NACA 16009 (naca16009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 16009 (naca16009-il) Reynolds number: 1,000,000 Max Cl/Cd: 46.95 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16009-il-1000000.txt Download as CSV file: xf-naca16009-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6224 0.08188 0.08030 -0.0345 1.0000 0.0069
-9.500 -0.6414 0.07601 0.07440 -0.0384 1.0000 0.0067
-9.250 -0.6636 0.07218 0.07055 -0.0372 1.0000 0.0065
-9.000 -0.6900 0.06990 0.06823 -0.0322 1.0000 0.0064
-8.750 -0.7139 0.06759 0.06589 -0.0266 1.0000 0.0064
-6.750 -0.6912 0.02792 0.02421 -0.0097 0.9869 0.0068
-6.500 -0.6727 0.02351 0.01931 -0.0078 0.9853 0.0071
-6.250 -0.6489 0.02065 0.01609 -0.0070 0.9843 0.0072
-6.000 -0.6227 0.01831 0.01343 -0.0068 0.9836 0.0072
-5.750 -0.5937 0.01687 0.01177 -0.0072 0.9830 0.0076
-5.500 -0.5635 0.01589 0.01066 -0.0079 0.9825 0.0079
-5.250 -0.5422 0.01423 0.00881 -0.0064 0.9802 0.0079
-5.000 -0.5192 0.01297 0.00742 -0.0054 0.9778 0.0079
-4.750 -0.4930 0.01215 0.00651 -0.0052 0.9760 0.0082
-4.500 -0.4694 0.01085 0.00502 -0.0044 0.9743 0.0095
-4.250 -0.4402 0.01032 0.00443 -0.0050 0.9731 0.0111
-4.000 -0.4093 0.00996 0.00401 -0.0059 0.9722 0.0127
-3.750 -0.3773 0.00972 0.00375 -0.0071 0.9715 0.0147
-3.500 -0.3471 0.00911 0.00323 -0.0078 0.9708 0.0469
-3.250 -0.3162 0.00871 0.00302 -0.0089 0.9701 0.0910
-3.000 -0.2872 0.00820 0.00279 -0.0097 0.9692 0.1714
-2.750 -0.2752 0.00745 0.00258 -0.0067 0.9636 0.3185
-2.500 -0.2640 0.00600 0.00223 -0.0038 0.9600 0.6068
-2.250 -0.2465 0.00525 0.00208 -0.0017 0.9578 0.7640
-2.000 -0.2188 0.00506 0.00203 -0.0016 0.9565 0.8146
-1.750 -0.1942 0.00499 0.00203 -0.0009 0.9537 0.8455
-1.500 -0.1693 0.00495 0.00203 -0.0002 0.9503 0.8683
-1.250 -0.1414 0.00492 0.00203 -0.0001 0.9480 0.8844
-1.000 -0.1122 0.00490 0.00202 -0.0005 0.9461 0.8954
-0.750 -0.0834 0.00494 0.00208 -0.0005 0.9445 0.9111
-0.500 -0.0537 0.00505 0.00220 -0.0007 0.9429 0.9233
-0.250 -0.0298 0.00513 0.00230 0.0003 0.9388 0.9313
0.000 0.0000 0.00518 0.00235 0.0000 0.9352 0.9352
0.250 0.0298 0.00513 0.00230 -0.0003 0.9313 0.9388
0.500 0.0537 0.00505 0.00220 0.0007 0.9234 0.9429
0.750 0.0834 0.00494 0.00208 0.0005 0.9111 0.9445
1.000 0.1122 0.00490 0.00202 0.0005 0.8954 0.9462
1.250 0.1414 0.00492 0.00203 0.0002 0.8843 0.9480
1.500 0.1694 0.00495 0.00204 0.0001 0.8694 0.9503
1.750 0.1940 0.00499 0.00203 0.0009 0.8446 0.9537
2.000 0.2188 0.00506 0.00203 0.0016 0.8148 0.9565
2.250 0.2465 0.00525 0.00208 0.0016 0.7645 0.9578
2.500 0.2639 0.00601 0.00223 0.0039 0.6053 0.9601
2.750 0.2753 0.00743 0.00257 0.0067 0.3205 0.9636
3.000 0.2871 0.00821 0.00279 0.0098 0.1702 0.9692
3.250 0.3162 0.00872 0.00301 0.0090 0.0907 0.9701
3.500 0.3472 0.00911 0.00323 0.0078 0.0469 0.9708
3.750 0.3776 0.00966 0.00367 0.0070 0.0154 0.9715
4.000 0.4093 0.00996 0.00401 0.0059 0.0127 0.9722
4.250 0.4402 0.01032 0.00444 0.0050 0.0112 0.9731
4.500 0.4695 0.01083 0.00500 0.0044 0.0096 0.9743
4.750 0.4931 0.01214 0.00650 0.0052 0.0082 0.9760
5.000 0.5192 0.01297 0.00742 0.0054 0.0079 0.9778
5.250 0.5422 0.01421 0.00880 0.0064 0.0079 0.9802
5.500 0.5635 0.01589 0.01065 0.0079 0.0079 0.9825
5.750 0.5937 0.01687 0.01177 0.0072 0.0076 0.9830
6.000 0.6227 0.01830 0.01342 0.0068 0.0072 0.9836
6.250 0.6490 0.02065 0.01608 0.0070 0.0072 0.9843
6.500 0.6728 0.02349 0.01928 0.0077 0.0071 0.9853
6.750 0.6910 0.02804 0.02433 0.0098 0.0068 0.9869
7.500 0.7021 0.04788 0.04548 0.0179 0.0082 0.9954
7.750 0.7292 0.05058 0.04833 0.0179 0.0073 0.9963
8.000 0.7396 0.05594 0.05390 0.0181 0.0068 0.9982
8.250 0.7455 0.06146 0.05960 0.0178 0.0065 0.9999
8.500 0.7316 0.06464 0.06287 0.0221 0.0064 1.0000
8.750 0.7138 0.06759 0.06589 0.0266 0.0064 1.0000
9.000 0.6901 0.06990 0.06824 0.0322 0.0064 1.0000
9.250 0.6638 0.07218 0.07055 0.0372 0.0066 1.0000
9.500 0.6417 0.07602 0.07442 0.0383 0.0067 1.0000
9.750 0.6228 0.08192 0.08034 0.0344 0.0069 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 16009 (naca16009-il)