NACA 0010 (naca0010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.13 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0010-il-1000000-n5.txt Download as CSV file: xf-naca0010-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1723 0.11150 0.10900 0.0130 1.0000 0.0055
-17.500 -1.2382 0.09501 0.09230 0.0043 1.0000 0.0053
-17.250 -1.3086 0.07798 0.07503 -0.0052 1.0000 0.0052
-17.000 -1.3517 0.06616 0.06299 -0.0123 1.0000 0.0052
-16.750 -1.3792 0.05742 0.05407 -0.0178 1.0000 0.0051
-16.500 -1.3970 0.05074 0.04721 -0.0219 1.0000 0.0051
-16.250 -1.4084 0.04549 0.04181 -0.0249 1.0000 0.0052
-16.000 -1.4153 0.04137 0.03754 -0.0268 1.0000 0.0052
-15.750 -1.4191 0.03803 0.03406 -0.0278 1.0000 0.0053
-15.500 -1.4204 0.03533 0.03123 -0.0280 1.0000 0.0053
-15.250 -1.4204 0.03303 0.02881 -0.0275 1.0000 0.0054
-15.000 -1.4216 0.03086 0.02651 -0.0263 1.0000 0.0055
-14.750 -1.4194 0.02915 0.02468 -0.0246 1.0000 0.0057
-14.500 -1.4148 0.02774 0.02318 -0.0227 1.0000 0.0058
-14.250 -1.4082 0.02655 0.02190 -0.0206 1.0000 0.0060
-14.000 -1.3990 0.02552 0.02079 -0.0186 1.0000 0.0062
-13.750 -1.3856 0.02455 0.01973 -0.0171 1.0000 0.0064
-13.500 -1.3705 0.02365 0.01875 -0.0158 1.0000 0.0066
-13.250 -1.3540 0.02280 0.01781 -0.0147 1.0000 0.0068
-13.000 -1.3364 0.02200 0.01693 -0.0136 1.0000 0.0070
-12.750 -1.3177 0.02126 0.01609 -0.0126 1.0000 0.0072
-12.500 -1.2983 0.02056 0.01531 -0.0117 1.0000 0.0074
-12.250 -1.2794 0.01973 0.01441 -0.0107 1.0000 0.0078
-12.000 -1.2593 0.01901 0.01363 -0.0099 1.0000 0.0082
-11.750 -1.2383 0.01836 0.01293 -0.0091 1.0000 0.0087
-11.500 -1.2167 0.01776 0.01228 -0.0084 1.0000 0.0091
-11.250 -1.1944 0.01721 0.01166 -0.0077 1.0000 0.0096
-11.000 -1.1717 0.01671 0.01109 -0.0071 1.0000 0.0100
-10.750 -1.1494 0.01613 0.01048 -0.0064 1.0000 0.0109
-10.500 -1.1264 0.01562 0.00995 -0.0059 1.0000 0.0118
-10.250 -1.1029 0.01516 0.00945 -0.0053 1.0000 0.0127
-10.000 -1.0791 0.01474 0.00898 -0.0048 1.0000 0.0135
-9.750 -1.0553 0.01431 0.00855 -0.0042 1.0000 0.0149
-9.500 -1.0310 0.01394 0.00817 -0.0037 1.0000 0.0163
-9.250 -1.0065 0.01360 0.00780 -0.0033 1.0000 0.0174
-9.000 -0.9822 0.01325 0.00744 -0.0027 1.0000 0.0187
-8.750 -0.9576 0.01294 0.00714 -0.0023 1.0000 0.0202
-8.500 -0.9329 0.01267 0.00685 -0.0018 1.0000 0.0215
-8.250 -0.9082 0.01241 0.00655 -0.0012 1.0000 0.0224
-8.000 -0.8835 0.01217 0.00629 -0.0007 1.0000 0.0231
-7.750 -0.8596 0.01188 0.00596 0.0000 1.0000 0.0240
-7.500 -0.8361 0.01154 0.00562 0.0008 1.0000 0.0253
-7.250 -0.8124 0.01126 0.00533 0.0016 1.0000 0.0264
-7.000 -0.7886 0.01101 0.00507 0.0024 1.0000 0.0275
-6.750 -0.7648 0.01078 0.00483 0.0031 1.0000 0.0284
-6.500 -0.7396 0.01057 0.00459 0.0036 0.9997 0.0293
-6.250 -0.7073 0.01035 0.00435 0.0026 0.9978 0.0299
-6.000 -0.6748 0.01008 0.00406 0.0014 0.9957 0.0310
-5.750 -0.6420 0.00978 0.00376 0.0002 0.9938 0.0330
-5.500 -0.6105 0.00953 0.00352 -0.0006 0.9906 0.0347
-5.250 -0.5783 0.00930 0.00329 -0.0016 0.9873 0.0364
-5.000 -0.5457 0.00910 0.00308 -0.0027 0.9839 0.0381
-4.750 -0.5156 0.00888 0.00288 -0.0032 0.9780 0.0422
-4.500 -0.4841 0.00865 0.00268 -0.0041 0.9726 0.0487
-4.250 -0.4551 0.00836 0.00248 -0.0044 0.9642 0.0649
-4.000 -0.4262 0.00812 0.00230 -0.0046 0.9549 0.0802
-3.750 -0.3981 0.00791 0.00214 -0.0046 0.9436 0.0951
-3.500 -0.3712 0.00771 0.00198 -0.0043 0.9299 0.1121
-3.250 -0.3449 0.00751 0.00183 -0.0039 0.9137 0.1325
-3.000 -0.3186 0.00733 0.00169 -0.0035 0.8951 0.1554
-2.750 -0.2927 0.00716 0.00156 -0.0030 0.8739 0.1819
-2.500 -0.2666 0.00698 0.00143 -0.0026 0.8514 0.2137
-2.250 -0.2405 0.00682 0.00132 -0.0022 0.8268 0.2481
-2.000 -0.2141 0.00668 0.00122 -0.0019 0.8015 0.2808
-1.750 -0.1876 0.00657 0.00114 -0.0016 0.7755 0.3148
-1.500 -0.1613 0.00641 0.00106 -0.0012 0.7486 0.3621
-1.250 -0.1347 0.00629 0.00100 -0.0010 0.7206 0.4026
-1.000 -0.1079 0.00621 0.00096 -0.0008 0.6922 0.4407
-0.750 -0.0813 0.00612 0.00092 -0.0005 0.6628 0.4840
-0.500 -0.0543 0.00609 0.00090 -0.0003 0.6330 0.5157
-0.250 -0.0271 0.00608 0.00088 -0.0002 0.6032 0.5441
0.000 0.0000 0.00608 0.00088 0.0000 0.5725 0.5728
0.250 0.0271 0.00608 0.00088 0.0002 0.5437 0.6029
0.500 0.0543 0.00609 0.00090 0.0003 0.5153 0.6331
0.750 0.0813 0.00612 0.00092 0.0005 0.4835 0.6628
1.000 0.1080 0.00621 0.00096 0.0008 0.4405 0.6917
1.250 0.1348 0.00629 0.00100 0.0010 0.4026 0.7203
1.500 0.1614 0.00640 0.00106 0.0012 0.3645 0.7484
1.750 0.1876 0.00657 0.00114 0.0016 0.3145 0.7757
2.000 0.2141 0.00668 0.00122 0.0019 0.2808 0.8017
2.250 0.2405 0.00682 0.00132 0.0022 0.2475 0.8270
2.500 0.2666 0.00698 0.00143 0.0026 0.2135 0.8513
2.750 0.2926 0.00716 0.00156 0.0030 0.1816 0.8739
3.000 0.3187 0.00733 0.00169 0.0035 0.1554 0.8950
3.250 0.3449 0.00751 0.00183 0.0039 0.1328 0.9136
3.500 0.3712 0.00771 0.00198 0.0043 0.1121 0.9299
3.750 0.3981 0.00791 0.00214 0.0046 0.0951 0.9437
4.000 0.4262 0.00812 0.00230 0.0046 0.0802 0.9549
4.250 0.4551 0.00836 0.00248 0.0044 0.0650 0.9642
4.500 0.4841 0.00865 0.00268 0.0041 0.0487 0.9726
4.750 0.5157 0.00888 0.00288 0.0032 0.0422 0.9780
5.000 0.5458 0.00910 0.00308 0.0027 0.0380 0.9839
5.250 0.5783 0.00930 0.00329 0.0016 0.0363 0.9872
5.500 0.6105 0.00953 0.00352 0.0006 0.0347 0.9906
5.750 0.6420 0.00978 0.00376 -0.0002 0.0330 0.9938
6.000 0.6748 0.01008 0.00406 -0.0014 0.0310 0.9957
6.250 0.7073 0.01035 0.00435 -0.0025 0.0299 0.9978
6.500 0.7396 0.01057 0.00459 -0.0036 0.0293 0.9997
6.750 0.7648 0.01078 0.00483 -0.0032 0.0284 1.0000
7.000 0.7886 0.01101 0.00507 -0.0024 0.0275 1.0000
7.250 0.8124 0.01126 0.00533 -0.0016 0.0264 1.0000
7.500 0.8361 0.01154 0.00562 -0.0008 0.0253 1.0000
7.750 0.8596 0.01188 0.00596 0.0000 0.0239 1.0000
8.000 0.8835 0.01217 0.00629 0.0007 0.0231 1.0000
8.250 0.9082 0.01241 0.00655 0.0012 0.0224 1.0000
8.500 0.9329 0.01267 0.00685 0.0018 0.0215 1.0000
8.750 0.9576 0.01294 0.00714 0.0023 0.0202 1.0000
9.000 0.9822 0.01325 0.00744 0.0027 0.0187 1.0000
9.250 1.0065 0.01360 0.00780 0.0033 0.0174 1.0000
9.500 1.0310 0.01394 0.00817 0.0037 0.0163 1.0000
9.750 1.0553 0.01431 0.00855 0.0042 0.0149 1.0000
10.000 1.0791 0.01473 0.00898 0.0048 0.0135 1.0000
10.250 1.1029 0.01516 0.00945 0.0053 0.0127 1.0000
10.500 1.1264 0.01562 0.00994 0.0058 0.0118 1.0000
10.750 1.1494 0.01613 0.01048 0.0064 0.0109 1.0000
11.000 1.1718 0.01671 0.01109 0.0071 0.0100 1.0000
11.250 1.1945 0.01721 0.01166 0.0077 0.0096 1.0000
11.500 1.2167 0.01776 0.01228 0.0084 0.0091 1.0000
11.750 1.2384 0.01836 0.01293 0.0091 0.0087 1.0000
12.000 1.2593 0.01901 0.01363 0.0099 0.0082 1.0000
12.250 1.2794 0.01973 0.01441 0.0107 0.0078 1.0000
12.500 1.2983 0.02056 0.01531 0.0117 0.0074 1.0000
12.750 1.3178 0.02126 0.01609 0.0126 0.0072 1.0000
13.000 1.3365 0.02200 0.01692 0.0136 0.0070 1.0000
13.250 1.3541 0.02280 0.01781 0.0146 0.0068 1.0000
13.500 1.3707 0.02365 0.01875 0.0158 0.0066 1.0000
13.750 1.3859 0.02455 0.01973 0.0171 0.0064 1.0000
14.000 1.3993 0.02553 0.02079 0.0185 0.0062 1.0000
14.250 1.4086 0.02656 0.02190 0.0205 0.0060 1.0000
14.500 1.4154 0.02774 0.02318 0.0226 0.0058 1.0000
14.750 1.4202 0.02914 0.02467 0.0245 0.0057 1.0000
15.000 1.4223 0.03086 0.02652 0.0261 0.0055 1.0000
15.250 1.4214 0.03301 0.02879 0.0273 0.0054 1.0000
15.500 1.4215 0.03530 0.03121 0.0278 0.0053 1.0000
15.750 1.4206 0.03797 0.03401 0.0276 0.0053 1.0000
16.000 1.4169 0.04131 0.03748 0.0267 0.0052 1.0000
16.250 1.4099 0.04546 0.04177 0.0247 0.0052 1.0000
16.500 1.3988 0.05066 0.04713 0.0218 0.0051 1.0000
16.750 1.3814 0.05730 0.05395 0.0176 0.0051 1.0000
17.000 1.3536 0.06611 0.06295 0.0120 0.0051 1.0000
17.250 1.3111 0.07786 0.07491 0.0049 0.0052 1.0000
17.500 1.2406 0.09492 0.09221 -0.0046 0.0053 1.0000
17.750 1.1733 0.11168 0.10918 -0.0134 0.0055 1.0000
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