NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 500,000 Max Cl/Cd: 60.23 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0009sm-il-500000-n5.txt Download as CSV file: xf-n0009sm-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9442 0.10031 0.09756 -0.0049 1.0000 0.0043
-15.000 -1.0016 0.08451 0.08164 -0.0131 1.0000 0.0040
-14.750 -1.0614 0.06779 0.06469 -0.0232 1.0000 0.0038
-14.500 -1.0959 0.05647 0.05314 -0.0314 1.0000 0.0036
-14.250 -1.1134 0.04947 0.04595 -0.0365 1.0000 0.0037
-14.000 -1.1313 0.04362 0.03989 -0.0400 1.0000 0.0036
-13.750 -1.1399 0.03993 0.03603 -0.0412 1.0000 0.0037
-13.500 -1.1486 0.03684 0.03276 -0.0409 1.0000 0.0038
-13.250 -1.1526 0.03457 0.03034 -0.0397 1.0000 0.0039
-13.000 -1.1568 0.03256 0.02817 -0.0376 1.0000 0.0039
-12.750 -1.1591 0.03086 0.02631 -0.0348 1.0000 0.0040
-12.500 -1.1592 0.02946 0.02477 -0.0316 1.0000 0.0041
-12.250 -1.1571 0.02819 0.02335 -0.0284 1.0000 0.0042
-12.000 -1.1498 0.02692 0.02190 -0.0260 1.0000 0.0044
-11.750 -1.1401 0.02576 0.02058 -0.0237 1.0000 0.0046
-11.500 -1.1276 0.02476 0.01944 -0.0218 1.0000 0.0047
-11.250 -1.1173 0.02350 0.01803 -0.0195 1.0000 0.0050
-11.000 -1.1044 0.02241 0.01682 -0.0175 1.0000 0.0054
-10.750 -1.0891 0.02151 0.01583 -0.0158 1.0000 0.0058
-10.500 -1.0724 0.02073 0.01495 -0.0142 1.0000 0.0063
-10.250 -1.0554 0.01995 0.01405 -0.0126 1.0000 0.0069
-10.000 -1.0372 0.01928 0.01328 -0.0111 1.0000 0.0074
-9.750 -1.0207 0.01839 0.01229 -0.0094 1.0000 0.0085
-9.500 -1.0021 0.01773 0.01157 -0.0079 1.0000 0.0094
-9.250 -0.9828 0.01714 0.01089 -0.0065 1.0000 0.0104
-9.000 -0.9637 0.01653 0.01021 -0.0050 1.0000 0.0117
-8.750 -0.9440 0.01597 0.00963 -0.0036 1.0000 0.0136
-8.500 -0.9236 0.01552 0.00912 -0.0024 1.0000 0.0155
-8.250 -0.9031 0.01506 0.00865 -0.0011 1.0000 0.0181
-8.000 -0.8820 0.01468 0.00826 0.0001 1.0000 0.0207
-7.750 -0.8603 0.01437 0.00787 0.0012 1.0000 0.0227
-7.500 -0.8397 0.01394 0.00741 0.0026 1.0000 0.0251
-7.250 -0.8185 0.01359 0.00705 0.0038 1.0000 0.0276
-7.000 -0.7969 0.01328 0.00671 0.0050 1.0000 0.0297
-6.750 -0.7752 0.01300 0.00636 0.0062 1.0000 0.0313
-6.500 -0.7539 0.01266 0.00599 0.0074 1.0000 0.0334
-6.250 -0.7328 0.01232 0.00564 0.0087 1.0000 0.0370
-6.000 -0.7112 0.01205 0.00535 0.0099 1.0000 0.0397
-5.750 -0.6894 0.01181 0.00507 0.0111 1.0000 0.0419
-5.500 -0.6678 0.01155 0.00476 0.0123 1.0000 0.0437
-5.250 -0.6406 0.01121 0.00442 0.0123 0.9990 0.0477
-5.000 -0.6074 0.01094 0.00415 0.0111 0.9966 0.0518
-4.750 -0.5739 0.01072 0.00388 0.0097 0.9941 0.0560
-4.500 -0.5424 0.01041 0.00361 0.0088 0.9912 0.0635
-4.250 -0.5102 0.01017 0.00337 0.0078 0.9877 0.0705
-4.000 -0.4769 0.00991 0.00315 0.0065 0.9844 0.0813
-3.750 -0.4427 0.00959 0.00291 0.0050 0.9816 0.1002
-3.500 -0.4143 0.00923 0.00269 0.0047 0.9760 0.1301
-3.250 -0.3824 0.00887 0.00249 0.0037 0.9714 0.1671
-3.000 -0.3490 0.00854 0.00229 0.0023 0.9677 0.2058
-2.750 -0.3210 0.00821 0.00212 0.0023 0.9601 0.2456
-2.500 -0.2871 0.00784 0.00196 0.0008 0.9551 0.2988
-2.250 -0.2567 0.00755 0.00183 0.0002 0.9464 0.3424
-2.000 -0.2224 0.00725 0.00170 -0.0013 0.9383 0.3886
-1.750 -0.1893 0.00696 0.00158 -0.0024 0.9275 0.4374
-1.500 -0.1576 0.00663 0.00148 -0.0033 0.9137 0.5013
-1.250 -0.1280 0.00630 0.00138 -0.0036 0.8958 0.5708
-1.000 -0.0987 0.00613 0.00130 -0.0038 0.8721 0.6098
-0.750 -0.0719 0.00603 0.00124 -0.0033 0.8442 0.6453
-0.500 -0.0470 0.00596 0.00120 -0.0024 0.8151 0.6804
-0.250 -0.0232 0.00593 0.00117 -0.0013 0.7828 0.7147
0.000 0.0000 0.00591 0.00116 0.0000 0.7484 0.7486
0.250 0.0232 0.00593 0.00117 0.0013 0.7150 0.7831
0.500 0.0470 0.00596 0.00120 0.0024 0.6806 0.8149
0.750 0.0718 0.00603 0.00124 0.0033 0.6445 0.8444
1.000 0.0987 0.00613 0.00130 0.0038 0.6096 0.8721
1.250 0.1280 0.00630 0.00138 0.0036 0.5711 0.8957
1.500 0.1576 0.00663 0.00148 0.0033 0.5012 0.9137
1.750 0.1893 0.00696 0.00158 0.0025 0.4375 0.9275
2.000 0.2226 0.00724 0.00169 0.0012 0.3903 0.9385
2.250 0.2567 0.00755 0.00183 -0.0002 0.3424 0.9465
2.500 0.2872 0.00784 0.00196 -0.0008 0.2988 0.9551
2.750 0.3210 0.00822 0.00212 -0.0023 0.2452 0.9601
3.000 0.3489 0.00854 0.00229 -0.0023 0.2056 0.9677
3.250 0.3824 0.00887 0.00249 -0.0037 0.1669 0.9715
3.500 0.4143 0.00924 0.00269 -0.0047 0.1292 0.9761
3.750 0.4428 0.00960 0.00291 -0.0050 0.0996 0.9817
4.000 0.4771 0.00991 0.00315 -0.0065 0.0811 0.9845
4.250 0.5103 0.01017 0.00337 -0.0078 0.0704 0.9878
4.500 0.5424 0.01041 0.00361 -0.0088 0.0634 0.9912
4.750 0.5740 0.01072 0.00388 -0.0097 0.0559 0.9942
5.000 0.6076 0.01094 0.00414 -0.0111 0.0517 0.9967
5.250 0.6407 0.01121 0.00442 -0.0124 0.0477 0.9990
5.500 0.6676 0.01155 0.00476 -0.0123 0.0438 1.0000
5.750 0.6892 0.01181 0.00507 -0.0111 0.0419 1.0000
6.000 0.7110 0.01205 0.00535 -0.0099 0.0396 1.0000
6.250 0.7327 0.01232 0.00564 -0.0087 0.0370 1.0000
6.500 0.7538 0.01266 0.00599 -0.0074 0.0335 1.0000
6.750 0.7750 0.01300 0.00637 -0.0061 0.0314 1.0000
7.000 0.7967 0.01328 0.00670 -0.0049 0.0297 1.0000
7.250 0.8183 0.01359 0.00706 -0.0037 0.0276 1.0000
7.500 0.8396 0.01394 0.00741 -0.0025 0.0251 1.0000
7.750 0.8603 0.01437 0.00786 -0.0012 0.0227 1.0000
8.000 0.8819 0.01468 0.00826 -0.0001 0.0207 1.0000
8.250 0.9031 0.01505 0.00864 0.0011 0.0180 1.0000
8.500 0.9235 0.01552 0.00912 0.0024 0.0155 1.0000
8.750 0.9440 0.01597 0.00963 0.0036 0.0135 1.0000
9.000 0.9636 0.01654 0.01021 0.0050 0.0116 1.0000
9.250 0.9829 0.01713 0.01088 0.0065 0.0104 1.0000
9.500 1.0022 0.01773 0.01157 0.0079 0.0094 1.0000
9.750 1.0207 0.01840 0.01230 0.0094 0.0084 1.0000
10.000 1.0374 0.01927 0.01328 0.0111 0.0074 1.0000
10.250 1.0551 0.02000 0.01411 0.0126 0.0070 1.0000
10.500 1.0723 0.02075 0.01497 0.0142 0.0064 1.0000
10.750 1.0891 0.02153 0.01586 0.0158 0.0058 1.0000
11.000 1.1045 0.02242 0.01684 0.0175 0.0054 1.0000
11.250 1.1177 0.02349 0.01803 0.0194 0.0050 1.0000
11.500 1.1283 0.02474 0.01942 0.0217 0.0047 1.0000
11.750 1.1399 0.02582 0.02065 0.0237 0.0046 1.0000
12.000 1.1503 0.02693 0.02191 0.0259 0.0044 1.0000
12.250 1.1573 0.02821 0.02337 0.0283 0.0043 1.0000
12.500 1.1594 0.02950 0.02481 0.0316 0.0042 1.0000
12.750 1.1606 0.03082 0.02627 0.0346 0.0040 1.0000
13.000 1.1568 0.03262 0.02823 0.0375 0.0040 1.0000
13.250 1.1537 0.03456 0.03034 0.0395 0.0039 1.0000
13.500 1.1481 0.03698 0.03291 0.0408 0.0039 1.0000
13.750 1.1384 0.04023 0.03634 0.0409 0.0038 1.0000
14.000 1.1273 0.04433 0.04062 0.0394 0.0037 1.0000
14.250 1.1131 0.04976 0.04625 0.0360 0.0038 1.0000
14.500 1.0910 0.05774 0.05444 0.0301 0.0037 1.0000
14.750 1.0571 0.06911 0.06604 0.0220 0.0038 1.0000
15.000 1.0035 0.08454 0.08168 0.0128 0.0040 1.0000
15.250 0.9413 0.10131 0.09857 0.0040 0.0043 1.0000
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Polar data table (+)
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