NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M14 AIRFOIL (m14-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.67 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m14-il-1000000-n5.txt Download as CSV file: xf-m14-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M14 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 -0.4820 0.10426 0.10270 -0.0044 1.0000 0.0068
-9.500 -0.4879 0.09807 0.09653 -0.0073 1.0000 0.0075
-9.250 -0.4915 0.09276 0.09123 -0.0103 1.0000 0.0079
-9.000 -0.4862 0.08966 0.08814 -0.0122 1.0000 0.0081
-8.750 -0.4813 0.08652 0.08501 -0.0143 1.0000 0.0082
-8.500 -0.4759 0.08309 0.08160 -0.0174 0.9815 0.0084
-8.250 -0.4676 0.07910 0.07752 -0.0221 0.9254 0.0087
-8.000 -0.4617 0.07477 0.07304 -0.0262 0.8894 0.0091
-7.750 -0.4635 0.06340 0.06150 -0.0374 0.8632 0.0106
-7.500 -0.4465 0.06051 0.05848 -0.0400 0.8421 0.0109
-7.250 -0.4280 0.05787 0.05573 -0.0422 0.8229 0.0111
-6.750 -0.3999 0.03871 0.03592 -0.0534 0.7939 0.0144
-6.500 -0.3763 0.03745 0.03454 -0.0538 0.7792 0.0146
-6.250 -0.3524 0.03613 0.03310 -0.0543 0.7660 0.0149
-6.000 -0.3393 0.02343 0.01962 -0.0555 0.7574 0.0177
-5.750 -0.3071 0.02915 0.02564 -0.0555 0.7433 0.0165
-5.500 -0.2951 0.01703 0.01225 -0.0550 0.7359 0.0194
-5.250 -0.2686 0.01657 0.01168 -0.0550 0.7257 0.0197
-5.000 -0.2418 0.01612 0.01111 -0.0550 0.7155 0.0199
-4.750 -0.2150 0.01553 0.01039 -0.0550 0.7058 0.0202
-4.500 -0.1881 0.01491 0.00963 -0.0549 0.6968 0.0205
-4.250 -0.1609 0.01436 0.00894 -0.0549 0.6875 0.0209
-4.000 -0.1335 0.01392 0.00839 -0.0549 0.6786 0.0214
-3.750 -0.1062 0.01336 0.00769 -0.0549 0.6698 0.0219
-3.500 -0.0787 0.01278 0.00697 -0.0549 0.6607 0.0223
-3.250 -0.0511 0.01226 0.00633 -0.0549 0.6520 0.0227
-3.000 -0.0234 0.01179 0.00574 -0.0548 0.6426 0.0230
-2.750 0.0044 0.01135 0.00518 -0.0548 0.6335 0.0233
-2.500 0.0322 0.01095 0.00468 -0.0548 0.6237 0.0235
-2.250 0.0600 0.01057 0.00422 -0.0548 0.6135 0.0236
-2.000 0.0878 0.01023 0.00380 -0.0548 0.6041 0.0238
-1.750 0.1156 0.00992 0.00342 -0.0548 0.5950 0.0239
-1.500 0.1436 0.00969 0.00314 -0.0549 0.5861 0.0242
-1.250 0.1716 0.00948 0.00288 -0.0549 0.5779 0.0244
-1.000 0.1994 0.00923 0.00257 -0.0549 0.5694 0.0245
-0.750 0.2274 0.00901 0.00231 -0.0550 0.5616 0.0246
-0.500 0.2553 0.00884 0.00210 -0.0550 0.5534 0.0247
-0.250 0.2834 0.00870 0.00193 -0.0551 0.5460 0.0249
0.000 0.3115 0.00862 0.00180 -0.0551 0.5377 0.0251
0.250 0.3397 0.00853 0.00171 -0.0552 0.5304 0.0253
0.500 0.3676 0.00833 0.00144 -0.0553 0.5229 0.0266
0.750 0.3958 0.00823 0.00133 -0.0554 0.5155 0.0276
1.000 0.4239 0.00820 0.00128 -0.0554 0.5075 0.0284
1.250 0.4522 0.00817 0.00124 -0.0556 0.5006 0.0290
1.750 0.5087 0.00816 0.00121 -0.0558 0.4855 0.0301
2.000 0.5368 0.00818 0.00121 -0.0559 0.4775 0.0306
2.250 0.5650 0.00819 0.00122 -0.0560 0.4701 0.0317
2.500 0.5931 0.00823 0.00125 -0.0562 0.4626 0.0327
2.750 0.6213 0.00826 0.00128 -0.0563 0.4543 0.0336
3.250 0.6770 0.00814 0.00146 -0.0566 0.4375 0.1799
3.500 0.7091 0.00642 0.00167 -0.0581 0.4291 1.0000
3.750 0.7359 0.00655 0.00175 -0.0580 0.4173 1.0000
4.000 0.7627 0.00671 0.00185 -0.0578 0.4025 1.0000
4.250 0.7889 0.00696 0.00198 -0.0577 0.3761 1.0000
4.500 0.8147 0.00727 0.00214 -0.0575 0.3440 1.0000
4.750 0.8407 0.00757 0.00232 -0.0573 0.3161 1.0000
5.000 0.8665 0.00790 0.00253 -0.0571 0.2866 1.0000
5.250 0.8921 0.00826 0.00275 -0.0570 0.2562 1.0000
5.500 0.9143 0.00911 0.00321 -0.0564 0.1773 1.0000
5.750 0.9372 0.00986 0.00368 -0.0559 0.1215 1.0000
6.000 0.9585 0.01080 0.00427 -0.0553 0.0542 1.0000
6.250 0.9827 0.01131 0.00467 -0.0549 0.0315 1.0000
6.500 1.0072 0.01177 0.00505 -0.0545 0.0176 1.0000
6.750 1.0324 0.01209 0.00538 -0.0543 0.0147 1.0000
7.000 1.0573 0.01247 0.00576 -0.0539 0.0119 1.0000
7.250 1.0824 0.01279 0.00610 -0.0537 0.0109 1.0000
7.500 1.1072 0.01313 0.00647 -0.0534 0.0100 1.0000
7.750 1.1315 0.01352 0.00688 -0.0530 0.0091 1.0000
8.000 1.1550 0.01399 0.00739 -0.0525 0.0082 1.0000
8.250 1.1786 0.01444 0.00787 -0.0520 0.0077 1.0000
8.500 1.2023 0.01484 0.00830 -0.0516 0.0072 1.0000
8.750 1.2255 0.01527 0.00877 -0.0511 0.0067 1.0000
9.000 1.2481 0.01573 0.00927 -0.0506 0.0063 1.0000
9.250 1.2700 0.01626 0.00983 -0.0499 0.0059 1.0000
9.500 1.2899 0.01695 0.01058 -0.0490 0.0055 1.0000
9.750 1.3101 0.01758 0.01126 -0.0481 0.0053 1.0000
10.000 1.3302 0.01817 0.01191 -0.0472 0.0051 1.0000
10.250 1.3492 0.01882 0.01263 -0.0462 0.0049 1.0000
10.500 1.3673 0.01950 0.01338 -0.0450 0.0047 1.0000
10.750 1.3842 0.02023 0.01417 -0.0437 0.0045 1.0000
11.000 1.4001 0.02097 0.01498 -0.0423 0.0044 1.0000
11.250 1.4147 0.02170 0.01577 -0.0407 0.0042 1.0000
11.500 1.4257 0.02247 0.01660 -0.0386 0.0040 1.0000
11.750 1.4358 0.02336 0.01754 -0.0365 0.0039 1.0000
12.000 1.4435 0.02450 0.01875 -0.0344 0.0037 1.0000
12.250 1.4467 0.02610 0.02045 -0.0322 0.0036 1.0000
12.500 1.4522 0.02767 0.02213 -0.0307 0.0035 1.0000
12.750 1.4590 0.02923 0.02379 -0.0295 0.0035 1.0000
13.000 1.4652 0.03097 0.02563 -0.0285 0.0034 1.0000
13.250 1.4702 0.03291 0.02767 -0.0276 0.0034 1.0000
13.500 1.4743 0.03505 0.02991 -0.0270 0.0033 1.0000
13.750 1.4769 0.03740 0.03238 -0.0265 0.0032 1.0000
14.000 1.4789 0.03991 0.03499 -0.0261 0.0032 1.0000
14.250 1.4795 0.04264 0.03783 -0.0259 0.0031 1.0000
14.500 1.4790 0.04554 0.04085 -0.0258 0.0031 1.0000
14.750 1.4780 0.04858 0.04400 -0.0259 0.0030 1.0000
15.000 1.4750 0.05190 0.04743 -0.0260 0.0030 1.0000
15.250 1.4709 0.05543 0.05108 -0.0263 0.0029 1.0000
15.500 1.4664 0.05910 0.05488 -0.0268 0.0029 1.0000
15.750 1.4608 0.06302 0.05891 -0.0275 0.0029 1.0000
16.000 1.4549 0.06713 0.06313 -0.0283 0.0028 1.0000
16.250 1.4477 0.07155 0.06768 -0.0294 0.0028 1.0000
16.500 1.4400 0.07615 0.07239 -0.0307 0.0028 1.0000
16.750 1.4318 0.08094 0.07730 -0.0321 0.0027 1.0000
17.000 1.4219 0.08614 0.08261 -0.0338 0.0027 1.0000
17.250 1.4121 0.09142 0.08801 -0.0356 0.0027 1.0000
17.500 1.4010 0.09701 0.09372 -0.0376 0.0027 1.0000
17.750 1.3886 0.10297 0.09980 -0.0399 0.0027 1.0000
18.000 1.3767 0.10898 0.10594 -0.0424 0.0026 1.0000
18.250 1.3638 0.11524 0.11231 -0.0450 0.0026 1.0000
18.500 1.3493 0.12196 0.11916 -0.0480 0.0026 1.0000
18.750 1.3357 0.12871 0.12602 -0.0512 0.0026 1.0000
19.000 1.3207 0.13591 0.13335 -0.0547 0.0026 1.0000
19.250 1.3056 0.14326 0.14082 -0.0585 0.0026 1.0000
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