NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M15 AIRFOIL (m15-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.51 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m15-il-1000000-n5.txt Download as CSV file: xf-m15-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8975 0.03707 0.03469 -0.0618 0.9978 0.0191
-12.000 -0.8808 0.03479 0.03225 -0.0626 0.9751 0.0192
-11.750 -0.8635 0.03327 0.03059 -0.0625 0.9538 0.0194
-11.500 -0.8497 0.03188 0.02904 -0.0613 0.9314 0.0195
-11.250 -0.8358 0.03052 0.02749 -0.0600 0.9112 0.0197
-11.000 -0.8224 0.02885 0.02559 -0.0587 0.8921 0.0198
-10.750 -0.8075 0.02725 0.02376 -0.0576 0.8746 0.0200
-10.500 -0.7908 0.02578 0.02205 -0.0566 0.8586 0.0202
-10.250 -0.7730 0.02438 0.02042 -0.0556 0.8437 0.0204
-10.000 -0.7533 0.02320 0.01902 -0.0548 0.8293 0.0206
-9.500 -0.7106 0.02120 0.01663 -0.0534 0.8015 0.0212
-9.250 -0.6886 0.02019 0.01541 -0.0527 0.7885 0.0214
-9.000 -0.6658 0.01928 0.01431 -0.0521 0.7759 0.0215
-8.750 -0.6422 0.01849 0.01334 -0.0516 0.7632 0.0217
-8.500 -0.6180 0.01779 0.01247 -0.0512 0.7505 0.0219
-8.250 -0.5931 0.01716 0.01170 -0.0508 0.7387 0.0220
-8.000 -0.5678 0.01659 0.01099 -0.0505 0.7285 0.0222
-7.750 -0.5420 0.01609 0.01035 -0.0502 0.7187 0.0223
-7.500 -0.5158 0.01566 0.00982 -0.0500 0.7098 0.0224
-7.250 -0.4914 0.01477 0.00876 -0.0495 0.7002 0.0228
-7.000 -0.4656 0.01419 0.00809 -0.0493 0.6899 0.0230
-6.750 -0.4392 0.01376 0.00756 -0.0491 0.6803 0.0232
-6.500 -0.4124 0.01338 0.00711 -0.0489 0.6713 0.0234
-6.250 -0.3855 0.01303 0.00669 -0.0488 0.6642 0.0236
-6.000 -0.3583 0.01271 0.00629 -0.0486 0.6568 0.0238
-5.750 -0.3311 0.01240 0.00593 -0.0485 0.6498 0.0240
-5.500 -0.3038 0.01210 0.00556 -0.0484 0.6428 0.0242
-5.250 -0.2764 0.01182 0.00522 -0.0483 0.6371 0.0245
-5.000 -0.2488 0.01153 0.00489 -0.0483 0.6327 0.0247
-4.750 -0.2212 0.01126 0.00458 -0.0482 0.6281 0.0249
-4.500 -0.1935 0.01101 0.00429 -0.0482 0.6233 0.0252
-4.250 -0.1658 0.01078 0.00401 -0.0481 0.6193 0.0255
-4.000 -0.1379 0.01055 0.00375 -0.0481 0.6157 0.0257
-3.750 -0.1100 0.01034 0.00351 -0.0481 0.6114 0.0260
-3.500 -0.0820 0.01016 0.00328 -0.0481 0.6068 0.0263
-3.250 -0.0540 0.01001 0.00310 -0.0481 0.6028 0.0266
-3.000 -0.0256 0.00986 0.00294 -0.0482 0.5994 0.0269
-2.750 0.0025 0.00970 0.00276 -0.0482 0.5951 0.0272
-2.500 0.0303 0.00948 0.00251 -0.0482 0.5905 0.0278
-2.250 0.0584 0.00933 0.00233 -0.0482 0.5861 0.0283
-2.000 0.0867 0.00919 0.00219 -0.0483 0.5818 0.0289
-1.750 0.1150 0.00907 0.00207 -0.0483 0.5770 0.0295
-1.500 0.1433 0.00899 0.00196 -0.0484 0.5719 0.0301
-1.250 0.1718 0.00890 0.00187 -0.0485 0.5668 0.0307
-1.000 0.2002 0.00882 0.00178 -0.0486 0.5605 0.0315
-0.750 0.2286 0.00877 0.00170 -0.0487 0.5547 0.0322
-0.500 0.2571 0.00869 0.00163 -0.0488 0.5481 0.0334
-0.250 0.2854 0.00864 0.00157 -0.0489 0.5400 0.0360
0.250 0.3418 0.00853 0.00148 -0.0491 0.5221 0.0538
0.500 0.3697 0.00845 0.00147 -0.0492 0.5106 0.0815
0.750 0.3976 0.00842 0.00147 -0.0492 0.4974 0.1029
1.000 0.4255 0.00841 0.00148 -0.0493 0.4837 0.1263
1.250 0.4529 0.00835 0.00150 -0.0493 0.4715 0.1745
1.500 0.4799 0.00824 0.00155 -0.0493 0.4598 0.2543
1.750 0.4987 0.00704 0.00157 -0.0482 0.4495 0.7029
2.000 0.5154 0.00653 0.00175 -0.0453 0.4414 0.9268
2.250 0.5428 0.00664 0.00185 -0.0451 0.4332 0.9499
2.500 0.5718 0.00675 0.00194 -0.0453 0.4261 0.9623
2.750 0.6036 0.00690 0.00205 -0.0461 0.4185 0.9756
3.000 0.6423 0.00708 0.00219 -0.0485 0.4116 0.9851
3.250 0.6843 0.00726 0.00232 -0.0517 0.4024 0.9881
3.500 0.7159 0.00738 0.00240 -0.0526 0.3949 0.9895
3.750 0.7460 0.00750 0.00248 -0.0533 0.3871 0.9907
4.000 0.7757 0.00762 0.00257 -0.0538 0.3795 0.9919
4.250 0.8050 0.00774 0.00266 -0.0543 0.3725 0.9932
4.500 0.8350 0.00787 0.00277 -0.0550 0.3674 0.9941
4.750 0.8662 0.00796 0.00285 -0.0558 0.3625 0.9947
5.000 0.8971 0.00808 0.00296 -0.0567 0.3560 0.9955
5.250 0.9278 0.00821 0.00308 -0.0575 0.3502 0.9963
5.500 0.9584 0.00832 0.00320 -0.0583 0.3448 0.9972
5.750 0.9885 0.00847 0.00333 -0.0590 0.3388 0.9981
6.000 1.0184 0.00861 0.00347 -0.0597 0.3327 0.9989
6.250 1.0476 0.00884 0.00364 -0.0603 0.3172 0.9998
6.500 1.0713 0.00913 0.00384 -0.0598 0.2957 1.0000
6.750 1.0926 0.00943 0.00405 -0.0587 0.2776 1.0000
7.000 1.1122 0.00984 0.00433 -0.0574 0.2504 1.0000
7.250 1.1295 0.01042 0.00472 -0.0557 0.2165 1.0000
7.500 1.1464 0.01100 0.00513 -0.0540 0.1850 1.0000
7.750 1.1635 0.01156 0.00554 -0.0523 0.1604 1.0000
8.000 1.1825 0.01199 0.00590 -0.0509 0.1445 1.0000
8.250 1.2008 0.01246 0.00628 -0.0494 0.1266 1.0000
8.500 1.2162 0.01313 0.00680 -0.0475 0.0999 1.0000
8.750 1.2290 0.01398 0.00746 -0.0453 0.0701 1.0000
9.000 1.2451 0.01461 0.00801 -0.0436 0.0547 1.0000
9.250 1.2622 0.01517 0.00853 -0.0421 0.0450 1.0000
9.500 1.2791 0.01572 0.00906 -0.0405 0.0375 1.0000
9.750 1.2953 0.01627 0.00958 -0.0389 0.0315 1.0000
10.000 1.3094 0.01683 0.01012 -0.0370 0.0271 1.0000
10.250 1.3216 0.01743 0.01072 -0.0347 0.0233 1.0000
10.500 1.3352 0.01803 0.01134 -0.0329 0.0205 1.0000
10.750 1.3482 0.01872 0.01205 -0.0311 0.0183 1.0000
11.000 1.3615 0.01946 0.01281 -0.0295 0.0166 1.0000
11.250 1.3739 0.02031 0.01367 -0.0280 0.0151 1.0000
11.500 1.3874 0.02113 0.01453 -0.0267 0.0143 1.0000
11.750 1.4000 0.02206 0.01551 -0.0255 0.0136 1.0000
12.000 1.4116 0.02310 0.01659 -0.0243 0.0129 1.0000
12.250 1.4222 0.02429 0.01782 -0.0232 0.0122 1.0000
12.500 1.4328 0.02552 0.01910 -0.0222 0.0117 1.0000
12.750 1.4438 0.02677 0.02041 -0.0214 0.0114 1.0000
13.000 1.4539 0.02815 0.02185 -0.0206 0.0110 1.0000
13.250 1.4629 0.02964 0.02340 -0.0198 0.0106 1.0000
13.500 1.4708 0.03129 0.02510 -0.0192 0.0102 1.0000
13.750 1.4773 0.03311 0.02697 -0.0185 0.0098 1.0000
14.000 1.4822 0.03513 0.02904 -0.0179 0.0094 1.0000
14.250 1.4867 0.03721 0.03119 -0.0174 0.0091 1.0000
14.500 1.4920 0.03925 0.03331 -0.0170 0.0090 1.0000
14.750 1.4963 0.04142 0.03555 -0.0166 0.0088 1.0000
15.000 1.4993 0.04373 0.03793 -0.0162 0.0086 1.0000
15.250 1.5016 0.04618 0.04045 -0.0160 0.0084 1.0000
15.500 1.5031 0.04879 0.04314 -0.0158 0.0082 1.0000
15.750 1.5037 0.05153 0.04596 -0.0158 0.0081 1.0000
16.000 1.5033 0.05444 0.04894 -0.0158 0.0079 1.0000
16.250 1.5023 0.05750 0.05208 -0.0159 0.0078 1.0000
16.500 1.5004 0.06075 0.05541 -0.0161 0.0076 1.0000
16.750 1.4974 0.06417 0.05891 -0.0165 0.0075 1.0000
17.000 1.4933 0.06781 0.06263 -0.0170 0.0073 1.0000
17.250 1.4880 0.07169 0.06660 -0.0176 0.0072 1.0000
17.500 1.4813 0.07585 0.07084 -0.0183 0.0071 1.0000
17.750 1.4752 0.07995 0.07504 -0.0192 0.0070 1.0000
18.000 1.4704 0.08393 0.07910 -0.0200 0.0069 1.0000
18.250 1.4652 0.08802 0.08328 -0.0210 0.0068 1.0000
18.500 1.4595 0.09224 0.08759 -0.0221 0.0067 1.0000
18.750 1.4529 0.09657 0.09202 -0.0233 0.0067 1.0000
19.000 1.4464 0.10093 0.09646 -0.0245 0.0066 1.0000
19.250 1.4398 0.10535 0.10097 -0.0259 0.0065 1.0000
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