MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.53 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske5-il-1000000-n5.txt Download as CSV file: xf-marske5-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE MONARCH AIRFOIL (NACA 43012A)
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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.1652 0.04952 0.04656 -0.0473 1.0000 0.0086
-16.250 -1.1893 0.04440 0.04124 -0.0481 1.0000 0.0086
-16.000 -1.2091 0.04039 0.03704 -0.0471 1.0000 0.0087
-15.750 -1.2175 0.03772 0.03421 -0.0454 1.0000 0.0087
-15.500 -1.2270 0.03514 0.03148 -0.0430 1.0000 0.0088
-15.250 -1.2275 0.03338 0.02960 -0.0406 1.0000 0.0089
-15.000 -1.2269 0.03174 0.02783 -0.0380 1.0000 0.0089
-14.750 -1.2236 0.03035 0.02634 -0.0353 1.0000 0.0090
-14.500 -1.2190 0.02906 0.02494 -0.0325 1.0000 0.0091
-14.250 -1.2122 0.02795 0.02374 -0.0297 1.0000 0.0092
-14.000 -1.2041 0.02695 0.02265 -0.0269 1.0000 0.0093
-13.750 -1.1946 0.02607 0.02169 -0.0241 1.0000 0.0094
-13.500 -1.1854 0.02519 0.02072 -0.0212 1.0000 0.0094
-13.250 -1.1742 0.02439 0.01985 -0.0184 1.0000 0.0096
-13.000 -1.1606 0.02360 0.01898 -0.0160 1.0000 0.0096
-12.750 -1.1461 0.02279 0.01808 -0.0138 1.0000 0.0097
-12.500 -1.1299 0.02208 0.01729 -0.0117 1.0000 0.0099
-12.250 -1.1129 0.02142 0.01656 -0.0098 1.0000 0.0100
-12.000 -1.0960 0.02070 0.01576 -0.0078 1.0000 0.0102
-11.750 -1.0780 0.02006 0.01505 -0.0059 1.0000 0.0103
-11.500 -1.0597 0.01943 0.01435 -0.0040 1.0000 0.0105
-11.250 -1.0410 0.01883 0.01368 -0.0022 1.0000 0.0106
-11.000 -1.0217 0.01827 0.01305 -0.0004 1.0000 0.0107
-10.750 -1.0020 0.01775 0.01247 0.0013 1.0000 0.0108
-10.500 -0.9827 0.01717 0.01185 0.0031 1.0000 0.0111
-10.250 -0.9627 0.01667 0.01132 0.0048 1.0000 0.0114
-10.000 -0.9422 0.01622 0.01084 0.0064 1.0000 0.0116
-9.750 -0.9214 0.01582 0.01042 0.0080 1.0000 0.0118
-9.500 -0.8938 0.01536 0.00994 0.0082 0.9965 0.0120
-9.250 -0.8624 0.01489 0.00944 0.0076 0.9817 0.0124
-9.000 -0.7769 0.01433 0.00844 -0.0044 0.8104 0.0130
-8.750 -0.7575 0.01415 0.00802 -0.0024 0.7589 0.0131
-8.500 -0.7350 0.01391 0.00765 -0.0011 0.7368 0.0134
-8.250 -0.7124 0.01359 0.00725 0.0002 0.7183 0.0138
-8.000 -0.6887 0.01335 0.00696 0.0014 0.7026 0.0141
-7.750 -0.6644 0.01311 0.00667 0.0024 0.6910 0.0145
-7.500 -0.6402 0.01288 0.00639 0.0034 0.6760 0.0150
-7.250 -0.6159 0.01266 0.00610 0.0044 0.6597 0.0154
-7.000 -0.5917 0.01245 0.00580 0.0055 0.6379 0.0160
-6.750 -0.5677 0.01227 0.00551 0.0066 0.6077 0.0164
-6.500 -0.5441 0.01216 0.00527 0.0077 0.5626 0.0170
-6.250 -0.5201 0.01210 0.00507 0.0088 0.5166 0.0175
-6.000 -0.4962 0.01207 0.00487 0.0099 0.4639 0.0182
-5.750 -0.4731 0.01211 0.00465 0.0110 0.3886 0.0187
-5.500 -0.4492 0.01212 0.00445 0.0121 0.3329 0.0193
-5.250 -0.4247 0.01201 0.00426 0.0130 0.3069 0.0199
-4.750 -0.3734 0.01185 0.00401 0.0145 0.2798 0.0214
-4.500 -0.3478 0.01175 0.00385 0.0153 0.2701 0.0222
-4.250 -0.3220 0.01164 0.00369 0.0160 0.2633 0.0228
-4.000 -0.2969 0.01149 0.00351 0.0169 0.2550 0.0235
-3.750 -0.2709 0.01138 0.00339 0.0176 0.2493 0.0243
-3.500 -0.2449 0.01129 0.00327 0.0183 0.2433 0.0252
-3.250 -0.2189 0.01122 0.00316 0.0190 0.2375 0.0261
-3.000 -0.1927 0.01114 0.00304 0.0196 0.2332 0.0267
-2.750 -0.1672 0.01098 0.00288 0.0204 0.2291 0.0276
-2.500 -0.1412 0.01090 0.00278 0.0211 0.2244 0.0287
-2.250 -0.1151 0.01084 0.00268 0.0217 0.2194 0.0297
-2.000 -0.0888 0.01076 0.00259 0.0224 0.2161 0.0305
-1.750 -0.0625 0.01069 0.00250 0.0230 0.2126 0.0314
-1.500 -0.0366 0.01060 0.00240 0.0237 0.2087 0.0327
-1.250 -0.0105 0.01056 0.00233 0.0243 0.2036 0.0339
-1.000 0.0159 0.01052 0.00227 0.0249 0.2003 0.0351
-0.750 0.0425 0.01048 0.00222 0.0255 0.1974 0.0365
-0.500 0.0687 0.01043 0.00217 0.0261 0.1942 0.0390
-0.250 0.0951 0.01041 0.00214 0.0266 0.1908 0.0418
0.000 0.1213 0.01039 0.00211 0.0272 0.1874 0.0485
0.250 0.1464 0.01026 0.00210 0.0280 0.1854 0.0850
0.500 0.1621 0.00946 0.00201 0.0304 0.1839 0.3260
0.750 0.1700 0.00840 0.00185 0.0343 0.1824 0.6036
1.000 0.1768 0.00769 0.00186 0.0391 0.1808 0.8031
1.250 0.2002 0.00766 0.00194 0.0404 0.1787 0.8441
1.500 0.2261 0.00771 0.00201 0.0411 0.1763 0.8617
1.750 0.2525 0.00779 0.00208 0.0417 0.1740 0.8745
2.000 0.2789 0.00788 0.00216 0.0423 0.1715 0.8850
2.250 0.3063 0.00795 0.00224 0.0427 0.1706 0.8940
2.500 0.3330 0.00803 0.00232 0.0432 0.1696 0.9028
2.750 0.3607 0.00811 0.00241 0.0435 0.1683 0.9103
3.000 0.3881 0.00820 0.00249 0.0438 0.1669 0.9159
3.250 0.4150 0.00830 0.00256 0.0442 0.1653 0.9192
3.500 0.4424 0.00840 0.00264 0.0444 0.1637 0.9221
3.750 0.4708 0.00851 0.00273 0.0444 0.1622 0.9248
4.000 0.4988 0.00863 0.00284 0.0445 0.1607 0.9279
4.250 0.5261 0.00876 0.00296 0.0447 0.1591 0.9315
4.500 0.5522 0.00890 0.00309 0.0452 0.1576 0.9353
4.750 0.5810 0.00902 0.00321 0.0451 0.1570 0.9381
5.000 0.6102 0.00914 0.00334 0.0448 0.1564 0.9409
5.250 0.6387 0.00926 0.00346 0.0447 0.1557 0.9443
5.500 0.6656 0.00938 0.00359 0.0450 0.1549 0.9484
5.750 0.6950 0.00951 0.00373 0.0447 0.1537 0.9512
6.000 0.7255 0.00966 0.00388 0.0441 0.1525 0.9536
6.250 0.7553 0.00981 0.00403 0.0437 0.1513 0.9563
6.500 0.7833 0.00996 0.00418 0.0436 0.1501 0.9597
6.750 0.8115 0.01012 0.00434 0.0434 0.1489 0.9628
7.000 0.8430 0.01031 0.00453 0.0426 0.1476 0.9643
7.250 0.8740 0.01052 0.00473 0.0418 0.1461 0.9660
7.500 0.9037 0.01076 0.00497 0.0412 0.1445 0.9681
7.750 0.9325 0.01093 0.00517 0.0409 0.1438 0.9707
8.000 0.9600 0.01108 0.00534 0.0408 0.1431 0.9737
8.250 0.9922 0.01126 0.00554 0.0397 0.1423 0.9746
8.500 1.0238 0.01144 0.00575 0.0387 0.1414 0.9757
8.750 1.0547 0.01164 0.00597 0.0379 0.1405 0.9770
9.000 1.0847 0.01185 0.00620 0.0372 0.1396 0.9786
9.250 1.1136 0.01205 0.00643 0.0367 0.1385 0.9805
9.500 1.1403 0.01227 0.00666 0.0367 0.1374 0.9832
9.750 1.1692 0.01249 0.00691 0.0362 0.1363 0.9847
10.000 1.1994 0.01274 0.00717 0.0353 0.1351 0.9857
10.250 1.2290 0.01301 0.00745 0.0346 0.1337 0.9870
10.500 1.2577 0.01332 0.00779 0.0340 0.1322 0.9885
10.750 1.2865 0.01354 0.00806 0.0334 0.1316 0.9901
11.000 1.3148 0.01377 0.00834 0.0329 0.1308 0.9919
11.250 1.3421 0.01402 0.00863 0.0326 0.1299 0.9937
11.500 1.3716 0.01427 0.00893 0.0318 0.1286 0.9950
11.750 1.4008 0.01453 0.00923 0.0310 0.1272 0.9964
12.000 1.4296 0.01481 0.00953 0.0303 0.1252 0.9977
12.250 1.4578 0.01513 0.00987 0.0296 0.1232 0.9989
12.500 1.4856 0.01550 0.01026 0.0289 0.1209 0.9998
12.750 1.5046 0.01576 0.01057 0.0301 0.1197 1.0000
13.000 1.5205 0.01603 0.01089 0.0320 0.1180 1.0000
13.250 1.5360 0.01633 0.01123 0.0338 0.1160 1.0000
13.500 1.5507 0.01667 0.01159 0.0357 0.1136 1.0000
13.750 1.5638 0.01710 0.01202 0.0378 0.1099 1.0000
14.000 1.5775 0.01750 0.01245 0.0398 0.1066 1.0000
14.250 1.5843 0.01802 0.01296 0.0429 0.1020 1.0000
14.500 1.5907 0.01855 0.01351 0.0459 0.0985 1.0000
14.750 1.5978 0.01917 0.01416 0.0485 0.0953 1.0000
15.000 1.6041 0.01995 0.01496 0.0509 0.0923 1.0000
15.250 1.6126 0.02070 0.01577 0.0527 0.0902 1.0000
15.500 1.6204 0.02159 0.01671 0.0544 0.0881 1.0000
15.750 1.6256 0.02274 0.01791 0.0558 0.0856 1.0000
16.000 1.6293 0.02416 0.01938 0.0569 0.0835 1.0000
16.250 1.6337 0.02570 0.02099 0.0575 0.0810 1.0000
16.500 1.6395 0.02727 0.02264 0.0577 0.0799 1.0000
16.750 1.6404 0.02938 0.02483 0.0576 0.0776 1.0000
17.000 1.6361 0.03213 0.02764 0.0573 0.0752 1.0000
17.250 1.6303 0.03517 0.03077 0.0566 0.0732 1.0000
17.500 1.6268 0.03812 0.03382 0.0557 0.0718 1.0000
17.750 1.6160 0.04202 0.03784 0.0543 0.0700 1.0000
18.000 1.5987 0.04695 0.04289 0.0522 0.0688 1.0000
18.250 1.5597 0.05501 0.05111 0.0484 0.0672 1.0000
18.500 1.5152 0.06432 0.06063 0.0439 0.0677 1.0000
18.750 1.4660 0.07445 0.07099 0.0391 0.0696 1.0000
19.000 1.3947 0.08772 0.08446 0.0327 0.0707 1.0000
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