MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Reynolds number: 1,000,000 Max Cl/Cd: 97 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske2-il-1000000-n5.txt Download as CSV file: xf-marske2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYB
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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.2377 0.05400 0.05095 -0.0466 1.0000 0.0084
-17.250 -1.2565 0.04869 0.04548 -0.0488 1.0000 0.0085
-17.000 -1.2706 0.04456 0.04118 -0.0495 1.0000 0.0086
-16.750 -1.2822 0.04109 0.03756 -0.0492 1.0000 0.0086
-16.500 -1.2891 0.03833 0.03466 -0.0482 1.0000 0.0086
-16.250 -1.2903 0.03622 0.03244 -0.0469 1.0000 0.0087
-16.000 -1.2890 0.03443 0.03055 -0.0453 1.0000 0.0088
-15.750 -1.2879 0.03271 0.02871 -0.0434 1.0000 0.0089
-15.500 -1.2852 0.03116 0.02705 -0.0413 1.0000 0.0090
-15.250 -1.2801 0.02983 0.02562 -0.0392 1.0000 0.0091
-15.000 -1.2743 0.02858 0.02426 -0.0369 1.0000 0.0092
-14.750 -1.2662 0.02752 0.02311 -0.0346 1.0000 0.0093
-14.500 -1.2575 0.02651 0.02201 -0.0322 1.0000 0.0094
-14.250 -1.2480 0.02557 0.02098 -0.0298 1.0000 0.0095
-14.000 -1.2377 0.02468 0.01999 -0.0274 1.0000 0.0097
-13.750 -1.2267 0.02388 0.01910 -0.0249 1.0000 0.0098
-13.500 -1.2152 0.02312 0.01827 -0.0223 1.0000 0.0099
-13.250 -1.2032 0.02241 0.01747 -0.0197 1.0000 0.0099
-13.000 -1.1891 0.02179 0.01678 -0.0174 1.0000 0.0101
-12.750 -1.1749 0.02100 0.01593 -0.0152 1.0000 0.0103
-12.500 -1.1587 0.02032 0.01518 -0.0132 1.0000 0.0105
-12.250 -1.1415 0.01969 0.01451 -0.0114 1.0000 0.0107
-12.000 -1.1234 0.01914 0.01391 -0.0096 1.0000 0.0109
-11.750 -1.1047 0.01861 0.01334 -0.0079 1.0000 0.0112
-11.500 -1.0856 0.01812 0.01282 -0.0063 1.0000 0.0115
-11.250 -1.0662 0.01764 0.01228 -0.0047 1.0000 0.0118
-11.000 -1.0468 0.01715 0.01175 -0.0030 1.0000 0.0121
-10.750 -1.0270 0.01669 0.01124 -0.0014 1.0000 0.0123
-10.500 -1.0069 0.01627 0.01076 0.0002 1.0000 0.0125
-10.250 -0.9873 0.01579 0.01026 0.0019 1.0000 0.0129
-10.000 -0.9670 0.01538 0.00984 0.0034 1.0000 0.0133
-9.750 -0.9464 0.01501 0.00945 0.0050 1.0000 0.0137
-9.500 -0.9258 0.01466 0.00908 0.0066 1.0000 0.0141
-9.250 -0.9052 0.01431 0.00871 0.0082 1.0000 0.0145
-9.000 -0.8848 0.01398 0.00834 0.0098 1.0000 0.0149
-8.750 -0.8525 0.01357 0.00790 0.0089 0.9966 0.0153
-8.500 -0.8219 0.01318 0.00752 0.0084 0.9875 0.0160
-8.250 -0.7834 0.01282 0.00717 0.0062 0.9754 0.0167
-8.000 -0.7182 0.01236 0.00666 -0.0017 0.9399 0.0179
-7.750 -0.6823 0.01221 0.00622 -0.0032 0.8446 0.0185
-7.500 -0.6632 0.01219 0.00596 -0.0011 0.7751 0.0191
-7.250 -0.6405 0.01210 0.00576 0.0002 0.7430 0.0197
-7.000 -0.6165 0.01195 0.00553 0.0012 0.7252 0.0203
-6.750 -0.5921 0.01180 0.00530 0.0021 0.7097 0.0211
-6.250 -0.5432 0.01145 0.00482 0.0039 0.6779 0.0223
-6.000 -0.5179 0.01128 0.00464 0.0047 0.6676 0.0231
-5.750 -0.4926 0.01113 0.00445 0.0054 0.6561 0.0238
-5.500 -0.4674 0.01098 0.00424 0.0062 0.6395 0.0245
-5.250 -0.4421 0.01086 0.00404 0.0070 0.6196 0.0253
-5.000 -0.4171 0.01074 0.00384 0.0078 0.5958 0.0259
-4.750 -0.3930 0.01061 0.00361 0.0087 0.5614 0.0267
-4.500 -0.3684 0.01056 0.00345 0.0096 0.5259 0.0275
-4.250 -0.3434 0.01052 0.00330 0.0104 0.4936 0.0284
-4.000 -0.3184 0.01049 0.00315 0.0111 0.4602 0.0292
-3.750 -0.2935 0.01048 0.00301 0.0119 0.4228 0.0298
-3.500 -0.2686 0.01044 0.00285 0.0127 0.3889 0.0307
-3.250 -0.2437 0.01040 0.00271 0.0135 0.3588 0.0318
-3.000 -0.2183 0.01038 0.00260 0.0141 0.3317 0.0327
-2.750 -0.1927 0.01036 0.00249 0.0148 0.3100 0.0337
-2.500 -0.1668 0.01034 0.00240 0.0154 0.2924 0.0348
-2.250 -0.1408 0.01030 0.00230 0.0160 0.2789 0.0358
-2.000 -0.1148 0.01023 0.00221 0.0166 0.2695 0.0373
-1.750 -0.0885 0.01019 0.00214 0.0171 0.2615 0.0390
-1.500 -0.0620 0.01014 0.00207 0.0176 0.2556 0.0409
-1.250 -0.0355 0.01009 0.00201 0.0181 0.2501 0.0440
-1.000 -0.0091 0.01006 0.00197 0.0186 0.2441 0.0480
-0.750 0.0173 0.01000 0.00192 0.0191 0.2393 0.0544
-0.500 0.0438 0.00995 0.00189 0.0195 0.2347 0.0643
-0.250 0.0693 0.00985 0.00185 0.0202 0.2291 0.0940
0.000 0.0859 0.00905 0.00172 0.0222 0.2245 0.3171
0.250 0.0983 0.00808 0.00157 0.0252 0.2222 0.5594
0.500 0.1122 0.00747 0.00152 0.0282 0.2194 0.7164
0.750 0.1338 0.00732 0.00156 0.0298 0.2157 0.7806
1.000 0.1577 0.00729 0.00163 0.0310 0.2116 0.8195
1.250 0.1834 0.00731 0.00169 0.0317 0.2078 0.8412
1.500 0.2100 0.00735 0.00175 0.0322 0.2053 0.8562
1.750 0.2361 0.00739 0.00182 0.0329 0.2023 0.8748
2.000 0.2623 0.00747 0.00189 0.0335 0.1985 0.8876
2.250 0.2898 0.00756 0.00196 0.0337 0.1944 0.8945
2.500 0.3169 0.00764 0.00203 0.0341 0.1914 0.9015
2.750 0.3441 0.00771 0.00209 0.0344 0.1891 0.9071
3.000 0.3722 0.00779 0.00217 0.0345 0.1865 0.9116
3.250 0.3997 0.00789 0.00225 0.0347 0.1837 0.9161
3.500 0.4264 0.00800 0.00232 0.0350 0.1808 0.9206
3.750 0.4543 0.00811 0.00243 0.0351 0.1777 0.9241
4.000 0.4827 0.00820 0.00252 0.0351 0.1764 0.9279
4.250 0.5104 0.00830 0.00262 0.0352 0.1746 0.9324
4.500 0.5373 0.00840 0.00272 0.0355 0.1723 0.9367
4.750 0.5665 0.00852 0.00283 0.0352 0.1697 0.9398
5.000 0.5951 0.00866 0.00295 0.0351 0.1674 0.9436
5.250 0.6224 0.00880 0.00309 0.0352 0.1649 0.9481
5.500 0.6514 0.00894 0.00323 0.0350 0.1626 0.9516
5.750 0.6820 0.00907 0.00336 0.0344 0.1608 0.9543
6.000 0.7117 0.00920 0.00351 0.0340 0.1589 0.9575
6.250 0.7391 0.00934 0.00364 0.0340 0.1567 0.9616
6.500 0.7702 0.00951 0.00381 0.0332 0.1544 0.9638
6.750 0.8017 0.00970 0.00399 0.0323 0.1520 0.9658
7.000 0.8322 0.00990 0.00419 0.0316 0.1497 0.9682
7.250 0.8615 0.01006 0.00437 0.0312 0.1486 0.9711
7.500 0.8900 0.01021 0.00454 0.0310 0.1476 0.9740
7.750 0.9223 0.01039 0.00474 0.0299 0.1460 0.9750
8.000 0.9540 0.01057 0.00494 0.0289 0.1441 0.9763
8.250 0.9849 0.01077 0.00514 0.0280 0.1415 0.9779
8.500 1.0146 0.01100 0.00536 0.0274 0.1386 0.9799
8.750 1.0426 0.01124 0.00561 0.0271 0.1361 0.9824
9.000 1.0710 0.01142 0.00582 0.0268 0.1348 0.9846
9.250 1.1020 0.01162 0.00605 0.0259 0.1329 0.9856
9.500 1.1326 0.01184 0.00629 0.0250 0.1305 0.9870
9.750 1.1625 0.01209 0.00654 0.0242 0.1279 0.9886
10.000 1.1915 0.01237 0.00683 0.0236 0.1249 0.9905
10.250 1.2199 0.01261 0.00710 0.0232 0.1221 0.9924
10.500 1.2479 0.01287 0.00738 0.0228 0.1190 0.9942
10.750 1.2775 0.01317 0.00768 0.0219 0.1154 0.9957
11.000 1.3067 0.01350 0.00802 0.0211 0.1118 0.9972
11.250 1.3359 0.01379 0.00835 0.0204 0.1088 0.9986
11.500 1.3644 0.01415 0.00872 0.0197 0.1048 0.9997
11.750 1.3846 0.01453 0.00910 0.0207 0.1013 1.0000
12.000 1.4015 0.01482 0.00943 0.0224 0.0990 1.0000
12.250 1.4175 0.01518 0.00981 0.0242 0.0957 1.0000
12.500 1.4324 0.01561 0.01024 0.0262 0.0922 1.0000
12.750 1.4477 0.01602 0.01067 0.0280 0.0885 1.0000
13.000 1.4613 0.01652 0.01117 0.0301 0.0842 1.0000
13.250 1.4740 0.01707 0.01173 0.0322 0.0799 1.0000
13.500 1.4853 0.01768 0.01234 0.0345 0.0744 1.0000
13.750 1.4936 0.01826 0.01294 0.0373 0.0714 1.0000
14.000 1.4996 0.01889 0.01358 0.0404 0.0664 1.0000
14.250 1.5037 0.01972 0.01441 0.0433 0.0612 1.0000
14.500 1.5066 0.02075 0.01545 0.0460 0.0555 1.0000
14.750 1.5064 0.02209 0.01680 0.0485 0.0489 1.0000
15.000 1.5103 0.02336 0.01810 0.0501 0.0457 1.0000
15.250 1.5104 0.02506 0.01984 0.0514 0.0424 1.0000
15.500 1.5114 0.02693 0.02177 0.0521 0.0397 1.0000
15.750 1.5132 0.02895 0.02387 0.0522 0.0384 1.0000
16.000 1.5110 0.03153 0.02653 0.0520 0.0368 1.0000
16.250 1.5071 0.03443 0.02952 0.0514 0.0351 1.0000
16.500 1.5025 0.03761 0.03279 0.0505 0.0342 1.0000
16.750 1.4937 0.04144 0.03674 0.0491 0.0334 1.0000
17.000 1.4794 0.04623 0.04165 0.0470 0.0329 1.0000
17.250 1.4566 0.05238 0.04795 0.0442 0.0323 1.0000
17.500 1.4286 0.05948 0.05521 0.0408 0.0324 1.0000
17.750 1.3869 0.06874 0.06466 0.0364 0.0325 1.0000
18.000 1.3397 0.07894 0.07507 0.0317 0.0328 1.0000
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Polar data table (+)
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