NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M20 AIRFOIL (m20-il) Reynolds number: 100,000 Max Cl/Cd: 56.31 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m20-il-100000-n5.txt Download as CSV file: xf-m20-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M20 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 -0.3218 0.10931 0.10493 -0.0091 0.8487 0.0327
-8.250 -0.3160 0.10633 0.10191 -0.0098 0.8348 0.0334
-8.000 -0.3100 0.10340 0.09894 -0.0108 0.8222 0.0343
-7.750 -0.3038 0.10054 0.09604 -0.0120 0.8109 0.0358
-7.500 -0.2978 0.09778 0.09324 -0.0136 0.8008 0.0377
-7.250 -0.2917 0.09534 0.09077 -0.0166 0.7903 0.0398
-7.000 -0.2793 0.09362 0.08898 -0.0232 0.7808 0.0413
-6.750 -0.2636 0.09149 0.08674 -0.0291 0.7723 0.0417
-6.500 -0.2450 0.08875 0.08389 -0.0340 0.7637 0.0419
-6.250 -0.2266 0.08570 0.08067 -0.0374 0.7565 0.0420
-6.000 -0.2239 0.07923 0.07429 -0.0345 0.7489 0.0430
-5.750 -0.2149 0.07552 0.07055 -0.0329 0.7420 0.0449
-5.500 -0.1986 0.07249 0.06746 -0.0345 0.7342 0.0476
-5.250 -0.1789 0.06952 0.06436 -0.0372 0.7275 0.0504
-5.000 -0.1393 0.06825 0.06275 -0.0452 0.7198 0.0543
-4.500 -0.1077 0.06022 0.05458 -0.0464 0.7069 0.0565
-4.250 -0.0903 0.05739 0.05169 -0.0466 0.7001 0.0597
-4.000 -0.0651 0.05491 0.04901 -0.0485 0.6940 0.0637
-3.750 -0.0181 0.05499 0.04849 -0.0533 0.6867 0.0676
-3.500 -0.0046 0.05003 0.04356 -0.0532 0.6815 0.0688
-3.250 0.0123 0.04705 0.04059 -0.0531 0.6745 0.0716
-3.000 0.0478 0.04657 0.03968 -0.0549 0.6683 0.0813
-2.750 0.0763 0.04423 0.03705 -0.0559 0.6623 0.0825
-2.500 0.0961 0.04091 0.03372 -0.0561 0.6560 0.0839
-2.250 0.1193 0.03870 0.03136 -0.0561 0.6510 0.0858
-2.000 0.1460 0.03687 0.02937 -0.0567 0.6440 0.0884
-1.750 0.1790 0.03598 0.02801 -0.0573 0.6384 0.0976
-1.500 0.2100 0.03250 0.02413 -0.0572 0.6333 0.0692
-1.250 0.2363 0.03056 0.02206 -0.0574 0.6270 0.0614
-1.000 0.2696 0.02850 0.01930 -0.0568 0.6223 0.0544
-0.750 0.2968 0.02697 0.01759 -0.0570 0.6162 0.0536
-0.500 0.3246 0.02566 0.01604 -0.0570 0.6105 0.0530
0.000 0.3812 0.02348 0.01333 -0.0568 0.5995 0.0529
0.250 0.4097 0.02272 0.01226 -0.0566 0.5943 0.0549
0.500 0.4371 0.02191 0.01133 -0.0566 0.5893 0.0567
0.750 0.4654 0.02123 0.01050 -0.0566 0.5832 0.0568
1.000 0.4932 0.02062 0.00974 -0.0564 0.5785 0.0570
1.250 0.5211 0.02013 0.00918 -0.0564 0.5735 0.0576
1.500 0.5488 0.01974 0.00876 -0.0564 0.5677 0.0585
1.750 0.5769 0.01937 0.00831 -0.0562 0.5631 0.0599
2.000 0.6051 0.01916 0.00804 -0.0563 0.5579 0.0620
2.250 0.6320 0.01903 0.00785 -0.0562 0.5526 0.0649
2.500 0.6585 0.01890 0.00763 -0.0559 0.5483 0.0694
2.750 0.6851 0.01891 0.00766 -0.0558 0.5433 0.0825
3.000 0.7115 0.01887 0.00770 -0.0556 0.5380 0.1121
3.250 0.7675 0.01730 0.00777 -0.0618 0.5333 1.0000
3.500 0.7930 0.01756 0.00794 -0.0615 0.5286 1.0000
3.750 0.8184 0.01783 0.00817 -0.0612 0.5233 1.0000
4.000 0.8439 0.01804 0.00831 -0.0608 0.5192 1.0000
4.250 0.8693 0.01831 0.00854 -0.0605 0.5150 1.0000
4.500 0.8944 0.01866 0.00893 -0.0603 0.5099 1.0000
4.750 0.9197 0.01892 0.00919 -0.0600 0.5056 1.0000
5.250 0.9699 0.01958 0.00994 -0.0595 0.4967 1.0000
5.500 0.9949 0.01992 0.01033 -0.0592 0.4922 1.0000
5.750 1.0204 0.02017 0.01061 -0.0589 0.4886 1.0000
6.000 1.0448 0.02061 0.01117 -0.0587 0.4838 1.0000
6.250 1.0692 0.02104 0.01173 -0.0584 0.4790 1.0000
6.500 1.0943 0.02134 0.01213 -0.0581 0.4750 1.0000
6.750 1.1190 0.02171 0.01262 -0.0578 0.4705 1.0000
7.000 1.1424 0.02211 0.01320 -0.0574 0.4635 1.0000
7.250 1.1658 0.02181 0.01294 -0.0565 0.4477 1.0000
7.500 1.1883 0.02148 0.01262 -0.0553 0.4275 1.0000
7.750 1.2085 0.02158 0.01283 -0.0543 0.4039 1.0000
8.000 1.2281 0.02181 0.01314 -0.0533 0.3777 1.0000
8.250 1.2440 0.02233 0.01360 -0.0519 0.3327 1.0000
8.500 1.2475 0.02394 0.01464 -0.0494 0.2395 1.0000
8.750 1.2308 0.02741 0.01732 -0.0458 0.1409 1.0000
9.000 1.2070 0.03104 0.02046 -0.0418 0.0653 1.0000
9.250 1.1944 0.03420 0.02350 -0.0397 0.0433 1.0000
9.500 1.1903 0.03700 0.02637 -0.0386 0.0382 1.0000
9.750 1.1891 0.03969 0.02919 -0.0378 0.0354 1.0000
10.000 1.1877 0.04250 0.03216 -0.0371 0.0331 1.0000
10.250 1.1845 0.04559 0.03540 -0.0366 0.0311 1.0000
10.500 1.1787 0.04903 0.03898 -0.0362 0.0295 1.0000
10.750 1.1708 0.05282 0.04291 -0.0360 0.0282 1.0000
11.000 1.1675 0.05612 0.04637 -0.0358 0.0275 1.0000
11.250 1.1638 0.05952 0.04993 -0.0356 0.0269 1.0000
11.500 1.1598 0.06296 0.05353 -0.0355 0.0263 1.0000
11.750 1.1562 0.06636 0.05707 -0.0353 0.0258 1.0000
12.000 1.1538 0.06962 0.06047 -0.0351 0.0251 1.0000
12.250 1.1533 0.07261 0.06358 -0.0348 0.0242 1.0000
12.500 1.1547 0.07530 0.06639 -0.0344 0.0231 1.0000
12.750 1.1580 0.07761 0.06874 -0.0337 0.0219 1.0000
13.000 1.1645 0.07920 0.07033 -0.0324 0.0209 1.0000
13.250 1.1811 0.07893 0.06998 -0.0292 0.0200 1.0000
13.500 1.2132 0.07711 0.06807 -0.0242 0.0192 1.0000
13.750 1.2275 0.07855 0.06967 -0.0228 0.0188 1.0000
14.000 1.2366 0.08069 0.07202 -0.0220 0.0182 1.0000
14.250 1.2434 0.08317 0.07475 -0.0215 0.0175 1.0000
14.500 1.2489 0.08589 0.07769 -0.0211 0.0169 1.0000
14.750 1.2538 0.08882 0.08083 -0.0206 0.0164 1.0000
15.000 1.2560 0.09218 0.08443 -0.0205 0.0163 1.0000
15.250 1.2543 0.09605 0.08854 -0.0208 0.0161 1.0000
15.500 1.2498 0.10035 0.09309 -0.0215 0.0160 1.0000
15.750 1.2430 0.10506 0.09803 -0.0227 0.0160 1.0000
16.000 1.2342 0.11015 0.10337 -0.0243 0.0160 1.0000
16.250 1.2238 0.11562 0.10908 -0.0264 0.0160 1.0000
16.500 1.2123 0.12149 0.11518 -0.0290 0.0160 1.0000
16.750 1.1998 0.12777 0.12168 -0.0321 0.0161 1.0000
17.000 1.1864 0.13451 0.12863 -0.0357 0.0161 1.0000
17.250 1.1724 0.14174 0.13606 -0.0398 0.0162 1.0000
17.500 1.1578 0.14950 0.14401 -0.0445 0.0164 1.0000
17.750 1.1428 0.15790 0.15258 -0.0498 0.0165 1.0000
18.000 1.1274 0.16705 0.16189 -0.0558 0.0167 1.0000
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