NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 500,000 Max Cl/Cd: 100.64 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m24-il-500000-n5.txt Download as CSV file: xf-m24-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3371 0.10618 0.10269 0.0046 0.5981 0.0183
-8.750 -0.3326 0.10270 0.09920 0.0028 0.5945 0.0184
-8.500 -0.3377 0.09714 0.09365 -0.0024 0.5921 0.0197
-8.250 -0.3280 0.09489 0.09138 -0.0027 0.5883 0.0200
-8.000 -0.3211 0.09221 0.08869 -0.0042 0.5850 0.0202
-7.750 -0.3162 0.08923 0.08571 -0.0065 0.5816 0.0206
-7.500 -0.3132 0.08638 0.08285 -0.0081 0.5780 0.0209
-7.250 -0.3052 0.08327 0.07970 -0.0104 0.5745 0.0214
-7.000 -0.2956 0.07891 0.07526 -0.0155 0.5716 0.0233
-6.500 -0.2706 0.07061 0.06681 -0.0217 0.5657 0.0235
-6.250 -0.2557 0.06683 0.06294 -0.0235 0.5624 0.0235
-6.000 -0.2398 0.06321 0.05923 -0.0249 0.5590 0.0235
-5.750 -0.2230 0.05975 0.05566 -0.0260 0.5556 0.0235
-5.500 -0.2063 0.05681 0.05264 -0.0265 0.5523 0.0234
-5.250 -0.1893 0.05324 0.04898 -0.0273 0.5489 0.0239
-5.000 -0.1703 0.05218 0.04789 -0.0273 0.5449 0.0243
-4.750 -0.1496 0.05052 0.04617 -0.0277 0.5411 0.0250
-4.500 -0.1274 0.04842 0.04396 -0.0283 0.5377 0.0265
-4.000 -0.0834 0.04244 0.03770 -0.0289 0.5308 0.0260
-3.750 -0.0608 0.03907 0.03414 -0.0288 0.5275 0.0252
-3.500 -0.0379 0.03541 0.03023 -0.0283 0.5243 0.0247
-3.250 -0.0139 0.03336 0.02803 -0.0281 0.5209 0.0251
-3.000 0.0105 0.03117 0.02568 -0.0277 0.5173 0.0255
-2.750 0.0342 0.02760 0.02181 -0.0266 0.5140 0.0252
-2.500 0.0580 0.02395 0.01781 -0.0254 0.5107 0.0252
-2.250 0.0813 0.01933 0.01258 -0.0238 0.5078 0.0254
-2.000 0.1079 0.01747 0.01037 -0.0233 0.5043 0.0257
-1.750 0.1357 0.01650 0.00919 -0.0232 0.5005 0.0262
-1.500 0.1639 0.01561 0.00809 -0.0232 0.4967 0.0265
-1.250 0.1924 0.01486 0.00715 -0.0232 0.4929 0.0267
-1.000 0.2210 0.01428 0.00642 -0.0233 0.4893 0.0270
-0.750 0.2497 0.01380 0.00583 -0.0234 0.4854 0.0273
-0.500 0.2784 0.01340 0.00536 -0.0236 0.4814 0.0276
-0.250 0.3069 0.01310 0.00497 -0.0237 0.4777 0.0279
0.000 0.3352 0.01286 0.00465 -0.0238 0.4742 0.0282
0.250 0.3636 0.01262 0.00440 -0.0239 0.4705 0.0284
0.500 0.3911 0.01223 0.00399 -0.0239 0.4664 0.0289
0.750 0.4186 0.01199 0.00374 -0.0239 0.4624 0.0294
1.000 0.4461 0.01185 0.00358 -0.0239 0.4589 0.0301
1.250 0.4738 0.01172 0.00347 -0.0240 0.4556 0.0310
1.500 0.5014 0.01160 0.00337 -0.0240 0.4518 0.0318
1.750 0.5289 0.01152 0.00326 -0.0240 0.4477 0.0324
2.000 0.5564 0.01147 0.00319 -0.0240 0.4438 0.0331
2.250 0.5841 0.01142 0.00314 -0.0241 0.4402 0.0339
2.500 0.6117 0.01137 0.00310 -0.0242 0.4365 0.0349
2.750 0.6393 0.01135 0.00308 -0.0242 0.4328 0.0367
3.000 0.6668 0.01136 0.00308 -0.0244 0.4292 0.0390
3.250 0.6943 0.01136 0.00311 -0.0244 0.4257 0.0467
3.500 0.7214 0.01129 0.00320 -0.0245 0.4218 0.0980
3.750 0.7487 0.01129 0.00330 -0.0246 0.4177 0.1360
4.000 0.7756 0.01130 0.00340 -0.0247 0.4140 0.1899
4.250 0.7873 0.01012 0.00340 -0.0219 0.4112 0.7463
4.750 0.8808 0.01041 0.00430 -0.0298 0.4031 0.9754
5.000 0.9216 0.01065 0.00450 -0.0329 0.3989 0.9799
5.250 0.9754 0.01095 0.00478 -0.0388 0.3946 0.9865
5.500 1.0214 0.01113 0.00497 -0.0431 0.3903 0.9905
5.750 1.0501 0.01127 0.00510 -0.0436 0.3866 0.9915
6.000 1.0779 0.01143 0.00525 -0.0440 0.3832 0.9923
6.250 1.1052 0.01159 0.00541 -0.0444 0.3801 0.9930
6.500 1.1325 0.01173 0.00558 -0.0446 0.3770 0.9938
6.750 1.1618 0.01187 0.00575 -0.0454 0.3732 0.9942
7.000 1.1905 0.01207 0.00594 -0.0461 0.3677 0.9947
7.250 1.2193 0.01225 0.00613 -0.0469 0.3609 0.9952
7.500 1.2476 0.01247 0.00634 -0.0476 0.3535 0.9958
7.750 1.2757 0.01270 0.00658 -0.0482 0.3466 0.9965
8.000 1.3035 0.01296 0.00685 -0.0489 0.3381 0.9972
8.250 1.3315 0.01323 0.00712 -0.0496 0.3316 0.9980
8.500 1.3593 0.01353 0.00744 -0.0503 0.3230 0.9988
8.750 1.3862 0.01390 0.00780 -0.0510 0.3111 0.9995
9.000 1.4094 0.01444 0.00828 -0.0511 0.2936 1.0000
9.250 1.4260 0.01506 0.00882 -0.0499 0.2760 1.0000
9.500 1.4388 0.01586 0.00953 -0.0482 0.2519 1.0000
9.750 1.4402 0.01722 0.01068 -0.0451 0.2156 1.0000
10.000 1.4213 0.01925 0.01248 -0.0392 0.1754 1.0000
10.250 1.3958 0.02080 0.01402 -0.0321 0.1639 1.0000
10.500 1.3720 0.02326 0.01640 -0.0268 0.1424 1.0000
10.750 1.3452 0.02672 0.01972 -0.0228 0.1101 1.0000
11.000 1.3217 0.03054 0.02342 -0.0200 0.0840 1.0000
11.250 1.3086 0.03384 0.02669 -0.0183 0.0666 1.0000
11.500 1.2883 0.03801 0.03077 -0.0168 0.0411 1.0000
11.750 1.2725 0.04194 0.03467 -0.0156 0.0254 1.0000
12.000 1.2681 0.04485 0.03761 -0.0149 0.0215 1.0000
12.250 1.2672 0.04754 0.04036 -0.0144 0.0195 1.0000
12.500 1.2673 0.05022 0.04310 -0.0141 0.0183 1.0000
12.750 1.2667 0.05302 0.04597 -0.0139 0.0173 1.0000
13.000 1.2654 0.05597 0.04899 -0.0137 0.0163 1.0000
13.250 1.2664 0.05871 0.05180 -0.0136 0.0158 1.0000
13.500 1.2669 0.06155 0.05472 -0.0135 0.0152 1.0000
13.750 1.2670 0.06445 0.05770 -0.0135 0.0146 1.0000
14.000 1.2662 0.06754 0.06085 -0.0136 0.0141 1.0000
14.250 1.2646 0.07077 0.06415 -0.0138 0.0136 1.0000
14.500 1.2621 0.07411 0.06756 -0.0139 0.0132 1.0000
14.750 1.2578 0.07775 0.07128 -0.0142 0.0128 1.0000
15.000 1.2559 0.08113 0.07474 -0.0145 0.0125 1.0000
15.250 1.2556 0.08433 0.07802 -0.0149 0.0123 1.0000
15.500 1.2541 0.08771 0.08147 -0.0153 0.0120 1.0000
15.750 1.2530 0.09104 0.08488 -0.0157 0.0117 1.0000
16.000 1.2509 0.09458 0.08850 -0.0163 0.0115 1.0000
16.250 1.2499 0.09798 0.09196 -0.0168 0.0112 1.0000
16.500 1.2478 0.10156 0.09561 -0.0174 0.0109 1.0000
16.750 1.2467 0.10498 0.09911 -0.0181 0.0107 1.0000
17.000 1.2446 0.10860 0.10279 -0.0188 0.0104 1.0000
17.250 1.2430 0.11216 0.10641 -0.0196 0.0102 1.0000
17.500 1.2395 0.11606 0.11037 -0.0206 0.0099 1.0000
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