NACA M12 (nacam12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 500,000 Max Cl/Cd: 71.5 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam12-il-500000.txt Download as CSV file: xf-nacam12-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4673 0.08013 0.07787 -0.0355 1.0000 0.0420
-10.250 -0.4651 0.07706 0.07482 -0.0358 1.0000 0.0424
-9.750 -0.7399 0.04812 0.04497 -0.0433 1.0000 0.0355
-9.500 -0.7220 0.04752 0.04441 -0.0422 1.0000 0.0336
-9.250 -0.7587 0.03809 0.03440 -0.0370 1.0000 0.0323
-9.000 -0.7708 0.03316 0.02899 -0.0322 1.0000 0.0324
-8.750 -0.7722 0.03027 0.02574 -0.0281 1.0000 0.0327
-8.500 -0.7701 0.02810 0.02329 -0.0242 1.0000 0.0329
-8.250 -0.7526 0.02599 0.02088 -0.0231 0.9986 0.0333
-8.000 -0.7217 0.02419 0.01877 -0.0245 0.9958 0.0339
-7.750 -0.6873 0.02326 0.01760 -0.0263 0.9936 0.0345
-7.500 -0.6577 0.02120 0.01526 -0.0274 0.9899 0.0349
-7.250 -0.6259 0.01919 0.01311 -0.0289 0.9867 0.0355
-7.000 -0.5910 0.01799 0.01185 -0.0307 0.9842 0.0362
-6.750 -0.5547 0.01712 0.01093 -0.0329 0.9822 0.0370
-6.500 -0.5227 0.01642 0.01018 -0.0339 0.9766 0.0379
-6.250 -0.4889 0.01565 0.00936 -0.0353 0.9720 0.0386
-6.000 -0.4566 0.01493 0.00858 -0.0363 0.9665 0.0393
-5.750 -0.4272 0.01430 0.00791 -0.0366 0.9581 0.0399
-5.500 -0.3985 0.01375 0.00730 -0.0368 0.9496 0.0405
-5.250 -0.3715 0.01329 0.00678 -0.0365 0.9398 0.0411
-5.000 -0.3476 0.01264 0.00608 -0.0356 0.9283 0.0421
-4.750 -0.3235 0.01212 0.00553 -0.0348 0.9173 0.0435
-4.500 -0.2987 0.01177 0.00514 -0.0340 0.9063 0.0447
-4.250 -0.2736 0.01146 0.00480 -0.0333 0.8943 0.0460
-4.000 -0.2480 0.01119 0.00447 -0.0327 0.8833 0.0475
-3.750 -0.2222 0.01097 0.00418 -0.0321 0.8723 0.0489
-3.500 -0.1965 0.01065 0.00386 -0.0316 0.8606 0.0523
-3.250 -0.1700 0.01046 0.00364 -0.0311 0.8497 0.0568
-3.000 -0.1441 0.01019 0.00338 -0.0306 0.8387 0.0691
-2.750 -0.1117 0.01090 0.00425 -0.0311 0.8271 0.1196
-2.500 -0.0824 0.01129 0.00450 -0.0311 0.8160 0.1273
-2.250 -0.0542 0.01156 0.00463 -0.0310 0.8049 0.1334
-2.000 -0.0270 0.01141 0.00444 -0.0308 0.7931 0.1376
-1.750 0.0004 0.01135 0.00433 -0.0307 0.7821 0.1423
-1.500 0.0276 0.01128 0.00418 -0.0305 0.7708 0.1469
-1.250 0.0544 0.01096 0.00389 -0.0303 0.7591 0.1519
-1.000 0.0820 0.01093 0.00380 -0.0302 0.7478 0.1548
-0.500 0.1349 0.01032 0.00322 -0.0297 0.7247 0.1627
-0.250 0.1623 0.01025 0.00312 -0.0296 0.7131 0.1661
0.000 0.1898 0.01023 0.00304 -0.0294 0.7015 0.1669
0.250 0.2170 0.01014 0.00293 -0.0293 0.6892 0.1672
0.500 0.2439 0.00999 0.00278 -0.0291 0.6770 0.1682
0.750 0.2710 0.00989 0.00267 -0.0289 0.6647 0.1690
1.000 0.2983 0.00989 0.00263 -0.0288 0.6523 0.1690
1.250 0.3259 0.00988 0.00260 -0.0287 0.6390 0.1688
1.500 0.3534 0.00988 0.00259 -0.0286 0.6259 0.1686
1.750 0.3809 0.00989 0.00258 -0.0285 0.6127 0.1684
2.000 0.4082 0.00992 0.00259 -0.0284 0.5992 0.1682
2.250 0.4354 0.00996 0.00259 -0.0283 0.5843 0.1681
2.500 0.4624 0.01001 0.00261 -0.0281 0.5690 0.1679
2.750 0.4896 0.01005 0.00264 -0.0280 0.5548 0.1679
3.000 0.5170 0.01009 0.00268 -0.0279 0.5416 0.1680
3.250 0.5442 0.01014 0.00273 -0.0279 0.5287 0.1684
3.500 0.5713 0.01021 0.00279 -0.0277 0.5161 0.1689
3.750 0.5982 0.01031 0.00286 -0.0276 0.5036 0.1690
4.000 0.6254 0.01039 0.00295 -0.0275 0.4904 0.1692
4.250 0.6525 0.01048 0.00304 -0.0274 0.4769 0.1696
4.500 0.6788 0.01061 0.00312 -0.0272 0.4577 0.1700
4.750 0.7049 0.01076 0.00322 -0.0269 0.4358 0.1706
5.000 0.7311 0.01091 0.00334 -0.0267 0.4146 0.1714
5.250 0.7573 0.01107 0.00347 -0.0265 0.3964 0.1723
5.500 0.7833 0.01125 0.00362 -0.0262 0.3775 0.1734
5.750 0.8087 0.01148 0.00380 -0.0259 0.3560 0.1747
6.000 0.8340 0.01171 0.00399 -0.0256 0.3317 0.1763
6.250 0.8587 0.01201 0.00421 -0.0251 0.3061 0.1786
6.500 0.8826 0.01237 0.00449 -0.0246 0.2768 0.1861
6.750 0.9055 0.01270 0.00484 -0.0241 0.2440 0.2678
7.000 0.9279 0.01318 0.00522 -0.0234 0.2095 0.2843
7.250 0.9498 0.01371 0.00565 -0.0226 0.1768 0.2977
7.500 0.9705 0.01432 0.00613 -0.0218 0.1419 0.3159
7.750 0.9887 0.01489 0.00671 -0.0206 0.1009 0.4347
8.000 0.9964 0.01429 0.00737 -0.0168 0.0785 0.9389
8.250 1.0261 0.01509 0.00811 -0.0179 0.0642 0.9783
8.500 1.0588 0.01576 0.00879 -0.0196 0.0573 0.9988
8.750 1.0762 0.01647 0.00948 -0.0181 0.0526 1.0000
9.000 1.0952 0.01696 0.01001 -0.0167 0.0500 1.0000
9.250 1.1137 0.01749 0.01058 -0.0153 0.0474 1.0000
9.500 1.1292 0.01821 0.01129 -0.0136 0.0448 1.0000
9.750 1.1436 0.01897 0.01211 -0.0116 0.0428 1.0000
10.000 1.1613 0.01950 0.01269 -0.0102 0.0410 1.0000
10.250 1.1764 0.02011 0.01334 -0.0085 0.0393 1.0000
10.500 1.1868 0.02089 0.01413 -0.0060 0.0377 1.0000
10.750 1.1897 0.02217 0.01545 -0.0027 0.0362 1.0000
11.000 1.2052 0.02278 0.01614 -0.0013 0.0351 1.0000
11.250 1.2186 0.02356 0.01698 0.0003 0.0337 1.0000
11.500 1.2307 0.02445 0.01792 0.0018 0.0324 1.0000
11.750 1.2397 0.02562 0.01912 0.0034 0.0313 1.0000
12.000 1.2393 0.02760 0.02114 0.0058 0.0301 1.0000
12.250 1.2522 0.02861 0.02226 0.0068 0.0294 1.0000
12.500 1.2630 0.02984 0.02357 0.0078 0.0284 1.0000
12.750 1.2729 0.03118 0.02499 0.0087 0.0275 1.0000
13.000 1.2819 0.03264 0.02650 0.0094 0.0266 1.0000
13.250 1.2879 0.03442 0.02831 0.0102 0.0258 1.0000
13.500 1.2853 0.03706 0.03099 0.0115 0.0249 1.0000
13.750 1.2939 0.03873 0.03279 0.0119 0.0245 1.0000
14.000 1.3003 0.04067 0.03484 0.0123 0.0238 1.0000
14.250 1.3054 0.04277 0.03705 0.0126 0.0232 1.0000
14.500 1.3097 0.04500 0.03936 0.0127 0.0226 1.0000
14.750 1.3133 0.04735 0.04180 0.0128 0.0221 1.0000
15.000 1.3159 0.04985 0.04436 0.0126 0.0217 1.0000
15.250 1.3166 0.05258 0.04714 0.0125 0.0212 1.0000
15.500 1.3131 0.05572 0.05034 0.0127 0.0207 1.0000
15.750 1.3114 0.05889 0.05363 0.0124 0.0204 1.0000
16.000 1.3112 0.06208 0.05696 0.0117 0.0200 1.0000
16.250 1.3100 0.06545 0.06046 0.0108 0.0196 1.0000
16.500 1.3077 0.06905 0.06419 0.0098 0.0193 1.0000
16.750 1.3047 0.07281 0.06807 0.0086 0.0189 1.0000
17.000 1.3010 0.07673 0.07211 0.0073 0.0186 1.0000
17.250 1.2969 0.08080 0.07628 0.0059 0.0183 1.0000
17.500 1.2925 0.08499 0.08057 0.0043 0.0181 1.0000
17.750 1.2877 0.08930 0.08496 0.0026 0.0178 1.0000
18.000 1.2824 0.09369 0.08944 0.0008 0.0176 1.0000
18.250 1.2765 0.09822 0.09405 -0.0010 0.0174 1.0000
18.500 1.2692 0.10298 0.09889 -0.0029 0.0172 1.0000
18.750 1.2579 0.10834 0.10436 -0.0050 0.0169 1.0000
19.000 1.2435 0.11451 0.11068 -0.0078 0.0168 1.0000
19.250 1.2307 0.12091 0.11724 -0.0113 0.0167 1.0000
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Polar data table (+)
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