NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.72 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0009sm-il-1000000.txt Download as CSV file: xf-n0009sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9871 0.10108 0.09896 -0.0031 1.0000 0.0037
-15.500 -1.0438 0.08589 0.08362 -0.0109 1.0000 0.0035
-15.250 -1.0914 0.07218 0.06974 -0.0187 1.0000 0.0035
-15.000 -1.1223 0.06145 0.05885 -0.0258 1.0000 0.0035
-14.750 -1.1600 0.05005 0.04716 -0.0343 1.0000 0.0033
-14.500 -1.1752 0.04398 0.04090 -0.0384 1.0000 0.0032
-14.250 -1.1861 0.03952 0.03631 -0.0407 1.0000 0.0034
-14.000 -1.1989 0.03570 0.03229 -0.0412 1.0000 0.0033
-13.750 -1.2016 0.03340 0.02987 -0.0405 1.0000 0.0035
-13.500 -1.2067 0.03120 0.02753 -0.0386 1.0000 0.0035
-13.250 -1.2041 0.02981 0.02604 -0.0366 1.0000 0.0037
-13.000 -1.2065 0.02823 0.02432 -0.0334 1.0000 0.0037
-12.750 -1.2068 0.02695 0.02292 -0.0299 1.0000 0.0038
-12.500 -1.2016 0.02578 0.02164 -0.0270 1.0000 0.0039
-12.250 -1.1928 0.02464 0.02037 -0.0246 1.0000 0.0040
-12.000 -1.1821 0.02356 0.01916 -0.0224 1.0000 0.0042
-11.750 -1.1702 0.02252 0.01799 -0.0202 1.0000 0.0044
-11.500 -1.1545 0.02177 0.01713 -0.0185 1.0000 0.0046
-11.250 -1.1400 0.02088 0.01613 -0.0167 1.0000 0.0046
-11.000 -1.1227 0.02020 0.01537 -0.0151 1.0000 0.0047
-10.750 -1.1151 0.01853 0.01348 -0.0121 1.0000 0.0051
-10.500 -1.1003 0.01755 0.01238 -0.0101 1.0000 0.0056
-10.250 -1.0829 0.01681 0.01157 -0.0084 1.0000 0.0060
-10.000 -1.0642 0.01621 0.01090 -0.0069 1.0000 0.0065
-9.750 -1.0448 0.01566 0.01028 -0.0055 1.0000 0.0071
-9.500 -1.0266 0.01498 0.00950 -0.0038 1.0000 0.0078
-9.250 -1.0087 0.01427 0.00874 -0.0020 1.0000 0.0093
-9.000 -0.9884 0.01382 0.00826 -0.0007 1.0000 0.0104
-8.750 -0.9685 0.01333 0.00771 0.0008 1.0000 0.0119
-8.500 -0.9485 0.01286 0.00726 0.0022 1.0000 0.0145
-8.250 -0.9267 0.01259 0.00696 0.0033 1.0000 0.0161
-8.000 -0.9066 0.01213 0.00654 0.0047 1.0000 0.0202
-7.750 -0.8842 0.01193 0.00632 0.0058 1.0000 0.0223
-7.500 -0.8620 0.01172 0.00607 0.0069 1.0000 0.0237
-7.250 -0.8417 0.01130 0.00568 0.0083 1.0000 0.0273
-7.000 -0.8193 0.01112 0.00550 0.0094 1.0000 0.0297
-6.750 -0.7967 0.01097 0.00534 0.0104 1.0000 0.0313
-6.500 -0.7737 0.01089 0.00524 0.0114 1.0000 0.0321
-6.250 -0.7546 0.01035 0.00465 0.0131 1.0000 0.0357
-6.000 -0.7332 0.01010 0.00439 0.0144 1.0000 0.0384
-5.750 -0.7112 0.00990 0.00418 0.0155 1.0000 0.0407
-5.500 -0.6888 0.00979 0.00405 0.0166 1.0000 0.0424
-5.250 -0.6586 0.00948 0.00372 0.0160 0.9990 0.0468
-5.000 -0.6243 0.00923 0.00349 0.0145 0.9972 0.0515
-4.750 -0.5891 0.00907 0.00330 0.0128 0.9954 0.0547
-4.500 -0.5537 0.00878 0.00305 0.0111 0.9938 0.0628
-4.250 -0.5211 0.00856 0.00284 0.0100 0.9913 0.0701
-4.000 -0.4881 0.00825 0.00262 0.0088 0.9885 0.0867
-3.750 -0.4543 0.00791 0.00241 0.0074 0.9859 0.1150
-3.500 -0.4198 0.00752 0.00222 0.0057 0.9837 0.1602
-3.250 -0.3843 0.00715 0.00205 0.0039 0.9820 0.2085
-3.000 -0.3557 0.00677 0.00188 0.0036 0.9771 0.2597
-2.750 -0.3231 0.00641 0.00172 0.0025 0.9733 0.3124
-2.500 -0.2883 0.00610 0.00158 0.0009 0.9705 0.3601
-2.250 -0.2521 0.00580 0.00146 -0.0010 0.9683 0.4071
-2.000 -0.2245 0.00552 0.00135 -0.0009 0.9606 0.4568
-1.750 -0.1893 0.00525 0.00124 -0.0025 0.9551 0.5038
-1.500 -0.1589 0.00501 0.00115 -0.0030 0.9442 0.5473
-1.250 -0.1276 0.00478 0.00107 -0.0037 0.9319 0.5947
-1.000 -0.0987 0.00454 0.00100 -0.0038 0.9149 0.6526
-0.750 -0.0729 0.00435 0.00095 -0.0031 0.8922 0.7080
-0.500 -0.0475 0.00427 0.00091 -0.0023 0.8666 0.7431
-0.250 -0.0235 0.00423 0.00088 -0.0012 0.8388 0.7762
0.000 0.0000 0.00422 0.00088 0.0000 0.8078 0.8080
0.250 0.0234 0.00423 0.00088 0.0012 0.7754 0.8383
0.500 0.0475 0.00427 0.00091 0.0024 0.7432 0.8667
0.750 0.0729 0.00435 0.00095 0.0031 0.7088 0.8922
1.000 0.0986 0.00454 0.00100 0.0038 0.6521 0.9148
1.250 0.1275 0.00478 0.00107 0.0037 0.5945 0.9317
1.500 0.1590 0.00500 0.00115 0.0030 0.5491 0.9442
1.750 0.1894 0.00525 0.00124 0.0025 0.5040 0.9551
2.000 0.2244 0.00553 0.00135 0.0010 0.4549 0.9606
2.250 0.2522 0.00580 0.00146 0.0010 0.4074 0.9683
2.500 0.2884 0.00610 0.00158 -0.0009 0.3602 0.9705
2.750 0.3232 0.00641 0.00172 -0.0025 0.3123 0.9733
3.000 0.3556 0.00677 0.00188 -0.0036 0.2592 0.9772
3.250 0.3845 0.00715 0.00205 -0.0039 0.2079 0.9820
3.500 0.4200 0.00752 0.00222 -0.0058 0.1597 0.9837
3.750 0.4544 0.00791 0.00241 -0.0074 0.1151 0.9859
4.000 0.4882 0.00825 0.00262 -0.0088 0.0865 0.9885
4.250 0.5213 0.00855 0.00284 -0.0101 0.0703 0.9914
4.500 0.5540 0.00878 0.00305 -0.0112 0.0626 0.9938
4.750 0.5893 0.00906 0.00330 -0.0129 0.0546 0.9954
5.000 0.6245 0.00923 0.00349 -0.0145 0.0514 0.9973
5.250 0.6588 0.00948 0.00372 -0.0160 0.0467 0.9990
5.500 0.6886 0.00979 0.00405 -0.0166 0.0425 1.0000
5.750 0.7110 0.00990 0.00418 -0.0155 0.0407 1.0000
6.000 0.7330 0.01009 0.00438 -0.0143 0.0383 1.0000
6.250 0.7544 0.01035 0.00465 -0.0130 0.0358 1.0000
6.500 0.7734 0.01090 0.00525 -0.0113 0.0321 1.0000
6.750 0.7966 0.01097 0.00533 -0.0104 0.0313 1.0000
7.000 0.8195 0.01108 0.00546 -0.0094 0.0295 1.0000
7.250 0.8416 0.01129 0.00566 -0.0083 0.0272 1.0000
7.500 0.8619 0.01171 0.00607 -0.0068 0.0237 1.0000
7.750 0.8841 0.01193 0.00632 -0.0057 0.0223 1.0000
8.000 0.9064 0.01213 0.00654 -0.0047 0.0201 1.0000
8.250 0.9262 0.01262 0.00700 -0.0032 0.0161 1.0000
8.500 0.9483 0.01286 0.00727 -0.0021 0.0146 1.0000
8.750 0.9684 0.01333 0.00771 -0.0007 0.0119 1.0000
9.000 0.9883 0.01383 0.00826 0.0007 0.0104 1.0000
9.250 1.0086 0.01426 0.00873 0.0021 0.0092 1.0000
9.500 1.0263 0.01501 0.00953 0.0038 0.0077 1.0000
9.750 1.0447 0.01567 0.01030 0.0055 0.0071 1.0000
10.000 1.0642 0.01621 0.01090 0.0069 0.0065 1.0000
10.250 1.0825 0.01685 0.01162 0.0085 0.0061 1.0000
10.500 1.1005 0.01752 0.01237 0.0101 0.0057 1.0000
10.750 1.1148 0.01858 0.01353 0.0122 0.0051 1.0000
11.000 1.1221 0.02029 0.01547 0.0152 0.0048 1.0000
11.250 1.1390 0.02100 0.01627 0.0168 0.0047 1.0000
11.500 1.1556 0.02170 0.01706 0.0184 0.0045 1.0000
11.750 1.1693 0.02265 0.01812 0.0203 0.0044 1.0000
12.000 1.1825 0.02358 0.01918 0.0223 0.0042 1.0000
12.250 1.1920 0.02475 0.02049 0.0247 0.0041 1.0000
12.500 1.2007 0.02590 0.02177 0.0270 0.0040 1.0000
12.750 1.2089 0.02689 0.02285 0.0295 0.0038 1.0000
13.000 1.2030 0.02851 0.02464 0.0338 0.0038 1.0000
13.250 1.2041 0.02989 0.02614 0.0365 0.0037 1.0000
13.500 1.2026 0.03162 0.02800 0.0388 0.0037 1.0000
13.750 1.1965 0.03395 0.03049 0.0405 0.0036 1.0000
14.000 1.1930 0.03642 0.03308 0.0410 0.0035 1.0000
14.250 1.1852 0.03982 0.03663 0.0403 0.0035 1.0000
14.500 1.1714 0.04477 0.04175 0.0377 0.0034 1.0000
14.750 1.1570 0.05090 0.04804 0.0333 0.0033 1.0000
15.000 1.1258 0.06115 0.05854 0.0257 0.0035 1.0000
15.250 1.0770 0.07545 0.07309 0.0164 0.0037 1.0000
15.500 1.0198 0.09089 0.08872 0.0078 0.0039 1.0000
15.750 0.9688 0.10517 0.10311 0.0005 0.0039 1.0000
16.000 0.9237 0.11857 0.11660 -0.0061 0.0041 1.0000
16.250 0.8587 0.13792 0.13608 -0.0156 0.0045 1.0000
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Polar data table (+)
Polar graphs
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