NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 1,000,000 Max Cl/Cd: 49.65 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034-il-1000000.txt Download as CSV file: xf-naca001034-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6799 0.08213 0.08059 -0.0229 1.0000 0.0068
-10.500 -0.6942 0.07141 0.06976 -0.0317 1.0000 0.0066
-10.250 -0.7066 0.06573 0.06398 -0.0352 1.0000 0.0066
-10.000 -0.7233 0.06097 0.05910 -0.0366 1.0000 0.0066
-9.750 -0.7422 0.05689 0.05489 -0.0357 1.0000 0.0066
-9.500 -0.7668 0.05299 0.05085 -0.0321 1.0000 0.0066
-9.250 -0.7845 0.04890 0.04657 -0.0287 1.0000 0.0067
-9.000 -0.7937 0.04574 0.04324 -0.0254 1.0000 0.0069
-8.750 -0.7954 0.04372 0.04110 -0.0223 1.0000 0.0071
-8.500 -0.7935 0.04223 0.03952 -0.0194 1.0000 0.0073
-8.250 -0.7910 0.04082 0.03801 -0.0162 1.0000 0.0076
-8.000 -0.7889 0.03917 0.03624 -0.0126 1.0000 0.0081
-7.250 -0.7826 0.02276 0.01828 0.0011 0.9976 0.0068
-7.000 -0.7569 0.02047 0.01573 0.0008 0.9963 0.0071
-6.750 -0.7261 0.02046 0.01574 -0.0009 0.9951 0.0078
-6.500 -0.7008 0.01648 0.01131 0.0000 0.9944 0.0072
-6.250 -0.6741 0.01500 0.00967 0.0000 0.9926 0.0074
-6.000 -0.6455 0.01410 0.00870 -0.0005 0.9906 0.0079
-5.750 -0.6154 0.01339 0.00793 -0.0014 0.9887 0.0087
-5.500 -0.5849 0.01266 0.00714 -0.0023 0.9870 0.0095
-5.250 -0.5535 0.01201 0.00643 -0.0033 0.9856 0.0100
-5.000 -0.5209 0.01152 0.00587 -0.0047 0.9844 0.0105
-4.750 -0.4913 0.01031 0.00452 -0.0055 0.9832 0.0122
-4.500 -0.4592 0.00988 0.00406 -0.0067 0.9816 0.0142
-4.250 -0.4312 0.00954 0.00368 -0.0069 0.9778 0.0159
-4.000 -0.4003 0.00925 0.00337 -0.0078 0.9749 0.0172
-3.750 -0.3697 0.00878 0.00284 -0.0085 0.9722 0.0255
-3.500 -0.3415 0.00810 0.00244 -0.0090 0.9694 0.0966
-3.250 -0.3236 0.00706 0.00206 -0.0075 0.9624 0.2638
-3.000 -0.3014 0.00630 0.00180 -0.0068 0.9572 0.3956
-2.750 -0.2802 0.00570 0.00161 -0.0056 0.9508 0.5059
-2.500 -0.2587 0.00521 0.00144 -0.0044 0.9442 0.6022
-2.250 -0.2368 0.00484 0.00135 -0.0032 0.9372 0.6826
-2.000 -0.2131 0.00462 0.00128 -0.0022 0.9300 0.7359
-1.750 -0.1878 0.00450 0.00123 -0.0016 0.9226 0.7656
-1.500 -0.1619 0.00441 0.00118 -0.0011 0.9156 0.7916
-1.250 -0.1351 0.00436 0.00114 -0.0009 0.9080 0.8053
-1.000 -0.1081 0.00432 0.00110 -0.0007 0.9008 0.8191
-0.750 -0.0814 0.00428 0.00108 -0.0005 0.8922 0.8329
-0.500 -0.0543 0.00426 0.00106 -0.0003 0.8842 0.8455
-0.250 -0.0272 0.00424 0.00105 -0.0001 0.8752 0.8561
0.000 0.0000 0.00423 0.00105 0.0000 0.8659 0.8658
0.250 0.0273 0.00424 0.00105 0.0001 0.8562 0.8752
0.500 0.0543 0.00426 0.00106 0.0003 0.8454 0.8842
0.750 0.0814 0.00428 0.00108 0.0005 0.8330 0.8922
1.000 0.1082 0.00432 0.00110 0.0007 0.8191 0.9008
1.250 0.1352 0.00436 0.00114 0.0009 0.8053 0.9079
1.500 0.1620 0.00441 0.00118 0.0011 0.7916 0.9156
1.750 0.1880 0.00449 0.00123 0.0016 0.7669 0.9226
2.000 0.2132 0.00462 0.00128 0.0022 0.7358 0.9300
2.250 0.2370 0.00483 0.00135 0.0031 0.6845 0.9371
2.500 0.2587 0.00521 0.00144 0.0044 0.6014 0.9442
2.750 0.2802 0.00571 0.00161 0.0056 0.5054 0.9508
3.000 0.3014 0.00630 0.00180 0.0067 0.3958 0.9572
3.250 0.3236 0.00707 0.00206 0.0075 0.2636 0.9624
3.500 0.3415 0.00810 0.00244 0.0090 0.0967 0.9694
3.750 0.3697 0.00878 0.00284 0.0085 0.0256 0.9722
4.000 0.4002 0.00926 0.00337 0.0078 0.0172 0.9749
4.250 0.4312 0.00953 0.00368 0.0069 0.0159 0.9777
4.500 0.4593 0.00987 0.00405 0.0067 0.0142 0.9816
4.750 0.4912 0.01032 0.00453 0.0055 0.0123 0.9832
5.000 0.5207 0.01153 0.00588 0.0047 0.0105 0.9844
5.250 0.5534 0.01203 0.00645 0.0034 0.0101 0.9856
5.500 0.5848 0.01268 0.00715 0.0023 0.0095 0.9870
5.750 0.6154 0.01338 0.00792 0.0013 0.0087 0.9887
6.000 0.6453 0.01411 0.00871 0.0006 0.0080 0.9906
6.250 0.6739 0.01502 0.00969 0.0001 0.0075 0.9926
6.500 0.7007 0.01649 0.01132 0.0000 0.0073 0.9944
6.750 0.7277 0.01945 0.01460 0.0002 0.0075 0.9951
7.000 0.7571 0.02041 0.01567 -0.0009 0.0070 0.9963
7.250 0.7828 0.02278 0.01830 -0.0011 0.0068 0.9977
9.250 0.7204 0.03934 0.03723 0.0347 0.0071 1.0000
9.500 0.7070 0.04120 0.03916 0.0385 0.0070 1.0000
9.750 0.6830 0.04504 0.04314 0.0415 0.0070 1.0000
10.000 0.6560 0.04972 0.04796 0.0425 0.0070 1.0000
10.250 0.6119 0.05880 0.05721 0.0399 0.0073 1.0000
10.500 0.5554 0.07669 0.07521 0.0284 0.0086 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010-34 (naca001034-il)