NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.88 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m24-il-1000000-n5.txt Download as CSV file: xf-m24-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3750 0.11171 0.10875 0.0098 0.5747 0.0119
-9.500 -0.3702 0.10827 0.10530 0.0081 0.5717 0.0122
-9.250 -0.3810 0.10082 0.09786 0.0042 0.5703 0.0133
-9.000 -0.3742 0.09817 0.09520 0.0027 0.5673 0.0135
-8.750 -0.3673 0.09554 0.09258 0.0011 0.5639 0.0135
-8.500 -0.3602 0.09296 0.08999 -0.0007 0.5602 0.0137
-8.250 -0.3548 0.09010 0.08712 -0.0030 0.5567 0.0138
-8.000 -0.3515 0.08705 0.08406 -0.0055 0.5537 0.0139
-7.750 -0.3476 0.08414 0.08114 -0.0072 0.5511 0.0141
-7.500 -0.3392 0.08082 0.07779 -0.0097 0.5481 0.0143
-7.250 -0.3296 0.07737 0.07431 -0.0121 0.5448 0.0146
-7.000 -0.3187 0.07376 0.07065 -0.0146 0.5415 0.0149
-6.750 -0.3145 0.06539 0.06215 -0.0196 0.5396 0.0163
-6.500 -0.2986 0.06262 0.05932 -0.0210 0.5365 0.0164
-6.250 -0.2807 0.06030 0.05696 -0.0220 0.5333 0.0165
-6.000 -0.2619 0.05797 0.05457 -0.0230 0.5298 0.0167
-5.750 -0.2426 0.05557 0.05209 -0.0239 0.5261 0.0168
-5.250 -0.2023 0.05033 0.04668 -0.0256 0.5194 0.0173
-5.000 -0.1813 0.04753 0.04378 -0.0262 0.5163 0.0176
-4.750 -0.1598 0.04461 0.04075 -0.0267 0.5129 0.0182
-4.500 -0.1388 0.04064 0.03660 -0.0268 0.5096 0.0187
-4.250 -0.1191 0.03549 0.03118 -0.0262 0.5066 0.0192
-4.000 -0.1023 0.02893 0.02425 -0.0246 0.5045 0.0199
-3.500 -0.0643 0.01865 0.01311 -0.0214 0.4989 0.0208
-3.250 -0.0397 0.01651 0.01062 -0.0207 0.4952 0.0211
-3.000 -0.0132 0.01527 0.00911 -0.0204 0.4913 0.0213
-2.750 0.0143 0.01435 0.00802 -0.0203 0.4879 0.0215
-2.500 0.0422 0.01362 0.00713 -0.0203 0.4844 0.0217
-2.250 0.0705 0.01304 0.00641 -0.0203 0.4806 0.0219
-2.000 0.0989 0.01262 0.00588 -0.0204 0.4765 0.0222
-1.750 0.1275 0.01223 0.00540 -0.0205 0.4729 0.0225
-1.500 0.1561 0.01183 0.00493 -0.0206 0.4693 0.0227
-1.250 0.1847 0.01150 0.00454 -0.0208 0.4657 0.0229
-1.000 0.2133 0.01125 0.00422 -0.0209 0.4618 0.0231
-0.750 0.2418 0.01104 0.00396 -0.0211 0.4580 0.0233
-0.500 0.2704 0.01086 0.00375 -0.0212 0.4544 0.0235
-0.250 0.2985 0.01055 0.00340 -0.0213 0.4505 0.0238
0.000 0.3264 0.01029 0.00312 -0.0213 0.4468 0.0242
0.250 0.3544 0.01014 0.00295 -0.0214 0.4431 0.0245
0.500 0.3826 0.01000 0.00281 -0.0215 0.4400 0.0248
0.750 0.4108 0.00989 0.00270 -0.0216 0.4361 0.0251
1.000 0.4389 0.00981 0.00260 -0.0217 0.4318 0.0255
1.250 0.4670 0.00975 0.00252 -0.0219 0.4278 0.0259
1.500 0.4951 0.00967 0.00245 -0.0220 0.4249 0.0263
1.750 0.5234 0.00962 0.00239 -0.0221 0.4215 0.0269
2.000 0.5516 0.00959 0.00236 -0.0223 0.4177 0.0276
2.250 0.5797 0.00958 0.00234 -0.0225 0.4136 0.0281
2.500 0.6079 0.00956 0.00232 -0.0227 0.4100 0.0285
2.750 0.6359 0.00952 0.00228 -0.0229 0.4063 0.0296
3.000 0.6641 0.00953 0.00228 -0.0231 0.4025 0.0307
3.250 0.6923 0.00956 0.00231 -0.0233 0.3988 0.0320
3.500 0.7205 0.00959 0.00234 -0.0236 0.3955 0.0335
3.750 0.7488 0.00960 0.00238 -0.0238 0.3925 0.0382
4.000 0.7762 0.00955 0.00247 -0.0240 0.3888 0.0932
4.250 0.8040 0.00958 0.00256 -0.0242 0.3847 0.1250
4.500 0.8316 0.00961 0.00268 -0.0244 0.3807 0.1769
4.750 0.8526 0.00895 0.00281 -0.0235 0.3779 0.5932
5.000 0.8651 0.00806 0.00295 -0.0202 0.3751 0.9409
5.250 0.8935 0.00821 0.00312 -0.0204 0.3716 0.9591
5.500 0.9252 0.00845 0.00335 -0.0214 0.3680 0.9733
5.750 0.9610 0.00865 0.00355 -0.0234 0.3647 0.9771
6.000 0.9968 0.00888 0.00379 -0.0254 0.3617 0.9837
6.250 1.0389 0.00908 0.00398 -0.0289 0.3578 0.9847
6.500 1.0692 0.00926 0.00413 -0.0299 0.3522 0.9851
6.750 1.0989 0.00942 0.00428 -0.0307 0.3447 0.9855
7.000 1.1280 0.00964 0.00445 -0.0315 0.3368 0.9860
7.250 1.1574 0.00980 0.00462 -0.0323 0.3321 0.9864
7.500 1.1864 0.00998 0.00480 -0.0331 0.3256 0.9869
7.750 1.2147 0.01024 0.00502 -0.0338 0.3170 0.9875
8.000 1.2425 0.01054 0.00528 -0.0344 0.3060 0.9882
8.250 1.2698 0.01086 0.00555 -0.0350 0.2933 0.9889
8.500 1.2963 0.01122 0.00587 -0.0355 0.2801 0.9898
8.750 1.3214 0.01171 0.00627 -0.0359 0.2629 0.9908
9.000 1.3425 0.01258 0.00696 -0.0359 0.2306 0.9922
9.250 1.3491 0.01496 0.00883 -0.0349 0.1512 0.9944
9.500 1.3497 0.01813 0.01158 -0.0347 0.0751 0.9971
9.750 1.3471 0.02064 0.01399 -0.0339 0.0452 1.0000
10.000 1.3232 0.02289 0.01619 -0.0283 0.0273 1.0000
10.250 1.3157 0.02475 0.01806 -0.0251 0.0201 1.0000
10.500 1.3161 0.02634 0.01969 -0.0230 0.0179 1.0000
10.750 1.3179 0.02802 0.02141 -0.0214 0.0162 1.0000
11.000 1.3217 0.02967 0.02310 -0.0200 0.0153 1.0000
11.250 1.3254 0.03147 0.02494 -0.0190 0.0145 1.0000
11.500 1.3282 0.03344 0.02696 -0.0180 0.0137 1.0000
11.750 1.3304 0.03555 0.02912 -0.0172 0.0129 1.0000
12.000 1.3338 0.03762 0.03123 -0.0166 0.0124 1.0000
12.250 1.3371 0.03972 0.03339 -0.0160 0.0121 1.0000
12.500 1.3400 0.04191 0.03564 -0.0155 0.0117 1.0000
12.750 1.3423 0.04421 0.03800 -0.0151 0.0113 1.0000
13.000 1.3439 0.04668 0.04053 -0.0148 0.0110 1.0000
13.250 1.3450 0.04928 0.04317 -0.0146 0.0106 1.0000
13.500 1.3456 0.05196 0.04591 -0.0144 0.0103 1.0000
13.750 1.3450 0.05481 0.04882 -0.0142 0.0099 1.0000
14.000 1.3445 0.05774 0.05181 -0.0142 0.0096 1.0000
14.250 1.3460 0.06045 0.05458 -0.0142 0.0094 1.0000
14.500 1.3475 0.06315 0.05735 -0.0142 0.0092 1.0000
14.750 1.3478 0.06608 0.06033 -0.0143 0.0090 1.0000
15.000 1.3486 0.06894 0.06326 -0.0144 0.0087 1.0000
15.250 1.3484 0.07199 0.06636 -0.0146 0.0085 1.0000
15.500 1.3477 0.07508 0.06951 -0.0148 0.0083 1.0000
15.750 1.3471 0.07820 0.07270 -0.0151 0.0081 1.0000
16.000 1.3455 0.08151 0.07606 -0.0155 0.0079 1.0000
16.250 1.3445 0.08475 0.07935 -0.0158 0.0077 1.0000
16.500 1.3411 0.08831 0.08298 -0.0163 0.0075 1.0000
16.750 1.3382 0.09184 0.08657 -0.0168 0.0073 1.0000
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