NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 1,000,000 Max Cl/Cd: 51.14 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034-il-1000000-n5.txt Download as CSV file: xf-naca001034-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6704 0.08564 0.08413 -0.0192 1.0000 0.0019
-10.250 -0.6855 0.07448 0.07293 -0.0300 1.0000 0.0018
-10.000 -0.7052 0.06779 0.06614 -0.0346 1.0000 0.0018
-9.750 -0.7254 0.06288 0.06114 -0.0356 1.0000 0.0018
-9.500 -0.7452 0.05894 0.05708 -0.0337 1.0000 0.0018
-9.250 -0.7617 0.05491 0.05291 -0.0308 1.0000 0.0018
-9.000 -0.7744 0.05037 0.04818 -0.0277 1.0000 0.0017
-8.750 -0.7858 0.04587 0.04346 -0.0236 1.0000 0.0017
-8.500 -0.7975 0.04126 0.03861 -0.0184 1.0000 0.0017
-8.250 -0.8062 0.03452 0.03142 -0.0134 0.9987 0.0017
-8.000 -0.8156 0.02046 0.01602 -0.0071 0.9951 0.0020
-7.750 -0.7932 0.01831 0.01355 -0.0066 0.9930 0.0021
-7.500 -0.7679 0.01692 0.01195 -0.0066 0.9910 0.0022
-7.250 -0.7408 0.01586 0.01072 -0.0069 0.9893 0.0023
-7.000 -0.7151 0.01442 0.00908 -0.0070 0.9878 0.0024
-6.750 -0.6879 0.01351 0.00806 -0.0074 0.9861 0.0026
-6.500 -0.6613 0.01309 0.00759 -0.0076 0.9828 0.0029
-6.250 -0.6335 0.01261 0.00707 -0.0080 0.9800 0.0031
-6.000 -0.6056 0.01202 0.00640 -0.0084 0.9777 0.0035
-5.750 -0.5804 0.01142 0.00570 -0.0081 0.9737 0.0037
-5.500 -0.5545 0.01093 0.00514 -0.0080 0.9694 0.0040
-5.250 -0.5280 0.01033 0.00445 -0.0079 0.9660 0.0045
-5.000 -0.5032 0.00998 0.00407 -0.0075 0.9606 0.0050
-4.750 -0.4768 0.00967 0.00371 -0.0074 0.9558 0.0057
-4.500 -0.4501 0.00943 0.00344 -0.0074 0.9512 0.0065
-4.250 -0.4251 0.00908 0.00303 -0.0069 0.9449 0.0083
-4.000 -0.3987 0.00884 0.00276 -0.0067 0.9395 0.0103
-3.750 -0.3726 0.00863 0.00251 -0.0065 0.9331 0.0146
-3.500 -0.3469 0.00837 0.00229 -0.0062 0.9266 0.0288
-3.250 -0.3217 0.00806 0.00207 -0.0059 0.9194 0.0581
-3.000 -0.2989 0.00748 0.00179 -0.0052 0.9117 0.1474
-2.750 -0.2774 0.00678 0.00152 -0.0043 0.9028 0.2689
-2.500 -0.2563 0.00608 0.00129 -0.0034 0.8938 0.4012
-2.250 -0.2344 0.00555 0.00112 -0.0025 0.8839 0.5076
-2.000 -0.2095 0.00530 0.00102 -0.0020 0.8733 0.5603
-1.750 -0.1847 0.00508 0.00092 -0.0015 0.8626 0.6117
-1.500 -0.1598 0.00488 0.00085 -0.0010 0.8523 0.6609
-1.250 -0.1338 0.00477 0.00080 -0.0007 0.8421 0.6913
-1.000 -0.1072 0.00471 0.00076 -0.0005 0.8314 0.7146
-0.750 -0.0807 0.00464 0.00073 -0.0003 0.8205 0.7374
-0.500 -0.0539 0.00461 0.00071 -0.0002 0.8093 0.7559
-0.250 -0.0269 0.00459 0.00070 -0.0001 0.7975 0.7713
0.000 0.0000 0.00459 0.00070 0.0000 0.7849 0.7851
0.250 0.0270 0.00459 0.00070 0.0001 0.7713 0.7976
0.500 0.0540 0.00461 0.00071 0.0002 0.7560 0.8094
0.750 0.0808 0.00464 0.00073 0.0003 0.7372 0.8206
1.000 0.1073 0.00471 0.00076 0.0005 0.7147 0.8314
1.250 0.1340 0.00477 0.00080 0.0007 0.6915 0.8421
1.500 0.1600 0.00488 0.00085 0.0010 0.6615 0.8524
1.750 0.1848 0.00507 0.00092 0.0015 0.6121 0.8626
2.000 0.2097 0.00530 0.00101 0.0020 0.5610 0.8732
2.500 0.2568 0.00605 0.00129 0.0033 0.4073 0.8937
2.750 0.2777 0.00677 0.00152 0.0043 0.2709 0.9027
3.000 0.2989 0.00749 0.00179 0.0051 0.1447 0.9117
3.250 0.3218 0.00807 0.00207 0.0058 0.0568 0.9194
3.500 0.3471 0.00837 0.00229 0.0062 0.0288 0.9266
3.750 0.3728 0.00863 0.00251 0.0064 0.0145 0.9331
4.000 0.3989 0.00884 0.00276 0.0067 0.0103 0.9396
4.250 0.4252 0.00908 0.00303 0.0069 0.0084 0.9450
4.500 0.4502 0.00944 0.00344 0.0073 0.0065 0.9511
4.750 0.4770 0.00967 0.00370 0.0074 0.0057 0.9557
5.000 0.5034 0.00998 0.00407 0.0075 0.0050 0.9605
5.250 0.5283 0.01033 0.00445 0.0079 0.0045 0.9659
5.500 0.5546 0.01094 0.00515 0.0079 0.0040 0.9694
5.750 0.5805 0.01142 0.00570 0.0081 0.0037 0.9739
6.000 0.6058 0.01203 0.00641 0.0083 0.0034 0.9778
6.250 0.6336 0.01262 0.00707 0.0080 0.0031 0.9801
6.500 0.6616 0.01306 0.00756 0.0075 0.0028 0.9828
6.750 0.6882 0.01350 0.00805 0.0073 0.0026 0.9861
7.000 0.7153 0.01443 0.00909 0.0070 0.0024 0.9878
7.250 0.7411 0.01584 0.01070 0.0068 0.0023 0.9894
7.500 0.7681 0.01692 0.01194 0.0065 0.0022 0.9911
7.750 0.7934 0.01832 0.01356 0.0065 0.0021 0.9931
8.000 0.8159 0.02047 0.01603 0.0071 0.0020 0.9951
8.500 0.7973 0.04128 0.03863 0.0184 0.0017 1.0000
8.750 0.7858 0.04590 0.04350 0.0236 0.0017 1.0000
9.000 0.7745 0.05041 0.04822 0.0276 0.0017 1.0000
9.250 0.7619 0.05496 0.05296 0.0307 0.0018 1.0000
9.500 0.7455 0.05901 0.05715 0.0336 0.0018 1.0000
9.750 0.7255 0.06301 0.06126 0.0354 0.0018 1.0000
10.000 0.7055 0.06792 0.06628 0.0344 0.0018 1.0000
10.250 0.6859 0.07470 0.07315 0.0296 0.0018 1.0000
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Polar data table (+)
Polar graphs
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