NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 1,000,000 Max Cl/Cd: 45.19 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001035-il-1000000-n5.txt Download as CSV file: xf-naca001035-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6292 0.08015 0.07858 -0.0412 1.0000 0.0020
-9.750 -0.6510 0.07572 0.07412 -0.0416 1.0000 0.0020
-9.500 -0.6651 0.07035 0.06867 -0.0438 0.9985 0.0020
-9.250 -0.6773 0.06557 0.06378 -0.0441 0.9961 0.0020
-9.000 -0.6847 0.06062 0.05869 -0.0435 0.9932 0.0019
-8.750 -0.6884 0.05562 0.05352 -0.0425 0.9904 0.0019
-8.500 -0.6883 0.05025 0.04793 -0.0413 0.9884 0.0018
-8.250 -0.6850 0.04454 0.04195 -0.0396 0.9870 0.0018
-8.000 -0.6851 0.03915 0.03625 -0.0359 0.9830 0.0017
-7.750 -0.6840 0.03186 0.02847 -0.0315 0.9802 0.0017
-7.500 -0.6898 0.01867 0.01400 -0.0236 0.9780 0.0019
-7.250 -0.6683 0.01678 0.01178 -0.0226 0.9762 0.0021
-7.000 -0.6469 0.01559 0.01037 -0.0215 0.9737 0.0023
-6.750 -0.6230 0.01462 0.00925 -0.0210 0.9718 0.0024
-6.500 -0.5985 0.01376 0.00825 -0.0207 0.9702 0.0025
-6.250 -0.5756 0.01271 0.00706 -0.0200 0.9686 0.0027
-6.000 -0.5489 0.01234 0.00667 -0.0202 0.9673 0.0031
-5.750 -0.5256 0.01191 0.00619 -0.0196 0.9650 0.0034
-5.500 -0.5042 0.01138 0.00558 -0.0185 0.9618 0.0037
-5.250 -0.4809 0.01088 0.00498 -0.0177 0.9593 0.0040
-5.000 -0.4563 0.01046 0.00449 -0.0173 0.9571 0.0043
-4.750 -0.4320 0.00997 0.00394 -0.0168 0.9552 0.0052
-4.500 -0.4068 0.00969 0.00362 -0.0165 0.9532 0.0061
-4.250 -0.3831 0.00949 0.00341 -0.0159 0.9500 0.0071
-4.000 -0.3595 0.00916 0.00302 -0.0152 0.9469 0.0099
-3.750 -0.3339 0.00894 0.00278 -0.0149 0.9444 0.0132
-3.500 -0.3081 0.00868 0.00257 -0.0147 0.9423 0.0258
-3.250 -0.2813 0.00847 0.00237 -0.0148 0.9404 0.0363
-3.000 -0.2587 0.00820 0.00220 -0.0139 0.9368 0.0667
-2.750 -0.2378 0.00772 0.00200 -0.0128 0.9332 0.1481
-2.500 -0.2199 0.00697 0.00176 -0.0112 0.9297 0.2920
-2.250 -0.1985 0.00646 0.00156 -0.0102 0.9271 0.3895
-2.000 -0.1848 0.00575 0.00137 -0.0076 0.9223 0.5333
-1.750 -0.1763 0.00494 0.00118 -0.0035 0.9173 0.6985
-1.500 -0.1582 0.00457 0.00112 -0.0014 0.9140 0.7866
-1.250 -0.1343 0.00447 0.00113 -0.0006 0.9106 0.8206
-1.000 -0.1089 0.00442 0.00113 -0.0001 0.9070 0.8431
-0.750 -0.0824 0.00439 0.00116 0.0001 0.9037 0.8639
-0.500 -0.0543 0.00438 0.00116 0.0000 0.9005 0.8758
-0.250 -0.0276 0.00438 0.00115 0.0001 0.8951 0.8826
0.000 0.0000 0.00437 0.00114 0.0000 0.8885 0.8885
0.250 0.0276 0.00438 0.00115 -0.0001 0.8826 0.8950
0.500 0.0543 0.00438 0.00116 0.0000 0.8758 0.9004
0.750 0.0823 0.00439 0.00116 -0.0001 0.8633 0.9037
1.000 0.1089 0.00442 0.00113 0.0001 0.8427 0.9070
1.250 0.1343 0.00447 0.00113 0.0006 0.8205 0.9107
1.500 0.1582 0.00457 0.00113 0.0014 0.7869 0.9141
1.750 0.1764 0.00494 0.00118 0.0035 0.6993 0.9172
2.000 0.1851 0.00575 0.00137 0.0075 0.5347 0.9222
2.250 0.1985 0.00646 0.00156 0.0102 0.3886 0.9271
2.500 0.2201 0.00697 0.00176 0.0112 0.2929 0.9297
3.000 0.2588 0.00820 0.00220 0.0139 0.0670 0.9368
3.250 0.2815 0.00847 0.00237 0.0148 0.0363 0.9403
3.500 0.3082 0.00868 0.00257 0.0147 0.0258 0.9423
3.750 0.3340 0.00894 0.00278 0.0149 0.0133 0.9445
4.000 0.3595 0.00916 0.00303 0.0151 0.0099 0.9470
4.250 0.3832 0.00950 0.00341 0.0159 0.0071 0.9500
4.500 0.4070 0.00969 0.00362 0.0165 0.0061 0.9531
4.750 0.4320 0.00998 0.00395 0.0168 0.0052 0.9552
5.000 0.4566 0.01045 0.00447 0.0172 0.0044 0.9571
5.250 0.4809 0.01089 0.00499 0.0177 0.0040 0.9592
5.500 0.5043 0.01138 0.00558 0.0185 0.0037 0.9618
5.750 0.5255 0.01192 0.00620 0.0196 0.0034 0.9650
6.000 0.5489 0.01233 0.00666 0.0202 0.0031 0.9672
6.250 0.5753 0.01273 0.00709 0.0201 0.0028 0.9685
6.500 0.5984 0.01375 0.00824 0.0207 0.0025 0.9701
6.750 0.6230 0.01461 0.00923 0.0210 0.0024 0.9718
7.000 0.6468 0.01555 0.01033 0.0215 0.0023 0.9737
7.250 0.6681 0.01678 0.01177 0.0226 0.0021 0.9762
7.500 0.6897 0.01866 0.01398 0.0236 0.0019 0.9780
7.750 0.6840 0.03183 0.02844 0.0315 0.0017 0.9802
8.000 0.6853 0.03911 0.03621 0.0359 0.0017 0.9831
8.250 0.6852 0.04451 0.04191 0.0396 0.0018 0.9870
8.500 0.6884 0.05026 0.04794 0.0412 0.0018 0.9884
8.750 0.6885 0.05564 0.05354 0.0425 0.0019 0.9904
9.000 0.6847 0.06067 0.05874 0.0435 0.0019 0.9932
9.250 0.6774 0.06563 0.06384 0.0440 0.0020 0.9961
9.500 0.6654 0.07039 0.06871 0.0437 0.0020 0.9985
9.750 0.6511 0.07573 0.07413 0.0416 0.0020 1.0000
10.000 0.6296 0.08012 0.07855 0.0412 0.0020 1.0000
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Polar data table (+)
Polar graphs
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