NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M23 AIRFOIL (m23-il) Reynolds number: 100,000 Max Cl/Cd: 53.31 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m23-il-100000-n5.txt Download as CSV file: xf-m23-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3642 0.11439 0.10981 0.0127 0.7410 0.0277
-8.250 -0.3574 0.11118 0.10660 0.0112 0.7346 0.0283
-8.000 -0.3512 0.10812 0.10349 0.0098 0.7294 0.0291
-7.750 -0.3439 0.10501 0.10040 0.0078 0.7228 0.0304
-7.500 -0.3375 0.10209 0.09746 0.0056 0.7172 0.0318
-7.250 -0.3314 0.09968 0.09502 0.0026 0.7119 0.0333
-7.000 -0.3186 0.09786 0.09315 -0.0030 0.7058 0.0343
-6.750 -0.3038 0.09582 0.09102 -0.0081 0.7009 0.0347
-6.500 -0.2861 0.09328 0.08838 -0.0125 0.6955 0.0349
-6.250 -0.2672 0.09028 0.08526 -0.0159 0.6899 0.0350
-6.000 -0.2543 0.08549 0.08043 -0.0173 0.6856 0.0353
-5.750 -0.2508 0.07950 0.07448 -0.0146 0.6805 0.0365
-5.500 -0.2383 0.07598 0.07093 -0.0148 0.6750 0.0385
-5.250 -0.2211 0.07296 0.06780 -0.0164 0.6706 0.0411
-5.000 -0.1990 0.06999 0.06472 -0.0192 0.6653 0.0440
-4.750 -0.1573 0.06935 0.06371 -0.0257 0.6598 0.0470
-4.250 -0.1292 0.06068 0.05496 -0.0259 0.6509 0.0496
-4.000 -0.1092 0.05793 0.05211 -0.0267 0.6455 0.0536
-3.750 -0.0660 0.05783 0.05151 -0.0304 0.6411 0.0596
-3.500 -0.0441 0.05401 0.04755 -0.0313 0.6365 0.0606
-3.250 -0.0297 0.05015 0.04374 -0.0311 0.6313 0.0626
-3.000 -0.0072 0.04798 0.04143 -0.0313 0.6270 0.0688
-2.750 0.0313 0.04719 0.04013 -0.0331 0.6226 0.0743
-2.500 0.0499 0.04369 0.03665 -0.0332 0.6173 0.0761
-2.250 0.0732 0.04146 0.03428 -0.0333 0.6129 0.0790
-2.000 0.1118 0.04213 0.03433 -0.0338 0.6091 0.0885
-1.500 0.1547 0.03631 0.02850 -0.0343 0.5991 0.0955
-1.250 0.1893 0.03625 0.02788 -0.0343 0.5954 0.1034
-1.000 0.2218 0.03198 0.02321 -0.0340 0.5909 0.0590
-0.750 0.2482 0.03025 0.02134 -0.0341 0.5861 0.0570
-0.500 0.2762 0.02878 0.01959 -0.0339 0.5822 0.0557
-0.250 0.3054 0.02761 0.01810 -0.0338 0.5781 0.0577
0.000 0.3343 0.02644 0.01672 -0.0339 0.5729 0.0570
0.250 0.3629 0.02531 0.01534 -0.0338 0.5688 0.0557
0.500 0.3913 0.02427 0.01401 -0.0335 0.5654 0.0546
0.750 0.4208 0.02343 0.01301 -0.0338 0.5601 0.0539
1.000 0.4497 0.02266 0.01205 -0.0338 0.5555 0.0535
1.250 0.4783 0.02196 0.01115 -0.0337 0.5519 0.0534
1.500 0.5072 0.02145 0.01052 -0.0338 0.5476 0.0539
1.750 0.5360 0.02105 0.01008 -0.0341 0.5425 0.0548
2.000 0.5666 0.02070 0.00963 -0.0345 0.5385 0.0574
2.250 0.5955 0.02041 0.00922 -0.0346 0.5352 0.0617
2.500 0.6224 0.02036 0.00923 -0.0348 0.5297 0.0649
2.750 0.6485 0.02026 0.00906 -0.0345 0.5254 0.0676
3.000 0.6744 0.02017 0.00885 -0.0341 0.5220 0.0715
3.250 0.7007 0.02024 0.00894 -0.0340 0.5174 0.0786
3.500 0.7269 0.02032 0.00909 -0.0340 0.5126 0.1041
4.000 0.8365 0.01926 0.00958 -0.0459 0.5034 1.0000
4.250 0.8616 0.01961 0.00995 -0.0458 0.4984 1.0000
4.500 0.8865 0.01983 0.01013 -0.0454 0.4945 1.0000
4.750 0.9114 0.01997 0.01020 -0.0449 0.4914 1.0000
5.000 0.9360 0.02046 0.01079 -0.0449 0.4858 1.0000
5.250 0.9605 0.02078 0.01117 -0.0446 0.4815 1.0000
5.500 0.9852 0.02098 0.01136 -0.0442 0.4781 1.0000
5.750 1.0094 0.02138 0.01184 -0.0439 0.4737 1.0000
6.000 1.0333 0.02184 0.01245 -0.0438 0.4686 1.0000
6.250 1.0576 0.02213 0.01279 -0.0434 0.4649 1.0000
6.500 1.0824 0.02230 0.01299 -0.0428 0.4619 1.0000
6.750 1.1046 0.02301 0.01394 -0.0428 0.4558 1.0000
7.000 1.1295 0.02275 0.01368 -0.0419 0.4479 1.0000
7.250 1.1523 0.02259 0.01361 -0.0411 0.4341 1.0000
7.500 1.1745 0.02267 0.01382 -0.0405 0.4211 1.0000
7.750 1.1964 0.02288 0.01418 -0.0399 0.4092 1.0000
8.000 1.2175 0.02284 0.01421 -0.0390 0.3896 1.0000
8.250 1.2358 0.02324 0.01471 -0.0381 0.3639 1.0000
8.500 1.2523 0.02384 0.01535 -0.0371 0.3345 1.0000
8.750 1.2579 0.02528 0.01645 -0.0354 0.2694 1.0000
9.000 1.2386 0.02877 0.01925 -0.0325 0.1785 1.0000
9.250 1.2139 0.03263 0.02280 -0.0300 0.1298 1.0000
9.500 1.1902 0.03699 0.02691 -0.0284 0.0851 1.0000
9.750 1.1683 0.04165 0.03134 -0.0274 0.0497 1.0000
10.000 1.1560 0.04556 0.03520 -0.0268 0.0359 1.0000
10.250 1.1499 0.04894 0.03863 -0.0264 0.0313 1.0000
10.500 1.1444 0.05232 0.04208 -0.0260 0.0290 1.0000
10.750 1.1412 0.05552 0.04543 -0.0258 0.0276 1.0000
11.000 1.1376 0.05883 0.04889 -0.0256 0.0265 1.0000
11.250 1.1335 0.06226 0.05250 -0.0255 0.0256 1.0000
11.500 1.1288 0.06584 0.05623 -0.0255 0.0246 1.0000
11.750 1.1239 0.06960 0.06012 -0.0257 0.0236 1.0000
12.000 1.1179 0.07356 0.06421 -0.0260 0.0227 1.0000
12.250 1.1111 0.07772 0.06850 -0.0264 0.0218 1.0000
12.500 1.1053 0.08176 0.07264 -0.0268 0.0211 1.0000
12.750 1.1040 0.08521 0.07623 -0.0270 0.0207 1.0000
13.000 1.1036 0.08845 0.07960 -0.0271 0.0203 1.0000
13.250 1.1058 0.09119 0.08246 -0.0270 0.0199 1.0000
13.500 1.1124 0.09299 0.08436 -0.0262 0.0195 1.0000
13.750 1.1244 0.09365 0.08509 -0.0246 0.0190 1.0000
14.000 1.1397 0.09373 0.08525 -0.0226 0.0181 1.0000
14.250 1.1540 0.09415 0.08573 -0.0208 0.0170 1.0000
14.500 1.1680 0.09478 0.08641 -0.0191 0.0160 1.0000
14.750 1.1841 0.09522 0.08693 -0.0169 0.0156 1.0000
15.000 1.1984 0.09624 0.08808 -0.0151 0.0152 1.0000
15.250 1.2094 0.09801 0.09001 -0.0138 0.0150 1.0000
15.500 1.2169 0.10048 0.09266 -0.0130 0.0148 1.0000
15.750 1.2202 0.10367 0.09606 -0.0129 0.0147 1.0000
16.000 1.2200 0.10745 0.10010 -0.0133 0.0147 1.0000
16.250 1.2167 0.11174 0.10462 -0.0143 0.0147 1.0000
16.500 1.2111 0.11642 0.10953 -0.0157 0.0146 1.0000
16.750 1.2037 0.12149 0.11481 -0.0176 0.0146 1.0000
17.000 1.1949 0.12693 0.12046 -0.0199 0.0145 1.0000
17.250 1.1851 0.13272 0.12646 -0.0227 0.0145 1.0000
17.500 1.1744 0.13889 0.13284 -0.0259 0.0144 1.0000
17.750 1.1630 0.14548 0.13962 -0.0296 0.0145 1.0000
18.000 1.1508 0.15257 0.14691 -0.0339 0.0145 1.0000
18.250 1.1376 0.16037 0.15491 -0.0387 0.0147 1.0000
18.500 1.1226 0.16933 0.16407 -0.0445 0.0149 1.0000
18.750 1.0994 0.18213 0.17705 -0.0528 0.0156 1.0000
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