NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 500,000 Max Cl/Cd: 103.53 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m18-il-500000.txt Download as CSV file: xf-m18-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4127 0.10622 0.10410 -0.0100 1.0000 0.0292
-9.500 -0.4063 0.10296 0.10082 -0.0120 0.9397 0.0297
-9.250 -0.4070 0.10014 0.09788 -0.0119 0.8975 0.0303
-9.000 -0.3339 0.08261 0.08015 -0.0286 0.8184 0.0333
-8.750 -0.3290 0.07944 0.07692 -0.0275 0.8056 0.0336
-8.500 -0.3249 0.07646 0.07389 -0.0276 0.7936 0.0339
-8.250 -0.3222 0.07325 0.07064 -0.0283 0.7818 0.0341
-8.000 -0.3220 0.06975 0.06711 -0.0295 0.7713 0.0344
-7.750 -0.3276 0.06561 0.06292 -0.0322 0.7618 0.0347
-7.500 -0.4171 0.06961 0.06678 -0.0322 0.7815 0.0342
-7.250 -0.4071 0.06682 0.06390 -0.0330 0.7698 0.0346
-7.000 -0.3964 0.06384 0.06082 -0.0339 0.7591 0.0351
-6.750 -0.3846 0.06057 0.05744 -0.0350 0.7485 0.0360
-6.500 -0.3718 0.05200 0.04833 -0.0388 0.7412 0.0393
-6.250 -0.3668 0.04728 0.04354 -0.0384 0.7324 0.0400
-6.000 -0.3497 0.04567 0.04185 -0.0380 0.7239 0.0404
-5.750 -0.3313 0.04408 0.04018 -0.0377 0.7154 0.0410
-5.500 -0.3124 0.04219 0.03817 -0.0374 0.7078 0.0419
-5.250 -0.2902 0.03866 0.03402 -0.0362 0.7007 0.0465
-5.000 -0.2799 0.03354 0.02872 -0.0354 0.6946 0.0477
-4.750 -0.2580 0.03214 0.02727 -0.0351 0.6870 0.0483
-4.500 -0.2356 0.03090 0.02592 -0.0347 0.6804 0.0491
-4.250 -0.2126 0.02950 0.02439 -0.0343 0.6740 0.0506
-4.000 -0.1845 0.02978 0.02412 -0.0328 0.6675 0.0552
-3.750 -0.1741 0.01916 0.01232 -0.0291 0.6638 0.0396
-3.500 -0.1473 0.01805 0.01107 -0.0288 0.6577 0.0391
-3.250 -0.1208 0.01663 0.00946 -0.0285 0.6514 0.0389
-3.000 -0.0936 0.01572 0.00836 -0.0282 0.6455 0.0389
-2.750 -0.0657 0.01505 0.00758 -0.0281 0.6390 0.0391
-2.500 -0.0382 0.01425 0.00665 -0.0279 0.6330 0.0396
-2.250 -0.0108 0.01342 0.00575 -0.0278 0.6273 0.0401
-2.000 0.0166 0.01282 0.00512 -0.0276 0.6211 0.0406
-1.750 0.0437 0.01240 0.00466 -0.0274 0.6152 0.0413
-1.500 0.0711 0.01206 0.00431 -0.0272 0.6091 0.0421
-1.250 0.0984 0.01176 0.00399 -0.0271 0.6026 0.0430
-1.000 0.1255 0.01153 0.00370 -0.0268 0.5964 0.0440
-0.750 0.1530 0.01128 0.00345 -0.0267 0.5894 0.0452
-0.500 0.1805 0.01113 0.00326 -0.0265 0.5829 0.0466
-0.250 0.2073 0.01084 0.00298 -0.0263 0.5764 0.0496
0.000 0.2349 0.01069 0.00283 -0.0262 0.5694 0.0528
0.250 0.2622 0.01055 0.00267 -0.0260 0.5629 0.0587
0.500 0.2893 0.01030 0.00256 -0.0258 0.5555 0.0885
0.750 0.3152 0.01005 0.00252 -0.0255 0.5488 0.1683
1.000 0.3400 0.00958 0.00251 -0.0252 0.5414 0.3136
1.250 0.3595 0.00792 0.00274 -0.0231 0.5350 0.9363
1.500 0.4044 0.00828 0.00304 -0.0262 0.5275 0.9655
1.750 0.4664 0.00869 0.00334 -0.0333 0.5192 0.9796
2.000 0.5370 0.00902 0.00358 -0.0425 0.5107 0.9915
2.250 0.5992 0.00913 0.00359 -0.0499 0.5030 0.9988
2.500 0.6321 0.00917 0.00359 -0.0512 0.4964 1.0000
2.750 0.6583 0.00921 0.00358 -0.0510 0.4894 1.0000
3.000 0.6844 0.00927 0.00358 -0.0508 0.4828 1.0000
3.250 0.7105 0.00931 0.00361 -0.0506 0.4763 1.0000
3.500 0.7366 0.00940 0.00364 -0.0504 0.4712 1.0000
3.750 0.7627 0.00947 0.00370 -0.0502 0.4667 1.0000
4.000 0.7888 0.00953 0.00377 -0.0500 0.4617 1.0000
4.250 0.8146 0.00963 0.00383 -0.0498 0.4570 1.0000
4.500 0.8405 0.00975 0.00392 -0.0496 0.4526 1.0000
4.750 0.8663 0.00981 0.00402 -0.0493 0.4480 1.0000
5.000 0.8919 0.00991 0.00410 -0.0491 0.4430 1.0000
5.250 0.9172 0.01008 0.00422 -0.0488 0.4382 1.0000
5.500 0.9426 0.01015 0.00435 -0.0484 0.4340 1.0000
5.750 0.9677 0.01024 0.00447 -0.0481 0.4292 1.0000
6.000 0.9924 0.01040 0.00461 -0.0476 0.4244 1.0000
6.250 1.0170 0.01053 0.00477 -0.0472 0.4195 1.0000
6.500 1.0417 0.01063 0.00492 -0.0467 0.4143 1.0000
6.750 1.0660 0.01079 0.00508 -0.0462 0.4096 1.0000
7.000 1.0901 0.01094 0.00526 -0.0457 0.4038 1.0000
7.250 1.1140 0.01104 0.00540 -0.0451 0.3961 1.0000
7.500 1.1374 0.01118 0.00556 -0.0445 0.3866 1.0000
7.750 1.1600 0.01136 0.00570 -0.0437 0.3748 1.0000
8.000 1.1833 0.01148 0.00587 -0.0430 0.3633 1.0000
8.250 1.2061 0.01165 0.00607 -0.0423 0.3516 1.0000
8.500 1.2282 0.01187 0.00629 -0.0415 0.3378 1.0000
8.750 1.2491 0.01216 0.00655 -0.0405 0.3193 1.0000
9.000 1.2682 0.01258 0.00689 -0.0393 0.2958 1.0000
9.250 1.2843 0.01319 0.00736 -0.0376 0.2662 1.0000
9.500 1.2978 0.01394 0.00796 -0.0355 0.2366 1.0000
9.750 1.3088 0.01479 0.00866 -0.0331 0.2064 1.0000
10.000 1.3132 0.01596 0.00958 -0.0298 0.1606 1.0000
10.250 1.3071 0.01755 0.01084 -0.0250 0.1148 1.0000
10.500 1.2995 0.01891 0.01203 -0.0198 0.0832 1.0000
10.750 1.2825 0.02063 0.01356 -0.0138 0.0546 1.0000
11.000 1.2761 0.02253 0.01539 -0.0106 0.0408 1.0000
11.250 1.2770 0.02431 0.01717 -0.0086 0.0347 1.0000
11.500 1.2817 0.02598 0.01890 -0.0073 0.0314 1.0000
11.750 1.2840 0.02799 0.02095 -0.0062 0.0291 1.0000
12.000 1.2864 0.03012 0.02316 -0.0053 0.0275 1.0000
12.250 1.2912 0.03210 0.02523 -0.0047 0.0263 1.0000
12.500 1.2940 0.03435 0.02755 -0.0041 0.0252 1.0000
12.750 1.2932 0.03700 0.03026 -0.0036 0.0242 1.0000
13.000 1.2858 0.04040 0.03374 -0.0032 0.0233 1.0000
13.250 1.2890 0.04273 0.03617 -0.0029 0.0227 1.0000
13.500 1.2896 0.04537 0.03889 -0.0027 0.0221 1.0000
13.750 1.2887 0.04819 0.04180 -0.0025 0.0215 1.0000
14.000 1.2870 0.05115 0.04484 -0.0024 0.0210 1.0000
14.250 1.2848 0.05428 0.04804 -0.0024 0.0205 1.0000
14.500 1.2815 0.05759 0.05142 -0.0026 0.0201 1.0000
14.750 1.2761 0.06120 0.05509 -0.0028 0.0197 1.0000
15.000 1.2684 0.06511 0.05906 -0.0030 0.0193 1.0000
15.250 1.2650 0.06853 0.06255 -0.0033 0.0190 1.0000
15.500 1.2660 0.07152 0.06564 -0.0036 0.0187 1.0000
15.750 1.2667 0.07455 0.06875 -0.0039 0.0184 1.0000
16.000 1.2674 0.07761 0.07190 -0.0043 0.0180 1.0000
16.250 1.2680 0.08070 0.07506 -0.0048 0.0176 1.0000
16.500 1.2687 0.08376 0.07817 -0.0052 0.0173 1.0000
16.750 1.2694 0.08688 0.08135 -0.0058 0.0169 1.0000
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