NACA 16009 (naca16009-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 200,000 Max Cl/Cd: 34.56 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16009-il-200000-n5.txt Download as CSV file: xf-naca16009-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6150 0.08858 0.08503 -0.0300 1.0000 0.0088
-9.750 -0.6247 0.08219 0.07866 -0.0349 1.0000 0.0087
-9.500 -0.6388 0.07674 0.07320 -0.0377 1.0000 0.0086
-9.250 -0.6560 0.07255 0.06896 -0.0375 1.0000 0.0085
-9.000 -0.6756 0.06933 0.06570 -0.0347 1.0000 0.0084
-8.750 -0.6945 0.06643 0.06274 -0.0306 1.0000 0.0084
-8.500 -0.7090 0.06310 0.05932 -0.0269 1.0000 0.0083
-8.250 -0.7214 0.05968 0.05577 -0.0228 1.0000 0.0083
-8.000 -0.7316 0.05618 0.05212 -0.0186 1.0000 0.0083
-7.750 -0.7394 0.05259 0.04834 -0.0142 1.0000 0.0083
-7.500 -0.7450 0.04891 0.04442 -0.0097 1.0000 0.0083
-7.250 -0.7476 0.04519 0.04043 -0.0051 1.0000 0.0085
-7.000 -0.7429 0.04199 0.03688 -0.0010 1.0000 0.0092
-6.750 -0.7451 0.03806 0.03252 0.0038 1.0000 0.0098
-6.500 -0.7429 0.03505 0.02920 0.0076 1.0000 0.0104
-6.250 -0.7344 0.03220 0.02596 0.0111 1.0000 0.0105
-6.000 -0.7221 0.02929 0.02260 0.0142 0.9999 0.0104
-5.750 -0.6986 0.02644 0.01921 0.0151 0.9984 0.0105
-5.500 -0.6733 0.02412 0.01648 0.0157 0.9970 0.0107
-5.250 -0.6469 0.02223 0.01429 0.0160 0.9959 0.0110
-5.000 -0.6195 0.02069 0.01253 0.0160 0.9947 0.0116
-4.750 -0.5926 0.01941 0.01108 0.0161 0.9935 0.0126
-4.500 -0.5669 0.01831 0.00984 0.0165 0.9918 0.0139
-4.250 -0.5397 0.01777 0.00919 0.0163 0.9898 0.0167
-4.000 -0.5153 0.01656 0.00789 0.0168 0.9877 0.0194
-3.750 -0.4880 0.01587 0.00704 0.0167 0.9857 0.0238
-3.500 -0.4601 0.01525 0.00638 0.0164 0.9840 0.0349
-3.250 -0.4314 0.01468 0.00591 0.0158 0.9824 0.0660
-3.000 -0.4090 0.01392 0.00552 0.0163 0.9795 0.1457
-2.750 -0.3914 0.01260 0.00512 0.0175 0.9765 0.3544
-2.500 -0.3795 0.01099 0.00487 0.0204 0.9737 0.6552
-2.250 -0.3468 0.01100 0.00549 0.0207 0.9741 0.8467
-2.000 -0.3113 0.01133 0.00577 0.0196 0.9732 0.8854
-1.750 -0.2715 0.01205 0.00643 0.0181 0.9736 0.9239
-1.500 -0.2151 0.01293 0.00717 0.0129 0.9772 0.9464
-1.250 -0.1771 0.01302 0.00716 0.0104 0.9759 0.9510
-1.000 -0.1453 0.01305 0.00711 0.0092 0.9734 0.9561
-0.750 -0.1063 0.01307 0.00708 0.0063 0.9721 0.9579
-0.500 -0.0681 0.01309 0.00705 0.0036 0.9707 0.9599
-0.250 -0.0304 0.01310 0.00704 0.0010 0.9694 0.9622
0.000 0.0000 0.01310 0.00703 0.0000 0.9658 0.9658
0.250 0.0304 0.01310 0.00703 -0.0010 0.9622 0.9694
0.500 0.0681 0.01309 0.00705 -0.0036 0.9599 0.9707
0.750 0.1063 0.01307 0.00708 -0.0063 0.9579 0.9721
1.000 0.1453 0.01304 0.00711 -0.0091 0.9561 0.9734
1.250 0.1771 0.01302 0.00716 -0.0104 0.9511 0.9759
1.500 0.2152 0.01293 0.00716 -0.0129 0.9464 0.9773
1.750 0.2716 0.01205 0.00643 -0.0181 0.9239 0.9736
2.000 0.3114 0.01133 0.00577 -0.0196 0.8855 0.9733
2.250 0.3467 0.01099 0.00549 -0.0207 0.8466 0.9742
2.500 0.3795 0.01098 0.00487 -0.0204 0.6554 0.9737
2.750 0.3914 0.01259 0.00512 -0.0175 0.3552 0.9765
3.000 0.4089 0.01392 0.00552 -0.0163 0.1460 0.9796
3.250 0.4315 0.01468 0.00590 -0.0158 0.0658 0.9824
3.500 0.4601 0.01525 0.00638 -0.0164 0.0348 0.9840
3.750 0.4880 0.01587 0.00704 -0.0167 0.0238 0.9858
4.000 0.5153 0.01656 0.00789 -0.0168 0.0194 0.9878
4.250 0.5397 0.01774 0.00916 -0.0163 0.0166 0.9898
4.500 0.5669 0.01830 0.00984 -0.0165 0.0138 0.9918
4.750 0.5925 0.01941 0.01108 -0.0161 0.0126 0.9935
5.000 0.6195 0.02069 0.01252 -0.0160 0.0116 0.9948
5.250 0.6469 0.02222 0.01428 -0.0160 0.0110 0.9959
5.500 0.6733 0.02411 0.01647 -0.0157 0.0107 0.9970
5.750 0.6986 0.02644 0.01920 -0.0151 0.0105 0.9984
6.000 0.7221 0.02928 0.02259 -0.0142 0.0104 0.9999
6.250 0.7344 0.03219 0.02595 -0.0111 0.0105 1.0000
6.500 0.7428 0.03502 0.02917 -0.0076 0.0104 1.0000
6.750 0.7452 0.03803 0.03249 -0.0038 0.0098 1.0000
7.000 0.7428 0.04198 0.03688 0.0010 0.0092 1.0000
7.250 0.7475 0.04519 0.04042 0.0052 0.0085 1.0000
7.500 0.7450 0.04889 0.04440 0.0097 0.0083 1.0000
7.750 0.7394 0.05258 0.04833 0.0142 0.0083 1.0000
8.000 0.7316 0.05617 0.05210 0.0186 0.0083 1.0000
8.250 0.7214 0.05968 0.05578 0.0228 0.0083 1.0000
8.500 0.7091 0.06309 0.05931 0.0268 0.0083 1.0000
8.750 0.6946 0.06644 0.06276 0.0306 0.0084 1.0000
9.000 0.6757 0.06936 0.06573 0.0347 0.0084 1.0000
9.250 0.6563 0.07257 0.06898 0.0375 0.0085 1.0000
9.500 0.6391 0.07680 0.07326 0.0376 0.0086 1.0000
9.750 0.6252 0.08225 0.07872 0.0347 0.0087 1.0000
10.000 0.6156 0.08866 0.08510 0.0298 0.0088 1.0000
10.250 0.6090 0.09426 0.09066 0.0266 0.0089 1.0000
10.500 0.6040 0.09953 0.09590 0.0241 0.0090 1.0000
10.750 0.6000 0.10457 0.10090 0.0219 0.0091 1.0000
11.000 0.5966 0.10946 0.10576 0.0200 0.0092 1.0000
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Polar data table (+)
Polar graphs
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