NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 500,000 Max Cl/Cd: 55.91 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0009sm-il-500000.txt Download as CSV file: xf-n0009sm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9606 0.06449 0.06155 -0.0264 1.0000 0.0073
-13.250 -0.9745 0.05737 0.05426 -0.0319 1.0000 0.0074
-13.000 -1.0011 0.04929 0.04597 -0.0377 1.0000 0.0072
-12.750 -1.0177 0.04406 0.04052 -0.0404 1.0000 0.0073
-12.500 -1.0291 0.04040 0.03666 -0.0409 1.0000 0.0073
-12.250 -1.0369 0.03768 0.03375 -0.0399 1.0000 0.0074
-12.000 -1.0608 0.03389 0.02966 -0.0366 1.0000 0.0075
-11.750 -1.0741 0.03140 0.02693 -0.0323 1.0000 0.0076
-11.500 -1.0836 0.02901 0.02431 -0.0279 1.0000 0.0079
-11.250 -1.0805 0.02724 0.02237 -0.0250 1.0000 0.0082
-11.000 -1.0713 0.02596 0.02096 -0.0227 1.0000 0.0085
-10.750 -1.0593 0.02486 0.01974 -0.0206 1.0000 0.0089
-10.500 -1.0463 0.02376 0.01851 -0.0186 1.0000 0.0094
-10.250 -1.0324 0.02269 0.01729 -0.0166 1.0000 0.0101
-10.000 -1.0141 0.02207 0.01653 -0.0151 1.0000 0.0108
-9.750 -1.0053 0.02030 0.01459 -0.0124 1.0000 0.0121
-9.500 -0.9869 0.01967 0.01392 -0.0109 1.0000 0.0134
-9.250 -0.9677 0.01908 0.01326 -0.0095 1.0000 0.0148
-9.000 -0.9473 0.01860 0.01267 -0.0082 1.0000 0.0160
-8.750 -0.9343 0.01724 0.01122 -0.0058 1.0000 0.0185
-8.500 -0.9127 0.01692 0.01089 -0.0047 1.0000 0.0209
-8.250 -0.8880 0.01701 0.01092 -0.0041 1.0000 0.0230
-8.000 -0.8723 0.01595 0.00984 -0.0020 1.0000 0.0269
-7.750 -0.8495 0.01580 0.00964 -0.0011 1.0000 0.0299
-7.500 -0.8256 0.01582 0.00959 -0.0003 1.0000 0.0319
-7.250 -0.8101 0.01469 0.00841 0.0018 1.0000 0.0354
-7.000 -0.7886 0.01438 0.00808 0.0030 1.0000 0.0381
-6.750 -0.7671 0.01405 0.00770 0.0043 1.0000 0.0407
-6.500 -0.7446 0.01388 0.00746 0.0054 1.0000 0.0426
-6.250 -0.7271 0.01308 0.00661 0.0073 1.0000 0.0464
-6.000 -0.7062 0.01272 0.00625 0.0086 1.0000 0.0496
-5.750 -0.6849 0.01241 0.00589 0.0099 1.0000 0.0527
-5.500 -0.6630 0.01219 0.00562 0.0111 1.0000 0.0548
-5.250 -0.6448 0.01154 0.00494 0.0130 1.0000 0.0595
-5.000 -0.6239 0.01121 0.00461 0.0144 1.0000 0.0637
-4.750 -0.6024 0.01098 0.00432 0.0156 1.0000 0.0675
-4.500 -0.5825 0.01056 0.00394 0.0172 1.0000 0.0756
-4.250 -0.5614 0.01029 0.00366 0.0185 1.0000 0.0844
-4.000 -0.5410 0.00995 0.00341 0.0199 1.0000 0.0999
-3.750 -0.5211 0.00958 0.00319 0.0214 1.0000 0.1309
-3.500 -0.5018 0.00916 0.00300 0.0228 1.0000 0.1834
-3.250 -0.4658 0.00869 0.00286 0.0207 0.9968 0.2576
-3.000 -0.4292 0.00831 0.00278 0.0185 0.9935 0.3301
-2.750 -0.3949 0.00794 0.00265 0.0169 0.9891 0.3905
-2.500 -0.3587 0.00762 0.00255 0.0149 0.9850 0.4506
-2.250 -0.3206 0.00730 0.00247 0.0126 0.9818 0.5164
-2.000 -0.2893 0.00697 0.00236 0.0118 0.9754 0.5718
-1.750 -0.2533 0.00667 0.00226 0.0101 0.9709 0.6279
-1.500 -0.2183 0.00637 0.00218 0.0087 0.9663 0.6827
-1.250 -0.1878 0.00605 0.00212 0.0084 0.9595 0.7449
-1.000 -0.1507 0.00577 0.00207 0.0068 0.9555 0.8048
-0.750 -0.1175 0.00559 0.00201 0.0061 0.9471 0.8417
-0.500 -0.0775 0.00546 0.00197 0.0039 0.9408 0.8719
-0.250 -0.0411 0.00539 0.00196 0.0024 0.9290 0.8971
0.000 0.0000 0.00536 0.00195 0.0000 0.9152 0.9152
0.250 0.0411 0.00539 0.00196 -0.0025 0.8974 0.9291
0.500 0.0775 0.00545 0.00197 -0.0038 0.8717 0.9408
0.750 0.1176 0.00559 0.00201 -0.0061 0.8410 0.9472
1.000 0.1507 0.00576 0.00207 -0.0068 0.8052 0.9555
1.250 0.1876 0.00605 0.00212 -0.0084 0.7446 0.9594
1.500 0.2183 0.00637 0.00219 -0.0087 0.6833 0.9665
1.750 0.2534 0.00666 0.00226 -0.0101 0.6290 0.9709
2.000 0.2894 0.00697 0.00236 -0.0118 0.5719 0.9754
2.250 0.3208 0.00729 0.00247 -0.0126 0.5167 0.9818
2.500 0.3587 0.00762 0.00254 -0.0149 0.4506 0.9850
2.750 0.3949 0.00794 0.00265 -0.0169 0.3904 0.9892
3.000 0.4291 0.00831 0.00277 -0.0184 0.3299 0.9935
3.250 0.4659 0.00869 0.00286 -0.0207 0.2566 0.9968
3.500 0.5018 0.00916 0.00300 -0.0228 0.1827 1.0000
3.750 0.5210 0.00957 0.00319 -0.0213 0.1315 1.0000
4.000 0.5408 0.00995 0.00341 -0.0199 0.0997 1.0000
4.250 0.5613 0.01028 0.00366 -0.0185 0.0844 1.0000
4.500 0.5823 0.01056 0.00393 -0.0171 0.0755 1.0000
4.750 0.6022 0.01098 0.00431 -0.0156 0.0674 1.0000
5.000 0.6238 0.01121 0.00461 -0.0143 0.0636 1.0000
5.250 0.6446 0.01153 0.00494 -0.0130 0.0594 1.0000
5.500 0.6628 0.01220 0.00562 -0.0111 0.0549 1.0000
5.750 0.6847 0.01242 0.00590 -0.0099 0.0527 1.0000
6.000 0.7060 0.01273 0.00625 -0.0086 0.0496 1.0000
6.250 0.7270 0.01308 0.00661 -0.0072 0.0464 1.0000
6.500 0.7443 0.01390 0.00748 -0.0053 0.0426 1.0000
6.750 0.7669 0.01407 0.00772 -0.0042 0.0407 1.0000
7.000 0.7885 0.01438 0.00808 -0.0030 0.0381 1.0000
7.250 0.8099 0.01470 0.00843 -0.0018 0.0354 1.0000
7.500 0.8255 0.01582 0.00959 0.0003 0.0319 1.0000
7.750 0.8495 0.01580 0.00964 0.0011 0.0299 1.0000
8.000 0.8722 0.01596 0.00985 0.0021 0.0269 1.0000
8.250 0.8884 0.01695 0.01086 0.0040 0.0230 1.0000
8.500 0.9127 0.01692 0.01089 0.0047 0.0209 1.0000
8.750 0.9343 0.01724 0.01123 0.0058 0.0185 1.0000
9.000 0.9476 0.01857 0.01263 0.0082 0.0160 1.0000
9.250 0.9683 0.01901 0.01318 0.0094 0.0147 1.0000
9.500 0.9872 0.01964 0.01389 0.0109 0.0133 1.0000
9.750 1.0051 0.02033 0.01462 0.0124 0.0121 1.0000
10.000 1.0138 0.02213 0.01660 0.0152 0.0108 1.0000
10.250 1.0302 0.02299 0.01763 0.0169 0.0102 1.0000
10.500 1.0455 0.02389 0.01866 0.0187 0.0096 1.0000
10.750 1.0594 0.02488 0.01976 0.0206 0.0089 1.0000
11.000 1.0708 0.02606 0.02108 0.0227 0.0086 1.0000
11.250 1.0802 0.02733 0.02247 0.0250 0.0082 1.0000
11.500 1.0836 0.02905 0.02435 0.0279 0.0079 1.0000
11.750 1.0759 0.03134 0.02686 0.0321 0.0076 1.0000
12.000 1.0573 0.03426 0.03007 0.0368 0.0075 1.0000
12.250 1.0474 0.03678 0.03279 0.0394 0.0074 1.0000
12.750 1.0188 0.04405 0.04050 0.0402 0.0073 1.0000
13.000 0.9975 0.04994 0.04663 0.0372 0.0074 1.0000
13.250 0.9841 0.05587 0.05273 0.0329 0.0074 1.0000
13.500 0.9716 0.06249 0.05950 0.0278 0.0074 1.0000
13.750 0.9556 0.07034 0.06750 0.0221 0.0075 1.0000
14.000 0.9304 0.08038 0.07769 0.0154 0.0075 1.0000
14.250 0.9222 0.08669 0.08407 0.0118 0.0077 1.0000
14.500 0.8787 0.10107 0.09862 0.0040 0.0080 1.0000
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Polar data table (+)
Polar graphs
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