NACA 0010 (naca0010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010 (naca0010-il) Reynolds number: 500,000 Max Cl/Cd: 57.81 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0010-il-500000-n5.txt Download as CSV file: xf-naca0010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0427 0.12024 0.11753 0.0178 1.0000 0.0088
-16.500 -1.0976 0.10476 0.10188 0.0097 1.0000 0.0086
-16.250 -1.1470 0.09107 0.08801 0.0023 1.0000 0.0084
-16.000 -1.1881 0.07916 0.07590 -0.0044 1.0000 0.0082
-15.750 -1.2206 0.06892 0.06547 -0.0106 1.0000 0.0081
-15.500 -1.2444 0.06048 0.05683 -0.0161 1.0000 0.0081
-15.250 -1.2616 0.05357 0.04973 -0.0206 1.0000 0.0082
-15.000 -1.2731 0.04808 0.04407 -0.0240 1.0000 0.0082
-14.750 -1.2810 0.04366 0.03948 -0.0262 1.0000 0.0083
-14.500 -1.2855 0.04014 0.03581 -0.0274 1.0000 0.0085
-14.250 -1.2878 0.03728 0.03279 -0.0277 1.0000 0.0086
-14.000 -1.2880 0.03492 0.03028 -0.0272 1.0000 0.0088
-13.750 -1.2866 0.03293 0.02815 -0.0261 1.0000 0.0090
-13.500 -1.2833 0.03126 0.02633 -0.0245 1.0000 0.0092
-13.250 -1.2784 0.02981 0.02473 -0.0226 1.0000 0.0094
-13.000 -1.2715 0.02855 0.02333 -0.0205 1.0000 0.0097
-12.750 -1.2605 0.02741 0.02205 -0.0188 1.0000 0.0099
-12.500 -1.2493 0.02612 0.02065 -0.0172 1.0000 0.0104
-12.250 -1.2343 0.02509 0.01954 -0.0160 1.0000 0.0109
-12.000 -1.2173 0.02420 0.01858 -0.0149 1.0000 0.0115
-11.750 -1.1994 0.02336 0.01764 -0.0139 1.0000 0.0121
-11.500 -1.1808 0.02254 0.01670 -0.0129 1.0000 0.0127
-11.250 -1.1616 0.02174 0.01577 -0.0119 1.0000 0.0132
-11.000 -1.1423 0.02091 0.01488 -0.0110 1.0000 0.0140
-10.750 -1.1210 0.02028 0.01421 -0.0103 1.0000 0.0149
-10.500 -1.0990 0.01973 0.01361 -0.0096 1.0000 0.0159
-10.250 -1.0767 0.01919 0.01299 -0.0089 1.0000 0.0170
-10.000 -1.0545 0.01862 0.01234 -0.0082 1.0000 0.0180
-9.750 -1.0318 0.01811 0.01180 -0.0076 1.0000 0.0192
-9.500 -1.0083 0.01769 0.01134 -0.0071 1.0000 0.0205
-9.250 -0.9848 0.01725 0.01084 -0.0065 1.0000 0.0218
-9.000 -0.9608 0.01688 0.01039 -0.0060 1.0000 0.0229
-8.750 -0.9380 0.01635 0.00981 -0.0053 1.0000 0.0240
-8.500 -0.9150 0.01584 0.00926 -0.0046 1.0000 0.0254
-8.250 -0.8913 0.01543 0.00883 -0.0040 1.0000 0.0267
-8.000 -0.8675 0.01506 0.00841 -0.0034 1.0000 0.0280
-7.750 -0.8435 0.01471 0.00800 -0.0027 1.0000 0.0292
-7.500 -0.8195 0.01439 0.00763 -0.0021 1.0000 0.0300
-7.250 -0.7972 0.01385 0.00705 -0.0012 1.0000 0.0315
-7.000 -0.7744 0.01341 0.00659 -0.0003 1.0000 0.0330
-6.750 -0.7513 0.01305 0.00621 0.0005 1.0000 0.0345
-6.500 -0.7280 0.01273 0.00586 0.0014 1.0000 0.0359
-6.250 -0.7046 0.01242 0.00551 0.0022 1.0000 0.0371
-6.000 -0.6812 0.01214 0.00519 0.0030 1.0000 0.0382
-5.750 -0.6582 0.01180 0.00483 0.0040 1.0000 0.0400
-5.500 -0.6352 0.01148 0.00451 0.0049 1.0000 0.0424
-5.250 -0.6121 0.01121 0.00424 0.0058 1.0000 0.0452
-5.000 -0.5834 0.01095 0.00397 0.0055 0.9986 0.0491
-4.750 -0.5495 0.01062 0.00369 0.0040 0.9957 0.0594
-4.500 -0.5162 0.01026 0.00343 0.0026 0.9925 0.0765
-4.250 -0.4831 0.00994 0.00318 0.0013 0.9886 0.0953
-4.000 -0.4488 0.00962 0.00296 -0.0002 0.9853 0.1173
-3.750 -0.4169 0.00931 0.00276 -0.0012 0.9800 0.1429
-3.500 -0.3841 0.00899 0.00256 -0.0024 0.9747 0.1722
-3.250 -0.3533 0.00869 0.00239 -0.0032 0.9673 0.2033
-3.000 -0.3212 0.00837 0.00222 -0.0042 0.9602 0.2419
-2.750 -0.2920 0.00803 0.00208 -0.0046 0.9499 0.2895
-2.500 -0.2631 0.00770 0.00194 -0.0048 0.9384 0.3398
-2.250 -0.2348 0.00742 0.00182 -0.0049 0.9246 0.3849
-2.000 -0.2075 0.00718 0.00171 -0.0047 0.9082 0.4282
-1.750 -0.1810 0.00699 0.00162 -0.0043 0.8895 0.4653
-1.500 -0.1550 0.00681 0.00153 -0.0037 0.8687 0.5057
-1.250 -0.1293 0.00665 0.00146 -0.0031 0.8455 0.5472
-0.750 -0.0775 0.00649 0.00135 -0.0018 0.7945 0.6116
-0.500 -0.0517 0.00644 0.00131 -0.0012 0.7661 0.6436
-0.250 -0.0258 0.00641 0.00129 -0.0006 0.7368 0.6754
0.000 0.0000 0.00640 0.00129 0.0000 0.7063 0.7064
0.250 0.0259 0.00641 0.00129 0.0006 0.6753 0.7366
0.500 0.0517 0.00644 0.00131 0.0012 0.6434 0.7662
0.750 0.0775 0.00650 0.00135 0.0018 0.6114 0.7944
1.250 0.1293 0.00665 0.00146 0.0031 0.5474 0.8455
1.500 0.1550 0.00681 0.00153 0.0037 0.5059 0.8687
1.750 0.1810 0.00699 0.00162 0.0043 0.4652 0.8893
2.000 0.2075 0.00718 0.00171 0.0047 0.4278 0.9082
2.250 0.2348 0.00742 0.00182 0.0049 0.3851 0.9246
2.500 0.2631 0.00770 0.00194 0.0048 0.3396 0.9383
2.750 0.2920 0.00803 0.00208 0.0046 0.2895 0.9499
3.000 0.3211 0.00837 0.00222 0.0042 0.2419 0.9603
3.250 0.3533 0.00869 0.00239 0.0032 0.2035 0.9673
3.500 0.3841 0.00899 0.00256 0.0024 0.1722 0.9747
3.750 0.4169 0.00930 0.00276 0.0012 0.1429 0.9800
4.000 0.4488 0.00961 0.00296 0.0002 0.1174 0.9853
4.250 0.4831 0.00994 0.00318 -0.0014 0.0954 0.9886
4.500 0.5162 0.01026 0.00343 -0.0026 0.0765 0.9925
4.750 0.5496 0.01061 0.00369 -0.0040 0.0594 0.9957
5.000 0.5834 0.01095 0.00397 -0.0055 0.0491 0.9986
5.250 0.6121 0.01121 0.00424 -0.0058 0.0452 1.0000
5.500 0.6352 0.01148 0.00451 -0.0049 0.0425 1.0000
5.750 0.6582 0.01180 0.00483 -0.0040 0.0400 1.0000
6.000 0.6812 0.01214 0.00519 -0.0030 0.0382 1.0000
6.250 0.7046 0.01242 0.00551 -0.0022 0.0371 1.0000
6.500 0.7280 0.01273 0.00586 -0.0013 0.0359 1.0000
6.750 0.7512 0.01305 0.00621 -0.0005 0.0345 1.0000
7.000 0.7744 0.01341 0.00659 0.0003 0.0330 1.0000
7.250 0.7972 0.01385 0.00705 0.0012 0.0315 1.0000
7.500 0.8195 0.01439 0.00763 0.0021 0.0300 1.0000
7.750 0.8435 0.01471 0.00800 0.0027 0.0292 1.0000
8.000 0.8675 0.01506 0.00841 0.0034 0.0280 1.0000
8.250 0.8913 0.01543 0.00883 0.0040 0.0267 1.0000
8.500 0.9151 0.01583 0.00926 0.0046 0.0254 1.0000
8.750 0.9380 0.01635 0.00980 0.0053 0.0240 1.0000
9.000 0.9609 0.01687 0.01038 0.0060 0.0229 1.0000
9.250 0.9848 0.01725 0.01084 0.0065 0.0218 1.0000
9.500 1.0083 0.01769 0.01134 0.0071 0.0205 1.0000
9.750 1.0318 0.01811 0.01180 0.0076 0.0192 1.0000
10.000 1.0545 0.01862 0.01234 0.0082 0.0180 1.0000
10.250 1.0767 0.01919 0.01299 0.0089 0.0170 1.0000
10.500 1.0990 0.01973 0.01361 0.0096 0.0159 1.0000
10.750 1.1211 0.02028 0.01421 0.0103 0.0149 1.0000
11.000 1.1423 0.02091 0.01488 0.0110 0.0140 1.0000
11.250 1.1616 0.02174 0.01577 0.0119 0.0132 1.0000
11.500 1.1809 0.02254 0.01670 0.0129 0.0127 1.0000
11.750 1.1995 0.02336 0.01764 0.0139 0.0120 1.0000
12.000 1.2175 0.02420 0.01857 0.0149 0.0115 1.0000
12.250 1.2346 0.02509 0.01954 0.0159 0.0109 1.0000
12.500 1.2496 0.02612 0.02065 0.0172 0.0104 1.0000
12.750 1.2609 0.02741 0.02205 0.0187 0.0099 1.0000
13.000 1.2719 0.02855 0.02333 0.0204 0.0097 1.0000
13.250 1.2789 0.02981 0.02473 0.0225 0.0094 1.0000
13.500 1.2839 0.03126 0.02633 0.0244 0.0092 1.0000
13.750 1.2872 0.03294 0.02815 0.0260 0.0090 1.0000
14.000 1.2888 0.03491 0.03027 0.0271 0.0088 1.0000
14.250 1.2886 0.03726 0.03277 0.0275 0.0086 1.0000
14.500 1.2865 0.04012 0.03579 0.0273 0.0085 1.0000
14.750 1.2820 0.04365 0.03947 0.0261 0.0083 1.0000
15.000 1.2744 0.04805 0.04403 0.0238 0.0082 1.0000
15.250 1.2628 0.05356 0.04972 0.0204 0.0082 1.0000
15.500 1.2460 0.06043 0.05678 0.0159 0.0081 1.0000
15.750 1.2223 0.06887 0.06541 0.0104 0.0081 1.0000
16.000 1.1898 0.07913 0.07587 0.0042 0.0082 1.0000
16.250 1.1483 0.09115 0.08809 -0.0026 0.0084 1.0000
16.500 1.0990 0.10483 0.10196 -0.0100 0.0086 1.0000
16.750 1.0437 0.12041 0.11770 -0.0182 0.0088 1.0000
17.000 0.9647 0.14290 0.14040 -0.0300 0.0092 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010 (naca0010-il)