NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 200,000 Max Cl/Cd: 32.22 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001035-il-200000-n5.txt Download as CSV file: xf-naca001035-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5941 0.08976 0.08623 -0.0368 1.0000 0.0104
-9.750 -0.6065 0.08386 0.08035 -0.0408 1.0000 0.0102
-9.500 -0.6227 0.07917 0.07564 -0.0421 1.0000 0.0101
-9.250 -0.6418 0.07548 0.07191 -0.0410 1.0000 0.0100
-9.000 -0.6630 0.07263 0.06903 -0.0377 1.0000 0.0099
-8.750 -0.6859 0.07045 0.06682 -0.0325 1.0000 0.0098
-8.500 -0.7045 0.06774 0.06404 -0.0277 1.0000 0.0096
-8.250 -0.7202 0.06475 0.06095 -0.0230 1.0000 0.0093
-8.000 -0.7336 0.06154 0.05761 -0.0182 1.0000 0.0090
-7.750 -0.7450 0.05803 0.05392 -0.0133 1.0000 0.0087
-7.500 -0.7542 0.05407 0.04974 -0.0081 1.0000 0.0082
-7.250 -0.7586 0.05084 0.04629 -0.0035 1.0000 0.0082
-7.000 -0.7579 0.04833 0.04358 0.0002 0.9999 0.0087
-6.750 -0.7434 0.04482 0.03975 0.0013 0.9974 0.0094
-6.500 -0.7271 0.04103 0.03557 0.0028 0.9951 0.0099
-6.250 -0.7123 0.03713 0.03125 0.0050 0.9924 0.0098
-6.000 -0.6941 0.03332 0.02695 0.0069 0.9900 0.0095
-5.750 -0.6721 0.02989 0.02301 0.0084 0.9881 0.0094
-5.500 -0.6469 0.02697 0.01960 0.0093 0.9869 0.0095
-5.250 -0.6225 0.02465 0.01689 0.0104 0.9852 0.0097
-5.000 -0.5958 0.02271 0.01463 0.0110 0.9836 0.0103
-4.750 -0.5679 0.02159 0.01325 0.0110 0.9819 0.0118
-4.500 -0.5406 0.02012 0.01160 0.0111 0.9805 0.0129
-4.250 -0.5164 0.01845 0.00982 0.0117 0.9792 0.0143
-4.000 -0.4894 0.01758 0.00887 0.0116 0.9776 0.0169
-3.750 -0.4673 0.01699 0.00817 0.0126 0.9744 0.0209
-3.500 -0.4438 0.01623 0.00728 0.0132 0.9716 0.0263
-3.250 -0.4169 0.01566 0.00665 0.0131 0.9694 0.0414
-3.000 -0.3929 0.01465 0.00612 0.0132 0.9675 0.1403
-2.750 -0.3899 0.01259 0.00558 0.0172 0.9630 0.4797
-2.500 -0.3723 0.01155 0.00597 0.0203 0.9617 0.7958
-2.250 -0.3305 0.01236 0.00684 0.0188 0.9625 0.8867
-2.000 -0.2905 0.01319 0.00755 0.0172 0.9626 0.9151
-1.750 -0.2541 0.01360 0.00780 0.0156 0.9614 0.9271
-1.500 -0.2136 0.01375 0.00784 0.0126 0.9604 0.9295
-1.250 -0.1733 0.01390 0.00788 0.0096 0.9594 0.9329
-1.000 -0.1397 0.01397 0.00786 0.0080 0.9575 0.9385
-0.750 -0.1037 0.01400 0.00783 0.0058 0.9559 0.9416
-0.500 -0.0645 0.01402 0.00781 0.0028 0.9549 0.9431
-0.250 -0.0295 0.01404 0.00780 0.0008 0.9526 0.9453
0.000 0.0000 0.01406 0.00782 0.0000 0.9486 0.9486
0.250 0.0295 0.01404 0.00780 -0.0008 0.9453 0.9526
0.500 0.0645 0.01402 0.00781 -0.0028 0.9431 0.9549
0.750 0.1037 0.01400 0.00783 -0.0058 0.9416 0.9559
1.000 0.1397 0.01397 0.00786 -0.0080 0.9386 0.9575
1.250 0.1733 0.01390 0.00788 -0.0096 0.9329 0.9594
1.500 0.2136 0.01375 0.00784 -0.0126 0.9295 0.9604
1.750 0.2542 0.01359 0.00780 -0.0156 0.9271 0.9614
2.000 0.2913 0.01316 0.00752 -0.0174 0.9148 0.9624
2.250 0.3306 0.01236 0.00683 -0.0188 0.8867 0.9625
2.500 0.3721 0.01155 0.00597 -0.0202 0.7965 0.9617
2.750 0.3898 0.01259 0.00558 -0.0172 0.4799 0.9630
3.000 0.3929 0.01465 0.00612 -0.0132 0.1404 0.9674
3.250 0.4169 0.01566 0.00665 -0.0131 0.0415 0.9694
3.500 0.4437 0.01623 0.00728 -0.0132 0.0262 0.9716
3.750 0.4673 0.01699 0.00817 -0.0126 0.0209 0.9744
4.000 0.4895 0.01758 0.00887 -0.0116 0.0169 0.9777
4.250 0.5165 0.01845 0.00982 -0.0118 0.0143 0.9792
4.500 0.5405 0.02013 0.01160 -0.0111 0.0129 0.9806
4.750 0.5678 0.02163 0.01328 -0.0109 0.0119 0.9819
5.000 0.5957 0.02271 0.01463 -0.0109 0.0103 0.9836
5.250 0.6224 0.02465 0.01689 -0.0104 0.0097 0.9852
5.500 0.6469 0.02696 0.01960 -0.0093 0.0095 0.9869
5.750 0.6721 0.02987 0.02299 -0.0084 0.0094 0.9881
6.000 0.6941 0.03332 0.02695 -0.0069 0.0095 0.9900
6.250 0.7123 0.03712 0.03124 -0.0050 0.0098 0.9924
6.500 0.7271 0.04103 0.03558 -0.0027 0.0099 0.9951
6.750 0.7434 0.04480 0.03974 -0.0014 0.0094 0.9974
7.000 0.7581 0.04824 0.04349 -0.0003 0.0086 0.9999
7.250 0.7586 0.05081 0.04625 0.0035 0.0082 1.0000
7.500 0.7544 0.05399 0.04965 0.0081 0.0082 1.0000
7.750 0.7450 0.05800 0.05390 0.0133 0.0086 1.0000
8.000 0.7337 0.06153 0.05760 0.0182 0.0090 1.0000
8.250 0.7203 0.06475 0.06094 0.0230 0.0093 1.0000
8.500 0.7046 0.06773 0.06403 0.0277 0.0096 1.0000
8.750 0.6860 0.07045 0.06682 0.0325 0.0098 1.0000
9.000 0.6631 0.07264 0.06904 0.0377 0.0099 1.0000
9.250 0.6420 0.07548 0.07192 0.0410 0.0100 1.0000
9.500 0.6231 0.07916 0.07563 0.0421 0.0101 1.0000
9.750 0.6068 0.08386 0.08035 0.0407 0.0102 1.0000
10.000 0.5946 0.08976 0.08623 0.0368 0.0104 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010-35 (naca001035-il)