NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 100,000 Max Cl/Cd: 31.73 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001064-il-100000-n5.txt Download as CSV file: xf-naca001064-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7444 0.08645 0.08112 -0.0258 1.0000 0.0330
-11.500 -0.7681 0.07778 0.07238 -0.0320 1.0000 0.0328
-11.250 -0.7927 0.07103 0.06550 -0.0359 1.0000 0.0326
-11.000 -0.8174 0.06564 0.05994 -0.0372 1.0000 0.0325
-10.750 -0.8415 0.06121 0.05530 -0.0361 1.0000 0.0325
-10.500 -0.8645 0.05741 0.05122 -0.0331 1.0000 0.0327
-10.250 -0.8831 0.05348 0.04688 -0.0298 1.0000 0.0331
-10.000 -0.8839 0.05067 0.04398 -0.0278 1.0000 0.0339
-9.750 -0.8777 0.04895 0.04218 -0.0261 1.0000 0.0351
-9.500 -0.8723 0.04692 0.03997 -0.0240 1.0000 0.0364
-9.250 -0.8690 0.04423 0.03697 -0.0215 1.0000 0.0375
-9.000 -0.8649 0.04128 0.03362 -0.0189 1.0000 0.0387
-8.750 -0.8579 0.03869 0.03057 -0.0162 1.0000 0.0405
-8.500 -0.8489 0.03647 0.02778 -0.0135 1.0000 0.0424
-8.250 -0.8353 0.03420 0.02535 -0.0117 1.0000 0.0439
-8.000 -0.8193 0.03261 0.02359 -0.0101 1.0000 0.0454
-7.750 -0.8027 0.03137 0.02219 -0.0085 1.0000 0.0476
-7.500 -0.7852 0.03003 0.02061 -0.0069 1.0000 0.0501
-7.250 -0.7660 0.02855 0.01884 -0.0053 1.0000 0.0520
-7.000 -0.7458 0.02727 0.01728 -0.0039 1.0000 0.0535
-6.750 -0.7264 0.02593 0.01597 -0.0027 1.0000 0.0560
-6.500 -0.7069 0.02500 0.01498 -0.0014 1.0000 0.0586
-6.250 -0.6867 0.02401 0.01389 -0.0001 1.0000 0.0607
-6.000 -0.6665 0.02307 0.01284 0.0013 1.0000 0.0628
-5.750 -0.6468 0.02223 0.01189 0.0029 1.0000 0.0650
-5.500 -0.6286 0.02134 0.01099 0.0045 1.0000 0.0676
-5.250 -0.6104 0.02067 0.01033 0.0061 1.0000 0.0719
-5.000 -0.5918 0.02006 0.00966 0.0077 1.0000 0.0769
-4.750 -0.5740 0.01936 0.00895 0.0095 1.0000 0.0818
-4.500 -0.5557 0.01874 0.00833 0.0112 1.0000 0.0891
-4.250 -0.5372 0.01812 0.00774 0.0128 1.0000 0.1000
-4.000 -0.5183 0.01754 0.00723 0.0142 1.0000 0.1187
-3.750 -0.4992 0.01694 0.00681 0.0156 1.0000 0.1521
-3.500 -0.4806 0.01624 0.00644 0.0169 1.0000 0.2133
-3.250 -0.4630 0.01534 0.00608 0.0183 1.0000 0.3177
-3.000 -0.4485 0.01413 0.00592 0.0206 1.0000 0.5178
-2.750 -0.4300 0.01362 0.00622 0.0233 1.0000 0.6942
-2.500 -0.4069 0.01370 0.00651 0.0253 1.0000 0.7785
-2.250 -0.3824 0.01386 0.00669 0.0266 1.0000 0.8220
-2.000 -0.3568 0.01410 0.00691 0.0277 1.0000 0.8599
-1.750 -0.3256 0.01445 0.00721 0.0278 1.0000 0.8944
-1.500 -0.2849 0.01491 0.00760 0.0259 0.9996 0.9253
-1.250 -0.2354 0.01536 0.00795 0.0220 0.9992 0.9490
-1.000 -0.1856 0.01556 0.00806 0.0174 0.9977 0.9603
-0.750 -0.1373 0.01565 0.00806 0.0127 0.9950 0.9659
-0.500 -0.0926 0.01570 0.00806 0.0087 0.9910 0.9726
-0.250 -0.0456 0.01572 0.00805 0.0042 0.9870 0.9774
0.000 0.0000 0.01574 0.00805 0.0000 0.9827 0.9827
0.250 0.0456 0.01572 0.00805 -0.0042 0.9774 0.9870
0.500 0.0926 0.01570 0.00805 -0.0087 0.9726 0.9910
0.750 0.1374 0.01565 0.00806 -0.0127 0.9659 0.9950
1.000 0.1857 0.01556 0.00805 -0.0174 0.9603 0.9977
1.250 0.2354 0.01536 0.00794 -0.0220 0.9491 0.9993
1.500 0.2849 0.01491 0.00760 -0.0259 0.9253 0.9996
1.750 0.3256 0.01445 0.00721 -0.0278 0.8944 1.0000
2.000 0.3568 0.01409 0.00691 -0.0277 0.8599 1.0000
2.250 0.3824 0.01386 0.00669 -0.0266 0.8220 1.0000
2.500 0.4069 0.01369 0.00651 -0.0253 0.7785 1.0000
2.750 0.4299 0.01362 0.00621 -0.0233 0.6938 1.0000
3.000 0.4484 0.01413 0.00591 -0.0205 0.5178 1.0000
3.250 0.4630 0.01533 0.00607 -0.0183 0.3181 1.0000
3.500 0.4805 0.01624 0.00643 -0.0169 0.2133 1.0000
3.750 0.4992 0.01693 0.00681 -0.0156 0.1522 1.0000
4.000 0.5182 0.01753 0.00723 -0.0142 0.1187 1.0000
4.250 0.5371 0.01812 0.00773 -0.0128 0.1001 1.0000
4.500 0.5556 0.01874 0.00833 -0.0111 0.0892 1.0000
4.750 0.5739 0.01936 0.00895 -0.0095 0.0818 1.0000
5.000 0.5917 0.02006 0.00965 -0.0077 0.0769 1.0000
5.250 0.6104 0.02067 0.01033 -0.0061 0.0719 1.0000
5.500 0.6286 0.02134 0.01098 -0.0045 0.0676 1.0000
5.750 0.6468 0.02223 0.01189 -0.0029 0.0650 1.0000
6.000 0.6665 0.02307 0.01284 -0.0013 0.0628 1.0000
6.250 0.6866 0.02401 0.01389 0.0001 0.0607 1.0000
6.500 0.7069 0.02500 0.01498 0.0014 0.0586 1.0000
6.750 0.7264 0.02593 0.01597 0.0027 0.0560 1.0000
7.000 0.7457 0.02727 0.01728 0.0039 0.0535 1.0000
7.250 0.7659 0.02855 0.01884 0.0053 0.0520 1.0000
7.500 0.7851 0.03003 0.02061 0.0069 0.0501 1.0000
7.750 0.8027 0.03137 0.02219 0.0085 0.0476 1.0000
8.000 0.8193 0.03261 0.02359 0.0101 0.0454 1.0000
8.250 0.8353 0.03420 0.02535 0.0117 0.0439 1.0000
8.500 0.8489 0.03647 0.02778 0.0135 0.0424 1.0000
8.750 0.8580 0.03869 0.03057 0.0162 0.0405 1.0000
9.000 0.8649 0.04128 0.03362 0.0188 0.0387 1.0000
9.250 0.8691 0.04423 0.03697 0.0215 0.0375 1.0000
9.500 0.8724 0.04693 0.03998 0.0240 0.0364 1.0000
9.750 0.8778 0.04897 0.04220 0.0260 0.0351 1.0000
10.000 0.8841 0.05068 0.04400 0.0278 0.0339 1.0000
10.250 0.8832 0.05350 0.04689 0.0298 0.0331 1.0000
10.500 0.8647 0.05743 0.05125 0.0330 0.0327 1.0000
10.750 0.8417 0.06125 0.05534 0.0361 0.0325 1.0000
11.000 0.8177 0.06570 0.06000 0.0371 0.0325 1.0000
11.250 0.7929 0.07111 0.06558 0.0357 0.0326 1.0000
11.500 0.7683 0.07791 0.07251 0.0318 0.0328 1.0000
11.750 0.7448 0.08661 0.08129 0.0255 0.0330 1.0000
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Polar data table (+)
Polar graphs
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