NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.55 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0009sm-il-1000000-n5.txt Download as CSV file: xf-n0009sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9702 0.11673 0.11456 0.0038 1.0000 0.0024
-16.250 -1.1286 0.08125 0.07874 -0.0149 1.0000 0.0021
-16.000 -1.1865 0.06550 0.06275 -0.0246 1.0000 0.0020
-15.750 -1.2351 0.05212 0.04908 -0.0344 1.0000 0.0019
-15.500 -1.2534 0.04559 0.04238 -0.0388 1.0000 0.0019
-15.250 -1.2645 0.04101 0.03765 -0.0412 1.0000 0.0020
-15.000 -1.2708 0.03763 0.03414 -0.0421 1.0000 0.0021
-14.750 -1.2794 0.03450 0.03084 -0.0420 1.0000 0.0020
-14.500 -1.2834 0.03220 0.02838 -0.0408 1.0000 0.0020
-14.250 -1.2822 0.03055 0.02663 -0.0392 1.0000 0.0021
-14.000 -1.2832 0.02890 0.02484 -0.0368 1.0000 0.0021
-13.750 -1.2794 0.02770 0.02354 -0.0343 1.0000 0.0022
-13.500 -1.2772 0.02653 0.02225 -0.0312 1.0000 0.0022
-13.250 -1.2719 0.02557 0.02120 -0.0282 1.0000 0.0023
-13.000 -1.2629 0.02452 0.02004 -0.0259 1.0000 0.0024
-12.750 -1.2521 0.02351 0.01892 -0.0237 1.0000 0.0025
-12.500 -1.2392 0.02262 0.01792 -0.0218 1.0000 0.0025
-12.250 -1.2250 0.02179 0.01699 -0.0200 1.0000 0.0026
-12.000 -1.2098 0.02100 0.01610 -0.0182 1.0000 0.0027
-11.750 -1.1938 0.02024 0.01525 -0.0166 1.0000 0.0028
-11.500 -1.1775 0.01948 0.01438 -0.0149 1.0000 0.0029
-11.250 -1.1614 0.01865 0.01345 -0.0132 1.0000 0.0031
-11.000 -1.1440 0.01794 0.01267 -0.0116 1.0000 0.0034
-10.750 -1.1259 0.01730 0.01197 -0.0101 1.0000 0.0036
-10.500 -1.1071 0.01672 0.01132 -0.0087 1.0000 0.0039
-10.250 -1.0879 0.01617 0.01071 -0.0073 1.0000 0.0042
-10.000 -1.0682 0.01568 0.01015 -0.0059 1.0000 0.0045
-9.750 -1.0481 0.01521 0.00962 -0.0046 1.0000 0.0048
-9.500 -1.0288 0.01465 0.00900 -0.0031 1.0000 0.0055
-9.250 -1.0089 0.01417 0.00847 -0.0017 1.0000 0.0061
-9.000 -0.9885 0.01373 0.00800 -0.0004 1.0000 0.0068
-8.750 -0.9680 0.01332 0.00754 0.0009 1.0000 0.0078
-8.500 -0.9479 0.01286 0.00708 0.0023 1.0000 0.0094
-8.250 -0.9270 0.01249 0.00668 0.0036 1.0000 0.0107
-8.000 -0.9065 0.01209 0.00629 0.0050 1.0000 0.0135
-7.750 -0.8852 0.01177 0.00596 0.0062 1.0000 0.0155
-7.500 -0.8639 0.01145 0.00562 0.0075 1.0000 0.0177
-7.250 -0.8427 0.01115 0.00534 0.0087 1.0000 0.0206
-7.000 -0.8129 0.01090 0.00507 0.0081 0.9991 0.0226
-6.750 -0.7818 0.01061 0.00477 0.0073 0.9978 0.0252
-6.500 -0.7506 0.01033 0.00450 0.0064 0.9962 0.0281
-6.250 -0.7186 0.01009 0.00425 0.0053 0.9946 0.0303
-6.000 -0.6870 0.00989 0.00402 0.0044 0.9930 0.0318
-5.750 -0.6574 0.00963 0.00375 0.0040 0.9907 0.0350
-5.500 -0.6269 0.00937 0.00353 0.0033 0.9882 0.0392
-5.250 -0.5953 0.00917 0.00332 0.0024 0.9857 0.0417
-5.000 -0.5627 0.00898 0.00310 0.0013 0.9836 0.0437
-4.750 -0.5295 0.00874 0.00288 0.0001 0.9817 0.0490
-4.500 -0.5022 0.00853 0.00269 0.0002 0.9767 0.0533
-4.250 -0.4714 0.00833 0.00251 -0.0004 0.9727 0.0592
-4.000 -0.4384 0.00812 0.00232 -0.0016 0.9694 0.0665
-3.750 -0.4078 0.00790 0.00215 -0.0022 0.9640 0.0763
-3.500 -0.3745 0.00768 0.00198 -0.0034 0.9583 0.0903
-3.250 -0.3402 0.00739 0.00180 -0.0050 0.9518 0.1150
-3.000 -0.3061 0.00709 0.00162 -0.0064 0.9418 0.1498
-2.750 -0.2727 0.00683 0.00146 -0.0077 0.9277 0.1806
-2.500 -0.2421 0.00662 0.00132 -0.0083 0.9092 0.2113
-2.250 -0.2146 0.00644 0.00120 -0.0082 0.8865 0.2471
-2.000 -0.1894 0.00627 0.00109 -0.0076 0.8598 0.2874
-1.750 -0.1649 0.00620 0.00101 -0.0068 0.8289 0.3164
-1.500 -0.1413 0.00611 0.00094 -0.0058 0.7965 0.3535
-1.250 -0.1175 0.00603 0.00088 -0.0048 0.7661 0.3903
-1.000 -0.0950 0.00587 0.00083 -0.0037 0.7333 0.4495
-0.750 -0.0725 0.00576 0.00079 -0.0025 0.6987 0.5061
-0.500 -0.0485 0.00574 0.00077 -0.0017 0.6658 0.5383
-0.250 -0.0242 0.00573 0.00076 -0.0008 0.6343 0.5698
0.000 -0.0001 0.00574 0.00075 0.0000 0.6008 0.6012
0.250 0.0241 0.00574 0.00076 0.0008 0.5684 0.6332
0.500 0.0484 0.00574 0.00077 0.0017 0.5385 0.6662
0.750 0.0726 0.00575 0.00079 0.0025 0.5073 0.6988
1.000 0.0950 0.00588 0.00083 0.0037 0.4488 0.7330
1.250 0.1175 0.00603 0.00088 0.0048 0.3897 0.7655
1.500 0.1414 0.00610 0.00094 0.0058 0.3558 0.7966
1.750 0.1648 0.00619 0.00101 0.0068 0.3169 0.8289
2.000 0.1893 0.00627 0.00109 0.0076 0.2866 0.8601
2.250 0.2146 0.00643 0.00120 0.0082 0.2475 0.8863
2.500 0.2421 0.00662 0.00132 0.0083 0.2114 0.9092
2.750 0.2727 0.00683 0.00146 0.0077 0.1806 0.9278
3.000 0.3060 0.00709 0.00162 0.0064 0.1497 0.9418
3.250 0.3402 0.00740 0.00180 0.0049 0.1141 0.9519
3.500 0.3746 0.00768 0.00198 0.0034 0.0901 0.9584
3.750 0.4078 0.00790 0.00215 0.0022 0.0763 0.9640
4.000 0.4385 0.00812 0.00232 0.0016 0.0665 0.9695
4.250 0.4716 0.00833 0.00250 0.0004 0.0593 0.9727
4.500 0.5023 0.00854 0.00269 -0.0003 0.0532 0.9768
4.750 0.5297 0.00874 0.00288 -0.0001 0.0489 0.9817
5.000 0.5629 0.00898 0.00310 -0.0014 0.0436 0.9836
5.250 0.5954 0.00917 0.00331 -0.0024 0.0417 0.9858
5.500 0.6271 0.00937 0.00353 -0.0033 0.0393 0.9882
5.750 0.6576 0.00963 0.00375 -0.0040 0.0350 0.9907
6.000 0.6872 0.00989 0.00402 -0.0045 0.0317 0.9931
6.250 0.7189 0.01009 0.00425 -0.0054 0.0303 0.9947
6.500 0.7508 0.01033 0.00450 -0.0064 0.0281 0.9963
6.750 0.7821 0.01061 0.00476 -0.0073 0.0252 0.9979
7.000 0.8132 0.01089 0.00506 -0.0082 0.0225 0.9992
7.250 0.8424 0.01115 0.00533 -0.0087 0.0204 1.0000
7.500 0.8637 0.01146 0.00561 -0.0074 0.0176 1.0000
7.750 0.8851 0.01176 0.00595 -0.0062 0.0155 1.0000
8.000 0.9063 0.01209 0.00629 -0.0049 0.0135 1.0000
8.250 0.9269 0.01249 0.00668 -0.0036 0.0109 1.0000
8.500 0.9478 0.01286 0.00708 -0.0023 0.0095 1.0000
8.750 0.9678 0.01333 0.00755 -0.0009 0.0077 1.0000
9.000 0.9884 0.01373 0.00800 0.0004 0.0068 1.0000
9.250 1.0088 0.01417 0.00847 0.0017 0.0061 1.0000
9.500 1.0287 0.01466 0.00900 0.0031 0.0055 1.0000
9.750 1.0481 0.01521 0.00963 0.0046 0.0048 1.0000
10.000 1.0682 0.01568 0.01015 0.0059 0.0045 1.0000
10.250 1.0879 0.01618 0.01072 0.0073 0.0043 1.0000
10.500 1.1072 0.01672 0.01132 0.0086 0.0040 1.0000
10.750 1.1259 0.01731 0.01197 0.0101 0.0036 1.0000
11.000 1.1442 0.01794 0.01267 0.0116 0.0034 1.0000
11.250 1.1617 0.01864 0.01345 0.0131 0.0031 1.0000
11.500 1.1777 0.01948 0.01438 0.0149 0.0029 1.0000
11.750 1.1936 0.02029 0.01531 0.0166 0.0028 1.0000
12.000 1.2102 0.02099 0.01610 0.0182 0.0027 1.0000
12.250 1.2251 0.02182 0.01702 0.0199 0.0026 1.0000
12.500 1.2394 0.02265 0.01795 0.0217 0.0026 1.0000
12.750 1.2529 0.02350 0.01889 0.0236 0.0025 1.0000
13.000 1.2630 0.02457 0.02010 0.0258 0.0024 1.0000
13.250 1.2728 0.02557 0.02120 0.0281 0.0024 1.0000
13.500 1.2772 0.02660 0.02233 0.0312 0.0023 1.0000
13.750 1.2792 0.02780 0.02365 0.0343 0.0023 1.0000
14.000 1.2816 0.02910 0.02507 0.0369 0.0022 1.0000
14.250 1.2837 0.03054 0.02662 0.0390 0.0022 1.0000
14.500 1.2810 0.03252 0.02874 0.0408 0.0021 1.0000
14.750 1.2794 0.03465 0.03101 0.0417 0.0020 1.0000
15.000 1.2722 0.03766 0.03417 0.0418 0.0020 1.0000
15.250 1.2633 0.04140 0.03806 0.0407 0.0020 1.0000
15.500 1.2506 0.04632 0.04315 0.0379 0.0021 1.0000
15.750 1.2301 0.05341 0.05043 0.0330 0.0020 1.0000
16.000 1.2003 0.06317 0.06039 0.0259 0.0020 1.0000
16.250 1.0949 0.08849 0.08608 0.0104 0.0022 1.0000
16.500 0.9549 0.12045 0.11831 -0.0062 0.0026 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA-0009 9.0% smoothed (n0009sm-il)