0000 0.0218
-8.000 -0.9067 0.01462 0.00902 0.0073 1.0000 0.0226
-7.750 -0.8805 0.01432 0.00867 0.0073 0.9994 0.0235
-7.500 -0.8486 0.01409 0.00841 0.0062 0.9983 0.0242
-7.250 -0.8193 0.01335 0.00760 0.0054 0.9970 0.0254
-7.000 -0.7889 0.01277 0.00701 0.0045 0.9958 0.0267
-6.750 -0.7567 0.01241 0.00664 0.0032 0.9947 0.0278
-6.500 -0.7245 0.01210 0.00631 0.0020 0.9937 0.0290
-6.250 -0.6943 0.01181 0.00600 0.0013 0.9917 0.0300
-6.000 -0.6630 0.01153 0.00569 0.0003 0.9898 0.0307
-5.750 -0.6323 0.01103 0.00514 -0.0006 0.9880 0.0318
-5.500 -0.6007 0.01053 0.00462 -0.0017 0.9865 0.0338
-5.250 -0.5676 0.01021 0.00429 -0.0030 0.9853 0.0352
-5.000 -0.5338 0.00992 0.00399 -0.0045 0.9843 0.0367
-4.750 -0.4993 0.00968 0.00374 -0.0061 0.9835 0.0382
-4.500 -0.4689 0.00943 0.00347 -0.0068 0.9809 0.0395
-4.250 -0.4385 0.00910 0.00315 -0.0075 0.9780 0.0436
-4.000 -0.4068 0.00885 0.00293 -0.0084 0.9755 0.0482
-3.750 -0.3755 0.00848 0.00269 -0.0093 0.9732 0.0715
-3.500 -0.3449 0.00809 0.00247 -0.0101 0.9708 0.1069
-3.250 -0.3199 0.00774 0.00229 -0.0097 0.9656 0.1494
-3.000 -0.2936 0.00737 0.00212 -0.0095 0.9607 0.2003
-2.750 -0.2674 0.00693 0.00193 -0.0093 0.9565 0.2663
-2.500 -0.2458 0.00639 0.00175 -0.0082 0.9497 0.3631
-2.250 -0.2237 0.00581 0.00157 -0.0071 0.9436 0.4735
-2.000 -0.2019 0.00531 0.00144 -0.0059 0.9370 0.5763
-1.750 -0.1796 0.00493 0.00136 -0.0047 0.9299 0.6579
-1.500 -0.1544 0.00474 0.00130 -0.0040 0.9236 0.7026
-1.250 -0.1291 0.00460 0.00126 -0.0034 0.9161 0.7359
-1.000 -0.1033 0.00448 0.00123 -0.0027 0.9092 0.7696
-0.750 -0.0776 0.00439 0.00122 -0.0021 0.9000 0.7972
-0.500 -0.0518 0.00433 0.00119 -0.0014 0.8881 0.8208
-0.250 -0.0258 0.00428 0.00117 -0.0007 0.8733 0.8386
0.000 0.0000 0.00427 0.00116 0.0000 0.8564 0.8562
0.250 0.0258 0.00428 0.00117 0.0007 0.8387 0.8733
0.500 0.0517 0.00433 0.00119 0.0014 0.8205 0.8882
0.750 0.0776 0.00438 0.00122 0.0021 0.7977 0.9000
1.000 0.1033 0.00448 0.00123 0.0027 0.7701 0.9092
1.250 0.1291 0.00460 0.00126 0.0034 0.7357 0.9161
1.500 0.1545 0.00474 0.00130 0.0040 0.7028 0.9236
1.750 0.1796 0.00493 0.00136 0.0047 0.6583 0.9299
2.000 0.2020 0.00530 0.00144 0.0059 0.5772 0.9369
2.250 0.2237 0.00581 0.00157 0.0071 0.4738 0.9436
2.500 0.2459 0.00638 0.00175 0.0082 0.3637 0.9496
2.750 0.2674 0.00693 0.00193 0.0093 0.2661 0.9565
3.000 0.2936 0.00737 0.00212 0.0095 0.2003 0.9607
3.250 0.3199 0.00774 0.00229 0.0097 0.1493 0.9656
3.500 0.3449 0.00809 0.00247 0.0101 0.1069 0.9708
3.750 0.3755 0.00848 0.00269 0.0093 0.0714 0.9732
4.000 0.4068 0.00885 0.00293 0.0084 0.0482 0.9755
4.250 0.4385 0.00910 0.00315 0.0075 0.0437 0.9780
4.500 0.4689 0.00943 0.00347 0.0068 0.0395 0.9809
4.750 0.4992 0.00968 0.00374 0.0062 0.0382 0.9835
5.000 0.5337 0.00992 0.00399 0.0045 0.0367 0.9843
5.250 0.5676 0.01020 0.00428 0.0030 0.0352 0.9853
5.500 0.6007 0.01053 0.00462 0.0017 0.0338 0.9865
5.750 0.6323 0.01102 0.00513 0.0006 0.0319 0.9880
6.000 0.6629 0.01153 0.00569 -0.0003 0.0307 0.9898
6.250 0.6943 0.01181 0.00600 -0.0013 0.0300 0.9917
6.500 0.7245 0.01209 0.00630 -0.0020 0.0289 0.9937
6.750 0.7568 0.01241 0.00664 -0.0032 0.0278 0.9947
7.000 0.7889 0.01277 0.00701 -0.0045 0.0267 0.9958
7.250 0.8193 0.01335 0.00760 -0.0054 0.0254 0.9970
7.500 0.8486 0.01409 0.00841 -0.0062 0.0242 0.9983
7.750 0.8805 0.01432 0.00867 -0.0073 0.0235 0.9994
8.000 0.9066 0.01462 0.00902 -0.0072 0.0226 1.0000
8.250 0.9254 0.01488 0.00931 -0.0056 0.0218 1.0000
8.500 0.9443 0.01511 0.00954 -0.0040 0.0210 1.0000
8.750 0.9622 0.01543 0.00986 -0.0023 0.0202 1.0000
9.000 0.9751 0.01635 0.01086 0.0003 0.0192 1.0000
9.250 0.9946 0.01652 0.01108 0.0019 0.0188 1.0000
9.500 1.0133 0.01681 0.01142 0.0035 0.0182 1.0000
9.750 1.0320 0.01711 0.01176 0.0051 0.0175 1.0000
10.000 1.0512 0.01739 0.01206 0.0066 0.0169 1.0000
10.250 1.0708 0.01766 0.01235 0.0079 0.0163 1.0000
10.500 1.0878 0.01823 0.01295 0.0097 0.0157 1.0000
10.750 1.1021 0.01915 0.01397 0.0118 0.0150 1.0000
11.000 1.1225 0.01948 0.01436 0.0130 0.0146 1.0000
11.250 1.1425 0.01990 0.01484 0.0141 0.0141 1.0000
11.500 1.1622 0.02036 0.01535 0.0152 0.0136 1.0000
11.750 1.1820 0.02080 0.01584 0.0163 0.0131 1.0000
12.000 1.2011 0.02131 0.01639 0.0174 0.0127 1.0000
12.250 1.2163 0.02219 0.01734 0.0190 0.0122 1.0000
12.500 1.2244 0.02374 0.01905 0.0215 0.0117 1.0000
12.750 1.2404 0.02447 0.01988 0.0230 0.0115 1.0000
13.000 1.2533 0.02530 0.02081 0.0249 0.0113 1.0000
13.250 1.2635 0.02622 0.02185 0.0271 0.0110 1.0000
13.500 1.2729 0.02720 0.02294 0.0292 0.0108 1.0000
13.750 1.2819 0.02824 0.02408 0.0313 0.0105 1.0000
14.000 1.2900 0.02935 0.02529 0.0332 0.0103 1.0000
14.250 1.2972 0.03057 0.02660 0.0349 0.0101 1.0000
14.500 1.3032 0.03192 0.02804 0.0365 0.0099 1.0000
14.750 1.3066 0.03355 0.02977 0.0381 0.0097 1.0000
15.000 1.3053 0.03570 0.03203 0.0394 0.0095 1.0000
15.250 1.2969 0.03872 0.03520 0.0404 0.0093 1.0000
15.500 1.2810 0.04288 0.03955 0.0406 0.0092 1.0000
15.750 1.2599 0.04829 0.04519 0.0392 0.0091 1.0000
16.000 1.2362 0.05503 0.05214 0.0359 0.0090 1.0000
16.250 1.2140 0.06264 0.05994 0.0311 0.0090 1.0000
16.500 1.1909 0.07157 0.06905 0.0249 0.0091 1.0000
16.750 1.1649 0.08180 0.07945 0.0183 0.0092 1.0000
17.000 1.1227 0.09525 0.09309 0.0106 0.0094 1.0000
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