NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M15 AIRFOIL (m15-il) Reynolds number: 500,000 Max Cl/Cd: 98.69 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m15-il-500000-n5.txt Download as CSV file: xf-m15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M15 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4266 0.08724 0.08490 -0.0341 0.9481 0.0213
-9.250 -0.4981 0.06414 0.06156 -0.0517 0.8772 0.0225
-9.000 -0.5065 0.05753 0.05476 -0.0553 0.8573 0.0227
-8.750 -0.5083 0.05162 0.04863 -0.0573 0.8406 0.0229
-8.500 -0.5081 0.04533 0.04206 -0.0584 0.8259 0.0233
-8.250 -0.5088 0.03797 0.03430 -0.0586 0.8125 0.0239
-8.000 -0.5206 0.02792 0.02328 -0.0566 0.8001 0.0248
-7.750 -0.5059 0.02501 0.01990 -0.0554 0.7875 0.0252
-7.500 -0.4869 0.02302 0.01754 -0.0544 0.7756 0.0255
-7.250 -0.4656 0.02150 0.01569 -0.0537 0.7647 0.0258
-7.000 -0.4424 0.02033 0.01425 -0.0531 0.7543 0.0262
-6.750 -0.4179 0.01945 0.01313 -0.0526 0.7450 0.0266
-6.500 -0.3930 0.01868 0.01215 -0.0522 0.7352 0.0268
-6.250 -0.3675 0.01795 0.01122 -0.0518 0.7251 0.0270
-6.000 -0.3424 0.01707 0.01013 -0.0514 0.7151 0.0272
-5.750 -0.3171 0.01614 0.00905 -0.0511 0.7052 0.0276
-5.500 -0.2910 0.01550 0.00830 -0.0509 0.6964 0.0278
-5.250 -0.2646 0.01498 0.00768 -0.0507 0.6874 0.0281
-5.000 -0.2378 0.01453 0.00714 -0.0505 0.6793 0.0284
-4.750 -0.2109 0.01411 0.00665 -0.0503 0.6717 0.0288
-4.500 -0.1838 0.01373 0.00619 -0.0502 0.6658 0.0291
-4.250 -0.1566 0.01335 0.00576 -0.0501 0.6602 0.0295
-4.000 -0.1294 0.01302 0.00535 -0.0499 0.6549 0.0298
-3.750 -0.1020 0.01272 0.00500 -0.0498 0.6499 0.0304
-3.500 -0.0745 0.01243 0.00468 -0.0497 0.6446 0.0310
-3.250 -0.0471 0.01217 0.00437 -0.0496 0.6397 0.0315
-3.000 -0.0197 0.01192 0.00406 -0.0495 0.6353 0.0319
-2.750 0.0080 0.01168 0.00379 -0.0495 0.6305 0.0323
-2.500 0.0357 0.01148 0.00355 -0.0494 0.6253 0.0326
-2.250 0.0628 0.01120 0.00324 -0.0493 0.6206 0.0334
-2.000 0.0905 0.01099 0.00303 -0.0492 0.6163 0.0342
-1.750 0.1184 0.01082 0.00285 -0.0492 0.6114 0.0351
-1.500 0.1462 0.01069 0.00270 -0.0492 0.6063 0.0361
-1.250 0.1741 0.01058 0.00256 -0.0492 0.6014 0.0373
-1.000 0.2023 0.01046 0.00245 -0.0492 0.5961 0.0388
-0.750 0.2302 0.01035 0.00233 -0.0492 0.5909 0.0416
-0.500 0.2581 0.01026 0.00224 -0.0492 0.5857 0.0458
-0.250 0.2861 0.01013 0.00216 -0.0492 0.5795 0.0562
0.000 0.3136 0.00999 0.00212 -0.0492 0.5731 0.0838
0.250 0.3415 0.00989 0.00209 -0.0493 0.5672 0.1085
0.500 0.3693 0.00979 0.00206 -0.0493 0.5599 0.1376
0.750 0.3965 0.00963 0.00206 -0.0493 0.5525 0.1913
1.000 0.4220 0.00919 0.00206 -0.0491 0.5440 0.3438
1.250 0.4328 0.00759 0.00224 -0.0453 0.5371 0.9191
1.500 0.4675 0.00773 0.00235 -0.0464 0.5266 0.9544
1.750 0.5016 0.00787 0.00243 -0.0477 0.5152 0.9705
2.000 0.5450 0.00805 0.00254 -0.0510 0.5025 0.9800
2.250 0.5951 0.00825 0.00265 -0.0559 0.4889 0.9881
2.500 0.6463 0.00846 0.00276 -0.0611 0.4749 0.9953
2.750 0.6802 0.00858 0.00281 -0.0626 0.4636 0.9970
3.000 0.7111 0.00869 0.00287 -0.0634 0.4540 0.9982
3.250 0.7413 0.00883 0.00295 -0.0641 0.4449 0.9993
3.500 0.7699 0.00895 0.00304 -0.0644 0.4365 1.0000
3.750 0.7943 0.00909 0.00313 -0.0639 0.4281 1.0000
4.000 0.8185 0.00924 0.00323 -0.0633 0.4187 1.0000
4.250 0.8426 0.00938 0.00334 -0.0627 0.4104 1.0000
4.500 0.8664 0.00954 0.00347 -0.0620 0.4020 1.0000
4.750 0.8904 0.00967 0.00360 -0.0613 0.3949 1.0000
5.000 0.9144 0.00981 0.00373 -0.0607 0.3889 1.0000
5.500 0.9619 0.01010 0.00402 -0.0593 0.3784 1.0000
5.750 0.9854 0.01025 0.00418 -0.0586 0.3720 1.0000
6.000 1.0087 0.01043 0.00436 -0.0578 0.3662 1.0000
6.250 1.0324 0.01057 0.00453 -0.0571 0.3605 1.0000
6.500 1.0556 0.01075 0.00472 -0.0563 0.3545 1.0000
6.750 1.0787 0.01093 0.00492 -0.0556 0.3463 1.0000
7.000 1.1007 0.01118 0.00513 -0.0546 0.3322 1.0000
7.250 1.1223 0.01146 0.00537 -0.0536 0.3164 1.0000
7.500 1.1430 0.01179 0.00563 -0.0525 0.2970 1.0000
7.750 1.1616 0.01226 0.00597 -0.0511 0.2698 1.0000
8.000 1.1786 0.01285 0.00640 -0.0495 0.2389 1.0000
8.250 1.1938 0.01356 0.00693 -0.0476 0.2055 1.0000
8.500 1.2096 0.01424 0.00748 -0.0459 0.1794 1.0000
8.750 1.2255 0.01491 0.00804 -0.0442 0.1594 1.0000
9.000 1.2418 0.01553 0.00859 -0.0426 0.1413 1.0000
9.250 1.2554 0.01629 0.00923 -0.0406 0.1186 1.0000
9.500 1.2641 0.01729 0.01007 -0.0380 0.0879 1.0000
9.750 1.2686 0.01832 0.01096 -0.0346 0.0654 1.0000
10.000 1.2758 0.01924 0.01183 -0.0319 0.0532 1.0000
10.250 1.2855 0.02012 0.01271 -0.0297 0.0452 1.0000
10.500 1.2954 0.02108 0.01366 -0.0277 0.0389 1.0000
10.750 1.3051 0.02212 0.01472 -0.0260 0.0336 1.0000
11.000 1.3150 0.02322 0.01584 -0.0244 0.0292 1.0000
11.250 1.3251 0.02438 0.01703 -0.0231 0.0259 1.0000
11.500 1.3338 0.02571 0.01838 -0.0218 0.0232 1.0000
11.750 1.3437 0.02700 0.01973 -0.0208 0.0213 1.0000
12.000 1.3518 0.02850 0.02129 -0.0197 0.0197 1.0000
12.250 1.3594 0.03012 0.02296 -0.0188 0.0185 1.0000
12.500 1.3673 0.03175 0.02466 -0.0181 0.0175 1.0000
12.750 1.3738 0.03356 0.02654 -0.0174 0.0166 1.0000
13.000 1.3788 0.03557 0.02861 -0.0167 0.0158 1.0000
13.250 1.3815 0.03783 0.03094 -0.0161 0.0151 1.0000
13.500 1.3865 0.03993 0.03313 -0.0157 0.0146 1.0000
13.750 1.3901 0.04219 0.03548 -0.0153 0.0142 1.0000
14.000 1.3925 0.04460 0.03798 -0.0149 0.0137 1.0000
14.250 1.3938 0.04717 0.04064 -0.0146 0.0134 1.0000
14.500 1.3939 0.04994 0.04349 -0.0144 0.0130 1.0000
14.750 1.3929 0.05289 0.04653 -0.0144 0.0127 1.0000
15.000 1.3905 0.05611 0.04982 -0.0144 0.0124 1.0000
15.250 1.3862 0.05964 0.05345 -0.0146 0.0121 1.0000
15.500 1.3819 0.06327 0.05717 -0.0150 0.0118 1.0000
15.750 1.3802 0.06663 0.06064 -0.0154 0.0116 1.0000
16.000 1.3778 0.07016 0.06427 -0.0159 0.0114 1.0000
16.250 1.3749 0.07384 0.06805 -0.0166 0.0112 1.0000
16.500 1.3714 0.07763 0.07193 -0.0173 0.0109 1.0000
16.750 1.3674 0.08154 0.07594 -0.0181 0.0107 1.0000
17.000 1.3632 0.08554 0.08004 -0.0191 0.0105 1.0000
17.250 1.3587 0.08963 0.08422 -0.0201 0.0103 1.0000
17.500 1.3537 0.09380 0.08849 -0.0212 0.0101 1.0000
17.750 1.3482 0.09810 0.09287 -0.0224 0.0100 1.0000
18.000 1.3420 0.10254 0.09741 -0.0237 0.0098 1.0000
18.250 1.3356 0.10707 0.10202 -0.0251 0.0097 1.0000
18.500 1.3290 0.11167 0.10671 -0.0267 0.0096 1.0000
18.750 1.3219 0.11636 0.11148 -0.0283 0.0094 1.0000
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