NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 200,000 Max Cl/Cd: 67.91 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m24-il-200000.txt Download as CSV file: xf-m24-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M24 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2225 0.10379 0.10003 -0.0161 0.7056 0.0409
-8.750 -0.2297 0.10117 0.09739 -0.0196 0.7025 0.0410
-8.500 -0.3016 0.10524 0.10134 -0.0049 0.7116 0.0402
-8.250 -0.3059 0.10292 0.09903 -0.0119 0.7069 0.0408
-8.000 -0.3110 0.10078 0.09682 -0.0172 0.7029 0.0410
-7.750 -0.3044 0.09649 0.09250 -0.0187 0.6986 0.0413
-7.500 -0.2912 0.09202 0.08805 -0.0162 0.6927 0.0417
-7.250 -0.2811 0.08873 0.08472 -0.0157 0.6879 0.0424
-7.000 -0.2721 0.08584 0.08176 -0.0164 0.6840 0.0432
-6.750 -0.2614 0.08287 0.07879 -0.0182 0.6787 0.0444
-6.500 -0.2502 0.07988 0.07575 -0.0203 0.6739 0.0458
-6.250 -0.2366 0.07700 0.07275 -0.0232 0.6699 0.0476
-6.000 -0.2113 0.07572 0.07110 -0.0308 0.6663 0.0490
-5.750 -0.2032 0.07046 0.06594 -0.0299 0.6611 0.0496
-5.500 -0.1906 0.06719 0.06266 -0.0293 0.6564 0.0502
-5.250 -0.1759 0.06446 0.05985 -0.0291 0.6526 0.0511
-5.000 -0.1584 0.06192 0.05723 -0.0297 0.6481 0.0525
-4.750 -0.1382 0.05944 0.05467 -0.0308 0.6430 0.0549
-4.500 -0.1045 0.05771 0.05247 -0.0338 0.6389 0.0588
-4.250 -0.0915 0.05406 0.04880 -0.0332 0.6354 0.0595
-4.000 -0.0741 0.05152 0.04626 -0.0331 0.6307 0.0606
-3.750 -0.0540 0.04935 0.04404 -0.0331 0.6257 0.0622
-3.500 -0.0317 0.04734 0.04188 -0.0331 0.6215 0.0649
-3.250 0.0022 0.04626 0.04021 -0.0334 0.6183 0.0702
-3.000 0.0196 0.04302 0.03707 -0.0335 0.6134 0.0713
-2.750 0.0401 0.04098 0.03502 -0.0332 0.6086 0.0729
-2.500 0.0628 0.03938 0.03329 -0.0329 0.6046 0.0763
-2.250 0.0936 0.03839 0.03176 -0.0323 0.6014 0.0838
-2.000 0.1148 0.03597 0.02944 -0.0325 0.5961 0.0854
-1.750 0.1380 0.03439 0.02781 -0.0322 0.5915 0.0880
-1.500 0.1642 0.03323 0.02644 -0.0318 0.5878 0.0937
-1.250 0.1910 0.03174 0.02460 -0.0312 0.5843 0.0999
-1.000 0.2155 0.03028 0.02318 -0.0313 0.5790 0.1030
-0.750 0.2449 0.02987 0.02240 -0.0307 0.5746 0.1144
-0.500 0.2687 0.02795 0.02045 -0.0305 0.5711 0.1173
-0.250 0.2963 0.02746 0.01970 -0.0301 0.5673 0.1309
0.000 0.3216 0.02605 0.01839 -0.0303 0.5620 0.1364
0.250 0.3487 0.02517 0.01734 -0.0300 0.5578 0.1497
0.500 0.3909 0.02081 0.01186 -0.0283 0.5550 0.0669
0.750 0.4205 0.01996 0.01082 -0.0283 0.5515 0.0659
1.000 0.4499 0.01933 0.01014 -0.0285 0.5462 0.0661
1.250 0.4786 0.01890 0.00962 -0.0285 0.5419 0.0682
1.500 0.5067 0.01840 0.00901 -0.0284 0.5384 0.0706
1.750 0.5335 0.01801 0.00867 -0.0282 0.5344 0.0731
2.000 0.5599 0.01781 0.00856 -0.0280 0.5295 0.0770
2.250 0.5863 0.01761 0.00832 -0.0277 0.5255 0.0828
2.500 0.6118 0.01732 0.00803 -0.0271 0.5223 0.0982
2.750 0.6337 0.01693 0.00801 -0.0260 0.5182 0.2066
3.000 0.8095 0.01616 0.00875 -0.0566 0.5094 1.0000
3.250 0.8353 0.01625 0.00870 -0.0563 0.5063 1.0000
3.500 0.8610 0.01648 0.00892 -0.0562 0.5021 1.0000
3.750 0.8866 0.01667 0.00912 -0.0561 0.4972 1.0000
4.000 0.9120 0.01677 0.00915 -0.0558 0.4933 1.0000
4.250 0.9376 0.01688 0.00915 -0.0555 0.4901 1.0000
4.500 0.9626 0.01717 0.00950 -0.0554 0.4858 1.0000
4.750 0.9875 0.01742 0.00979 -0.0552 0.4813 1.0000
5.000 1.0126 0.01758 0.00992 -0.0549 0.4777 1.0000
5.250 1.0379 0.01772 0.00997 -0.0546 0.4747 1.0000
5.500 1.0621 0.01806 0.01037 -0.0544 0.4705 1.0000
5.750 1.0860 0.01835 0.01074 -0.0541 0.4659 1.0000
6.000 1.1105 0.01855 0.01093 -0.0538 0.4623 1.0000
6.250 1.1355 0.01873 0.01106 -0.0534 0.4594 1.0000
6.500 1.1593 0.01911 0.01148 -0.0531 0.4560 1.0000
6.750 1.1817 0.01955 0.01206 -0.0527 0.4516 1.0000
7.000 1.2051 0.01983 0.01240 -0.0523 0.4478 1.0000
7.250 1.2297 0.02000 0.01254 -0.0519 0.4447 1.0000
7.500 1.2546 0.02028 0.01278 -0.0515 0.4419 1.0000
7.750 1.2742 0.02090 0.01361 -0.0509 0.4376 1.0000
8.000 1.2959 0.02129 0.01412 -0.0503 0.4336 1.0000
8.250 1.3205 0.02126 0.01405 -0.0498 0.4293 1.0000
8.500 1.3426 0.02142 0.01424 -0.0491 0.4240 1.0000
8.750 1.3626 0.02151 0.01443 -0.0481 0.4171 1.0000
9.000 1.3884 0.02132 0.01414 -0.0476 0.4120 1.0000
9.250 1.4051 0.02175 0.01478 -0.0464 0.4059 1.0000
9.500 1.4265 0.02172 0.01478 -0.0455 0.3995 1.0000
9.750 1.4452 0.02179 0.01489 -0.0443 0.3919 1.0000
10.000 1.4633 0.02177 0.01494 -0.0429 0.3837 1.0000
10.250 1.4778 0.02198 0.01524 -0.0412 0.3748 1.0000
10.500 1.4948 0.02201 0.01524 -0.0397 0.3658 1.0000
10.750 1.5021 0.02250 0.01592 -0.0370 0.3564 1.0000
11.000 1.5082 0.02292 0.01640 -0.0341 0.3450 1.0000
11.250 1.5093 0.02351 0.01701 -0.0306 0.3333 1.0000
11.500 1.4983 0.02446 0.01802 -0.0256 0.3229 1.0000
11.750 1.4858 0.02591 0.01951 -0.0215 0.3096 1.0000
12.000 1.4753 0.02785 0.02146 -0.0186 0.2935 1.0000
12.250 1.4614 0.03053 0.02411 -0.0163 0.2716 1.0000
12.500 1.4429 0.03400 0.02748 -0.0145 0.2450 1.0000
12.750 1.4200 0.03818 0.03153 -0.0129 0.2153 1.0000
13.000 1.3940 0.04293 0.03614 -0.0117 0.1884 1.0000
13.250 1.3676 0.04795 0.04105 -0.0108 0.1656 1.0000
13.500 1.3412 0.05336 0.04635 -0.0103 0.1411 1.0000
13.750 1.3130 0.05927 0.05214 -0.0101 0.1119 1.0000
14.000 1.2860 0.06531 0.05805 -0.0102 0.0895 1.0000
14.250 1.2632 0.07103 0.06369 -0.0105 0.0724 1.0000
14.500 1.2442 0.07646 0.06906 -0.0108 0.0565 1.0000
14.750 1.2299 0.08144 0.07402 -0.0113 0.0483 1.0000
15.000 1.2196 0.08597 0.07859 -0.0118 0.0440 1.0000
15.250 1.2107 0.09041 0.08307 -0.0123 0.0412 1.0000
15.500 1.2009 0.09505 0.08777 -0.0130 0.0392 1.0000
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Polar data table (+)
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