MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.84 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske3-il-1000000-n5.txt Download as CSV file: xf-marske3-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24
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
------ -------- --------- --------- -------- -------- --------
-16.250 -1.1758 0.04642 0.04340 -0.0474 1.0000 0.0071
-16.000 -1.1887 0.04269 0.03952 -0.0474 1.0000 0.0072
-15.750 -1.1957 0.03987 0.03657 -0.0466 1.0000 0.0073
-15.500 -1.2059 0.03697 0.03349 -0.0450 1.0000 0.0073
-15.250 -1.2078 0.03496 0.03135 -0.0432 1.0000 0.0073
-15.000 -1.2043 0.03346 0.02978 -0.0414 1.0000 0.0074
-14.750 -1.2044 0.03173 0.02791 -0.0390 1.0000 0.0075
-14.500 -1.1986 0.03051 0.02660 -0.0368 1.0000 0.0076
-14.250 -1.1953 0.02911 0.02509 -0.0342 1.0000 0.0076
-14.000 -1.1900 0.02789 0.02374 -0.0315 1.0000 0.0077
-13.750 -1.1812 0.02695 0.02272 -0.0290 1.0000 0.0078
-13.500 -1.1736 0.02593 0.02160 -0.0262 1.0000 0.0079
-13.250 -1.1642 0.02508 0.02066 -0.0234 1.0000 0.0080
-13.000 -1.1550 0.02425 0.01973 -0.0205 1.0000 0.0081
-12.750 -1.1439 0.02346 0.01886 -0.0177 1.0000 0.0083
-12.500 -1.1302 0.02266 0.01796 -0.0155 1.0000 0.0084
-12.250 -1.1156 0.02187 0.01708 -0.0133 1.0000 0.0085
-12.000 -1.0999 0.02115 0.01628 -0.0113 1.0000 0.0085
-11.750 -1.0838 0.02043 0.01546 -0.0092 1.0000 0.0086
-11.500 -1.0664 0.01981 0.01477 -0.0074 1.0000 0.0087
-11.250 -1.0500 0.01907 0.01395 -0.0053 1.0000 0.0088
-11.000 -1.0327 0.01840 0.01322 -0.0034 1.0000 0.0091
-10.750 -1.0142 0.01784 0.01261 -0.0016 1.0000 0.0092
-10.500 -0.9948 0.01736 0.01210 0.0000 1.0000 0.0095
-10.250 -0.9753 0.01688 0.01158 0.0017 1.0000 0.0096
-10.000 -0.9555 0.01644 0.01110 0.0033 1.0000 0.0099
-9.750 -0.9359 0.01599 0.01061 0.0050 1.0000 0.0100
-9.500 -0.9159 0.01558 0.01017 0.0067 1.0000 0.0103
-9.250 -0.8962 0.01516 0.00969 0.0084 1.0000 0.0105
-9.000 -0.8669 0.01467 0.00916 0.0081 0.9981 0.0108
-8.750 -0.8358 0.01421 0.00865 0.0075 0.9897 0.0111
-8.500 -0.8009 0.01369 0.00810 0.0060 0.9779 0.0114
-8.250 -0.7515 0.01318 0.00759 0.0014 0.9598 0.0120
-8.000 -0.6954 0.01303 0.00697 -0.0045 0.7921 0.0127
-7.750 -0.6754 0.01298 0.00670 -0.0027 0.7389 0.0131
-7.500 -0.6526 0.01278 0.00637 -0.0015 0.7164 0.0136
-7.250 -0.6291 0.01255 0.00605 -0.0004 0.6995 0.0139
-7.000 -0.6052 0.01229 0.00576 0.0005 0.6883 0.0146
-6.750 -0.5802 0.01210 0.00554 0.0013 0.6793 0.0151
-6.500 -0.5553 0.01193 0.00533 0.0021 0.6679 0.0157
-6.250 -0.5305 0.01172 0.00507 0.0029 0.6572 0.0162
-6.000 -0.5055 0.01153 0.00483 0.0037 0.6458 0.0169
-5.750 -0.4806 0.01134 0.00459 0.0045 0.6326 0.0175
-5.500 -0.4553 0.01122 0.00444 0.0053 0.6150 0.0182
-5.250 -0.4298 0.01111 0.00428 0.0060 0.5971 0.0190
-5.000 -0.4048 0.01099 0.00408 0.0068 0.5730 0.0198
-4.750 -0.3799 0.01090 0.00388 0.0076 0.5469 0.0204
-4.500 -0.3555 0.01080 0.00367 0.0085 0.5172 0.0211
-4.250 -0.3305 0.01072 0.00352 0.0092 0.4907 0.0219
-4.000 -0.3053 0.01069 0.00340 0.0099 0.4645 0.0228
-3.750 -0.2802 0.01063 0.00324 0.0107 0.4375 0.0235
-3.500 -0.2548 0.01059 0.00311 0.0114 0.4143 0.0244
-3.250 -0.2291 0.01055 0.00298 0.0120 0.3944 0.0249
-3.000 -0.2046 0.01041 0.00278 0.0128 0.3725 0.0260
-2.750 -0.1793 0.01034 0.00264 0.0135 0.3533 0.0268
-2.500 -0.1536 0.01029 0.00253 0.0142 0.3359 0.0277
-2.250 -0.1278 0.01025 0.00243 0.0148 0.3219 0.0287
-2.000 -0.1019 0.01021 0.00233 0.0154 0.3084 0.0294
-1.750 -0.0760 0.01018 0.00223 0.0160 0.2955 0.0301
-1.500 -0.0503 0.01009 0.00212 0.0166 0.2860 0.0316
-1.250 -0.0244 0.01006 0.00204 0.0172 0.2765 0.0329
-1.000 0.0020 0.01001 0.00198 0.0176 0.2703 0.0341
-0.750 0.0284 0.00999 0.00192 0.0181 0.2635 0.0355
-0.500 0.0548 0.00996 0.00187 0.0186 0.2582 0.0385
-0.250 0.0810 0.00990 0.00183 0.0191 0.2533 0.0466
0.000 0.0997 0.00928 0.00174 0.0209 0.2484 0.2249
0.250 0.1183 0.00874 0.00165 0.0227 0.2434 0.3762
0.500 0.1222 0.00747 0.00147 0.0274 0.2405 0.6927
0.750 0.1433 0.00731 0.00151 0.0291 0.2360 0.7631
1.000 0.1680 0.00730 0.00156 0.0300 0.2315 0.7927
1.250 0.1936 0.00733 0.00161 0.0307 0.2272 0.8123
1.500 0.2201 0.00736 0.00166 0.0312 0.2242 0.8260
1.750 0.2470 0.00741 0.00171 0.0316 0.2205 0.8347
2.000 0.2741 0.00748 0.00176 0.0319 0.2166 0.8418
2.250 0.3006 0.00755 0.00182 0.0324 0.2124 0.8514
2.500 0.3273 0.00760 0.00189 0.0328 0.2099 0.8624
2.750 0.3542 0.00767 0.00196 0.0331 0.2069 0.8706
3.000 0.3811 0.00775 0.00203 0.0335 0.2030 0.8774
3.250 0.4081 0.00785 0.00211 0.0338 0.1989 0.8834
3.500 0.4351 0.00794 0.00220 0.0340 0.1959 0.8889
3.750 0.4624 0.00802 0.00228 0.0342 0.1938 0.8935
4.000 0.4899 0.00810 0.00237 0.0344 0.1913 0.8988
4.250 0.5168 0.00820 0.00247 0.0347 0.1886 0.9050
4.500 0.5438 0.00831 0.00257 0.0349 0.1857 0.9107
4.750 0.5712 0.00843 0.00270 0.0350 0.1826 0.9159
5.000 0.5983 0.00854 0.00282 0.0352 0.1807 0.9213
5.250 0.6259 0.00864 0.00293 0.0353 0.1783 0.9261
5.500 0.6542 0.00876 0.00306 0.0352 0.1749 0.9311
5.750 0.6813 0.00891 0.00319 0.0353 0.1709 0.9370
6.000 0.7101 0.00907 0.00335 0.0350 0.1679 0.9417
6.250 0.7394 0.00921 0.00351 0.0346 0.1661 0.9467
6.500 0.7677 0.00934 0.00365 0.0345 0.1644 0.9520
6.750 0.7992 0.00949 0.00383 0.0336 0.1624 0.9552
7.000 0.8297 0.00966 0.00400 0.0329 0.1603 0.9589
7.250 0.8579 0.00984 0.00418 0.0327 0.1578 0.9636
7.500 0.8900 0.01005 0.00439 0.0316 0.1546 0.9657
7.750 0.9216 0.01025 0.00460 0.0306 0.1524 0.9680
8.000 0.9523 0.01042 0.00480 0.0298 0.1510 0.9710
8.250 0.9809 0.01059 0.00500 0.0295 0.1492 0.9748
8.500 1.0134 0.01080 0.00522 0.0282 0.1470 0.9761
8.750 1.0446 0.01102 0.00545 0.0273 0.1444 0.9777
9.000 1.0743 0.01126 0.00570 0.0265 0.1418 0.9799
9.250 1.1025 0.01151 0.00597 0.0262 0.1393 0.9827
9.500 1.1309 0.01170 0.00620 0.0258 0.1375 0.9852
9.750 1.1617 0.01193 0.00646 0.0248 0.1348 0.9865
10.000 1.1916 0.01219 0.00673 0.0240 0.1314 0.9881
10.250 1.2205 0.01252 0.00705 0.0233 0.1270 0.9902
10.500 1.2494 0.01277 0.00733 0.0227 0.1234 0.9923
10.750 1.2768 0.01311 0.00766 0.0223 0.1178 0.9944
11.000 1.3059 0.01346 0.00802 0.0215 0.1131 0.9961
11.250 1.3346 0.01381 0.00839 0.0207 0.1085 0.9978
11.500 1.3621 0.01430 0.00885 0.0200 0.1009 0.9992
11.750 1.3849 0.01484 0.00935 0.0202 0.0939 1.0000
12.000 1.3996 0.01524 0.00978 0.0223 0.0897 1.0000
12.250 1.4133 0.01571 0.01024 0.0244 0.0856 1.0000
12.500 1.4264 0.01621 0.01076 0.0266 0.0816 1.0000
12.750 1.4418 0.01658 0.01118 0.0284 0.0797 1.0000
13.000 1.4547 0.01708 0.01169 0.0306 0.0762 1.0000
13.250 1.4657 0.01768 0.01230 0.0329 0.0727 1.0000
13.500 1.4764 0.01816 0.01283 0.0354 0.0704 1.0000
13.750 1.4838 0.01868 0.01339 0.0384 0.0674 1.0000
14.000 1.4884 0.01942 0.01413 0.0414 0.0635 1.0000
14.250 1.4936 0.02027 0.01500 0.0440 0.0583 1.0000
14.500 1.4969 0.02134 0.01608 0.0463 0.0541 1.0000
14.750 1.4988 0.02264 0.01740 0.0483 0.0488 1.0000
15.000 1.4982 0.02432 0.01912 0.0498 0.0442 1.0000
15.250 1.4965 0.02639 0.02123 0.0506 0.0405 1.0000
15.500 1.4954 0.02874 0.02365 0.0506 0.0377 1.0000
15.750 1.4905 0.03168 0.02666 0.0501 0.0349 1.0000
16.000 1.4819 0.03519 0.03025 0.0492 0.0320 1.0000
16.250 1.4773 0.03847 0.03363 0.0482 0.0313 1.0000
16.500 1.4631 0.04305 0.03832 0.0464 0.0297 1.0000
16.750 1.4435 0.04858 0.04398 0.0440 0.0286 1.0000
17.000 1.4215 0.05464 0.05018 0.0414 0.0278 1.0000
17.250 1.3946 0.06144 0.05713 0.0384 0.0276 1.0000
17.500 1.3674 0.06840 0.06424 0.0353 0.0282 1.0000
17.750 1.3310 0.07685 0.07284 0.0316 0.0279 1.0000
18.000 1.3007 0.08450 0.08063 0.0282 0.0286 1.0000
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Polar data table (+)
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