NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M23 AIRFOIL (m23-il) Reynolds number: 200,000 Max Cl/Cd: 76.54 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m23-il-200000.txt Download as CSV file: xf-m23-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M23 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2915 0.10896 0.10557 0.0047 0.7375 0.0258
-8.500 -0.2916 0.10657 0.10319 0.0024 0.7325 0.0259
-8.250 -0.2921 0.10404 0.10066 -0.0001 0.7273 0.0260
-8.000 -0.2923 0.10128 0.09788 -0.0027 0.7230 0.0260
-7.500 -0.2757 0.09050 0.08708 -0.0019 0.7125 0.0265
-7.250 -0.2680 0.08607 0.08260 -0.0010 0.7080 0.0270
-7.000 -0.2633 0.08245 0.07898 -0.0019 0.7029 0.0274
-6.750 -0.3368 0.09236 0.08870 -0.0005 0.7127 0.0265
-6.500 -0.3281 0.08814 0.08443 0.0002 0.7079 0.0269
-6.250 -0.3158 0.08462 0.08089 -0.0011 0.7024 0.0275
-6.000 -0.3016 0.08131 0.07754 -0.0030 0.6969 0.0282
-5.750 -0.2860 0.07817 0.07429 -0.0051 0.6925 0.0293
-5.500 -0.2665 0.07503 0.07110 -0.0079 0.6869 0.0311
-5.250 -0.2309 0.07356 0.06942 -0.0142 0.6814 0.0333
-5.000 -0.1984 0.07186 0.06744 -0.0184 0.6772 0.0337
-4.750 -0.1844 0.06628 0.06185 -0.0194 0.6721 0.0342
-4.500 -0.1736 0.06197 0.05755 -0.0189 0.6671 0.0349
-4.250 -0.1568 0.05886 0.05434 -0.0191 0.6629 0.0360
-4.000 -0.1351 0.05618 0.05160 -0.0202 0.6576 0.0380
-3.750 -0.1086 0.05368 0.04895 -0.0217 0.6523 0.0409
-3.500 -0.0601 0.05415 0.04891 -0.0247 0.6480 0.0439
-3.250 -0.0457 0.04870 0.04345 -0.0252 0.6437 0.0450
-3.000 -0.0279 0.04568 0.04042 -0.0252 0.6383 0.0464
-2.750 -0.0056 0.04349 0.03811 -0.0254 0.6340 0.0489
-2.500 0.0348 0.04360 0.03783 -0.0264 0.6294 0.0559
-2.250 0.0597 0.04012 0.03417 -0.0269 0.6244 0.0573
-2.000 0.0790 0.03737 0.03140 -0.0269 0.6201 0.0590
-1.750 0.1027 0.03562 0.02950 -0.0268 0.6164 0.0622
-1.500 0.1431 0.03620 0.02960 -0.0271 0.6106 0.0703
-1.250 0.1613 0.03240 0.02589 -0.0274 0.6063 0.0727
-1.000 0.1858 0.03092 0.02426 -0.0273 0.6027 0.0768
-0.750 0.2193 0.03019 0.02320 -0.0274 0.5975 0.0856
-0.500 0.2431 0.02823 0.02125 -0.0276 0.5927 0.0885
-0.250 0.2742 0.02794 0.02055 -0.0272 0.5889 0.0997
0.000 0.2987 0.02596 0.01861 -0.0275 0.5846 0.1033
0.250 0.3280 0.02518 0.01765 -0.0276 0.5795 0.1154
0.500 0.3553 0.02432 0.01663 -0.0275 0.5753 0.1295
0.750 0.3825 0.02352 0.01565 -0.0274 0.5718 0.1436
1.000 0.4104 0.02260 0.01474 -0.0277 0.5663 0.1584
1.250 0.4375 0.02164 0.01373 -0.0278 0.5620 0.1747
1.500 0.4773 0.01946 0.01059 -0.0259 0.5590 0.0706
1.750 0.5063 0.01859 0.00968 -0.0260 0.5544 0.0680
2.000 0.5351 0.01793 0.00896 -0.0261 0.5495 0.0670
2.250 0.5631 0.01765 0.00856 -0.0260 0.5458 0.0694
2.500 0.5904 0.01728 0.00810 -0.0257 0.5424 0.0698
2.750 0.6179 0.01694 0.00787 -0.0258 0.5369 0.0702
3.000 0.6441 0.01655 0.00751 -0.0255 0.5326 0.0722
3.250 0.6705 0.01638 0.00731 -0.0251 0.5293 0.0765
3.750 0.7232 0.01616 0.00740 -0.0248 0.5199 0.1782
4.000 0.8236 0.01504 0.00761 -0.0404 0.5145 1.0000
4.250 0.8497 0.01531 0.00791 -0.0404 0.5098 1.0000
4.500 0.8755 0.01550 0.00810 -0.0402 0.5050 1.0000
4.750 0.9009 0.01562 0.00818 -0.0398 0.5012 1.0000
5.000 0.9263 0.01586 0.00839 -0.0396 0.4975 1.0000
5.250 0.9520 0.01615 0.00878 -0.0396 0.4923 1.0000
5.500 0.9774 0.01633 0.00898 -0.0393 0.4882 1.0000
5.750 1.0026 0.01649 0.00908 -0.0388 0.4849 1.0000
6.000 1.0279 0.01682 0.00956 -0.0388 0.4792 1.0000
6.250 1.0530 0.01673 0.00945 -0.0383 0.4725 1.0000
6.500 1.0779 0.01661 0.00939 -0.0378 0.4632 1.0000
6.750 1.1029 0.01635 0.00904 -0.0371 0.4543 1.0000
7.000 1.1277 0.01626 0.00905 -0.0368 0.4439 1.0000
7.250 1.1525 0.01632 0.00919 -0.0364 0.4356 1.0000
7.500 1.1770 0.01614 0.00908 -0.0359 0.4221 1.0000
7.750 1.2012 0.01598 0.00900 -0.0355 0.4029 1.0000
8.000 1.2247 0.01600 0.00904 -0.0350 0.3767 1.0000
8.250 1.2454 0.01649 0.00936 -0.0345 0.3255 1.0000
8.500 1.2428 0.01990 0.01168 -0.0331 0.1614 1.0000
8.750 1.2237 0.02404 0.01509 -0.0302 0.0486 1.0000
9.000 1.2227 0.02610 0.01712 -0.0283 0.0369 1.0000
9.250 1.2211 0.02790 0.01906 -0.0262 0.0341 1.0000
9.500 1.2203 0.02997 0.02125 -0.0247 0.0323 1.0000
9.750 1.2191 0.03237 0.02377 -0.0236 0.0308 1.0000
10.000 1.2161 0.03512 0.02665 -0.0228 0.0297 1.0000
10.250 1.2109 0.03823 0.02990 -0.0222 0.0289 1.0000
10.500 1.2035 0.04165 0.03346 -0.0217 0.0283 1.0000
10.750 1.1975 0.04497 0.03689 -0.0213 0.0280 1.0000
11.000 1.1930 0.04817 0.04020 -0.0209 0.0277 1.0000
11.250 1.1892 0.05128 0.04341 -0.0205 0.0273 1.0000
11.500 1.1864 0.05425 0.04646 -0.0200 0.0268 1.0000
11.750 1.1852 0.05706 0.04934 -0.0195 0.0261 1.0000
12.000 1.1856 0.05971 0.05208 -0.0190 0.0253 1.0000
12.250 1.1880 0.06205 0.05447 -0.0182 0.0248 1.0000
12.500 1.1933 0.06392 0.05638 -0.0170 0.0244 1.0000
12.750 1.2024 0.06523 0.05772 -0.0153 0.0242 1.0000
13.000 1.2165 0.06585 0.05836 -0.0130 0.0240 1.0000
13.250 1.2358 0.06602 0.05859 -0.0102 0.0241 1.0000
13.500 1.2617 0.06596 0.05866 -0.0068 0.0247 1.0000
13.750 1.2850 0.06693 0.05981 -0.0042 0.0250 1.0000
14.000 1.2987 0.06895 0.06201 -0.0028 0.0247 1.0000
14.250 1.3143 0.07154 0.06486 -0.0010 0.0256 1.0000
14.500 1.1325 0.07294 0.06668 0.0080 0.0257 1.0000
14.750 1.1368 0.07578 0.06971 0.0091 0.0257 1.0000
15.000 1.1364 0.07909 0.07322 0.0098 0.0257 1.0000
15.250 1.1335 0.08272 0.07707 0.0106 0.0263 1.0000
15.500 1.1624 0.08439 0.07890 0.0129 0.0293 1.0000
15.750 1.1293 0.08958 0.08445 0.0119 0.0305 1.0000
16.000 1.0935 0.09476 0.08994 0.0109 0.0314 1.0000
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Polar data table (+)
Polar graphs
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