NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 50,000 Max Cl/Cd: 30.38 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722343-il-50000.txt Download as CSV file: xf-nl722343-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-43 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4739 0.10424 0.09715 -0.0068 1.0000 0.2891
-8.500 -0.4727 0.10158 0.09455 -0.0059 1.0000 0.3086
-8.250 -0.4822 0.09976 0.09285 -0.0052 1.0000 0.3270
-8.000 -0.4588 0.09536 0.08842 -0.0030 1.0000 0.3499
-7.750 -0.4680 0.09387 0.08704 -0.0014 1.0000 0.3732
-7.500 -0.4499 0.09022 0.08341 0.0010 1.0000 0.4023
-7.250 -0.4372 0.08718 0.08041 0.0033 1.0000 0.4322
-7.000 -0.4364 0.08528 0.07859 0.0064 1.0000 0.4657
-5.250 -0.4880 0.03627 0.02980 -0.0233 1.0000 0.2179
-5.000 -0.4668 0.03032 0.02281 -0.0266 1.0000 0.1564
-4.750 -0.4602 0.04102 0.03168 -0.0279 1.0000 0.1281
-4.500 -0.4395 0.03748 0.02805 -0.0270 1.0000 0.1219
-4.250 -0.4141 0.03537 0.02502 -0.0257 1.0000 0.1136
-4.000 -0.3907 0.03314 0.02242 -0.0246 1.0000 0.1134
-3.750 -0.3667 0.03078 0.01982 -0.0235 1.0000 0.1140
-3.500 -0.3417 0.02883 0.01759 -0.0223 1.0000 0.1142
-3.250 -0.3165 0.02693 0.01559 -0.0211 1.0000 0.1160
-3.000 -0.2921 0.02548 0.01415 -0.0195 1.0000 0.1226
-2.750 -0.2684 0.02423 0.01286 -0.0176 1.0000 0.1318
-2.500 -0.0800 0.02015 0.01141 -0.0287 1.0000 1.0000
-2.250 -0.0717 0.01992 0.01095 -0.0261 1.0000 1.0000
-2.000 -0.0642 0.01972 0.01058 -0.0233 1.0000 1.0000
-1.750 -0.0574 0.01953 0.01024 -0.0205 1.0000 1.0000
-1.500 -0.0512 0.01935 0.00995 -0.0175 1.0000 1.0000
-1.250 -0.0458 0.01918 0.00967 -0.0144 1.0000 1.0000
-1.000 -0.0409 0.01901 0.00941 -0.0113 1.0000 1.0000
-0.750 -0.0367 0.01883 0.00914 -0.0081 1.0000 1.0000
-0.500 -0.0326 0.01865 0.00889 -0.0048 1.0000 1.0000
-0.250 -0.0278 0.01847 0.00866 -0.0018 1.0000 1.0000
0.000 -0.0198 0.01835 0.00846 0.0007 1.0000 1.0000
0.250 -0.0067 0.01831 0.00834 0.0023 1.0000 1.0000
0.500 0.0103 0.01836 0.00829 0.0032 1.0000 1.0000
0.750 0.0295 0.01848 0.00833 0.0037 1.0000 1.0000
1.000 0.0501 0.01865 0.00844 0.0040 1.0000 1.0000
1.250 0.0714 0.01888 0.00863 0.0041 1.0000 1.0000
1.500 0.0929 0.01916 0.00889 0.0041 1.0000 1.0000
1.750 0.1145 0.01950 0.00922 0.0041 1.0000 1.0000
2.000 0.1358 0.01990 0.00962 0.0040 1.0000 1.0000
2.250 0.1566 0.02036 0.01012 0.0039 1.0000 1.0000
2.500 0.1768 0.02091 0.01072 0.0037 1.0000 1.0000
2.750 0.1959 0.02155 0.01144 0.0035 1.0000 1.0000
3.000 0.2720 0.02294 0.01309 -0.0071 0.9694 1.0000
3.250 0.3748 0.02327 0.01386 -0.0202 0.9182 1.0000
3.500 0.4731 0.02168 0.01288 -0.0290 0.8508 1.0000
3.750 0.5608 0.01846 0.00968 -0.0304 0.6564 1.0000
4.000 0.5959 0.01986 0.00979 -0.0292 0.5112 1.0000
4.250 0.6252 0.02123 0.01073 -0.0292 0.4578 1.0000
4.500 0.6552 0.02243 0.01179 -0.0295 0.4243 1.0000
4.750 0.6845 0.02360 0.01287 -0.0298 0.3993 1.0000
5.000 0.7126 0.02481 0.01411 -0.0298 0.3789 1.0000
5.250 0.7389 0.02604 0.01543 -0.0297 0.3603 1.0000
5.500 0.7646 0.02736 0.01684 -0.0294 0.3432 1.0000
5.750 0.7894 0.02877 0.01836 -0.0290 0.3268 1.0000
6.000 0.8135 0.03030 0.02007 -0.0284 0.3106 1.0000
6.250 0.8365 0.03194 0.02187 -0.0277 0.2941 1.0000
6.500 0.8589 0.03367 0.02371 -0.0269 0.2767 1.0000
6.750 0.8809 0.03560 0.02572 -0.0260 0.2588 1.0000
7.000 0.8974 0.03775 0.02824 -0.0245 0.2403 1.0000
7.250 0.9132 0.03983 0.03058 -0.0228 0.2193 1.0000
7.500 0.9324 0.04168 0.03235 -0.0215 0.1967 1.0000
7.750 0.9423 0.04436 0.03546 -0.0193 0.1778 1.0000
8.000 0.9529 0.04727 0.03868 -0.0173 0.1617 1.0000
8.250 0.9634 0.05042 0.04205 -0.0156 0.1494 1.0000
8.500 0.9783 0.05307 0.04472 -0.0143 0.1376 1.0000
8.750 0.9690 0.05826 0.05059 -0.0119 0.1349 1.0000
9.000 0.9583 0.06367 0.05643 -0.0102 0.1337 1.0000
9.250 0.9439 0.06921 0.06227 -0.0091 0.1339 1.0000
9.500 0.9263 0.07487 0.06812 -0.0086 0.1350 1.0000
9.750 0.9075 0.08040 0.07373 -0.0084 0.1362 1.0000
10.000 0.8919 0.08601 0.07937 -0.0089 0.1374 1.0000
10.250 0.8827 0.09186 0.08523 -0.0100 0.1383 1.0000
10.500 0.7575 0.12562 0.11860 -0.0461 0.3042 1.0000
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Polar data table (+)
Polar graphs
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