MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 98.96 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske2-il-1000000.txt Download as CSV file: xf-marske2-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0738 0.04669 0.04395 -0.0411 1.0000 0.0136
-14.500 -1.1042 0.04144 0.03842 -0.0403 1.0000 0.0137
-14.250 -1.1202 0.03805 0.03481 -0.0383 1.0000 0.0137
-14.000 -1.1252 0.03584 0.03244 -0.0360 1.0000 0.0139
-13.750 -1.1363 0.03316 0.02953 -0.0328 1.0000 0.0140
-13.500 -1.1346 0.03162 0.02784 -0.0301 1.0000 0.0142
-13.250 -1.1360 0.02982 0.02586 -0.0267 1.0000 0.0142
-13.000 -1.1301 0.02863 0.02453 -0.0239 1.0000 0.0145
-12.750 -1.1219 0.02770 0.02347 -0.0211 1.0000 0.0146
-12.500 -1.1212 0.02602 0.02159 -0.0172 1.0000 0.0149
-12.250 -1.1180 0.02438 0.01977 -0.0136 1.0000 0.0150
-12.000 -1.1037 0.02374 0.01910 -0.0114 1.0000 0.0153
-11.750 -1.0882 0.02310 0.01841 -0.0094 1.0000 0.0155
-11.500 -1.0719 0.02244 0.01771 -0.0075 1.0000 0.0157
-11.250 -1.0531 0.02211 0.01735 -0.0058 1.0000 0.0160
-11.000 -1.0352 0.02157 0.01676 -0.0040 1.0000 0.0163
-10.750 -1.0175 0.02088 0.01598 -0.0022 1.0000 0.0166
-10.500 -0.9992 0.02023 0.01525 -0.0005 1.0000 0.0169
-10.250 -0.9804 0.01960 0.01453 0.0012 1.0000 0.0173
-10.000 -0.9608 0.01907 0.01391 0.0029 1.0000 0.0175
-9.750 -0.9434 0.01810 0.01283 0.0048 1.0000 0.0180
-9.500 -0.9238 0.01763 0.01236 0.0064 1.0000 0.0184
-9.250 -0.9029 0.01736 0.01210 0.0079 1.0000 0.0188
-9.000 -0.8820 0.01703 0.01175 0.0094 1.0000 0.0191
-8.750 -0.8613 0.01666 0.01134 0.0109 1.0000 0.0196
-8.500 -0.8407 0.01623 0.01087 0.0125 1.0000 0.0201
-8.250 -0.8201 0.01583 0.01040 0.0141 1.0000 0.0205
-8.000 -0.7992 0.01549 0.01001 0.0157 1.0000 0.0209
-7.750 -0.7813 0.01465 0.00912 0.0177 1.0000 0.0215
-7.500 -0.7613 0.01431 0.00880 0.0194 1.0000 0.0220
-7.250 -0.7348 0.01406 0.00856 0.0197 0.9992 0.0226
-7.000 -0.6945 0.01375 0.00824 0.0172 0.9942 0.0234
-6.750 -0.6565 0.01341 0.00787 0.0152 0.9842 0.0242
-6.500 -0.6125 0.01266 0.00708 0.0118 0.9692 0.0252
-6.250 -0.5522 0.01209 0.00651 0.0049 0.9310 0.0263
-6.000 -0.5207 0.01199 0.00614 0.0045 0.8402 0.0271
-5.750 -0.4997 0.01195 0.00588 0.0062 0.7855 0.0279
-5.500 -0.4760 0.01190 0.00569 0.0073 0.7577 0.0286
-5.250 -0.4545 0.01145 0.00515 0.0088 0.7386 0.0296
-5.000 -0.4309 0.01120 0.00486 0.0099 0.7239 0.0304
-4.750 -0.4064 0.01103 0.00464 0.0108 0.7105 0.0313
-4.500 -0.3816 0.01085 0.00442 0.0116 0.6969 0.0322
-4.250 -0.3561 0.01073 0.00425 0.0124 0.6826 0.0332
-4.000 -0.3323 0.01043 0.00390 0.0134 0.6688 0.0341
-3.750 -0.3087 0.01014 0.00358 0.0145 0.6530 0.0353
-3.500 -0.2838 0.01000 0.00338 0.0153 0.6315 0.0364
-3.250 -0.2587 0.00991 0.00321 0.0162 0.6035 0.0378
-3.000 -0.2340 0.00985 0.00302 0.0171 0.5682 0.0387
-2.750 -0.2106 0.00971 0.00275 0.0182 0.5300 0.0402
-2.500 -0.1865 0.00967 0.00258 0.0191 0.4916 0.0418
-2.250 -0.1617 0.00968 0.00247 0.0199 0.4524 0.0437
-2.000 -0.1366 0.00974 0.00237 0.0207 0.4104 0.0453
-1.750 -0.1127 0.00972 0.00221 0.0216 0.3681 0.0484
-1.500 -0.0877 0.00976 0.00213 0.0223 0.3338 0.0516
-1.250 -0.0625 0.00974 0.00204 0.0231 0.3108 0.0572
-1.000 -0.0373 0.00968 0.00196 0.0238 0.2946 0.0699
-0.750 -0.0182 0.00911 0.00182 0.0255 0.2830 0.2116
-0.500 -0.0146 0.00759 0.00154 0.0300 0.2770 0.5700
-0.250 -0.0056 0.00689 0.00150 0.0341 0.2698 0.7556
0.000 0.0161 0.00679 0.00157 0.0358 0.2632 0.8130
0.250 0.0407 0.00681 0.00164 0.0369 0.2564 0.8431
0.500 0.0664 0.00689 0.00171 0.0377 0.2492 0.8608
0.750 0.0927 0.00694 0.00176 0.0383 0.2448 0.8745
1.000 0.1181 0.00703 0.00184 0.0392 0.2396 0.8896
1.250 0.1454 0.00715 0.00194 0.0396 0.2332 0.8990
1.500 0.1714 0.00721 0.00199 0.0403 0.2302 0.9078
1.750 0.1988 0.00732 0.00210 0.0408 0.2261 0.9183
2.000 0.2250 0.00742 0.00218 0.0414 0.2216 0.9256
2.250 0.2534 0.00757 0.00229 0.0415 0.2166 0.9304
2.500 0.2806 0.00764 0.00236 0.0419 0.2139 0.9362
2.750 0.3074 0.00773 0.00243 0.0423 0.2104 0.9413
3.000 0.3374 0.00785 0.00252 0.0420 0.2062 0.9445
3.250 0.3659 0.00803 0.00266 0.0420 0.2014 0.9479
3.500 0.3942 0.00811 0.00274 0.0420 0.1997 0.9517
3.750 0.4200 0.00819 0.00281 0.0426 0.1973 0.9559
4.000 0.4522 0.00831 0.00292 0.0417 0.1944 0.9578
4.250 0.4838 0.00847 0.00305 0.0410 0.1913 0.9598
4.500 0.5148 0.00870 0.00323 0.0403 0.1869 0.9620
4.750 0.5461 0.00881 0.00335 0.0396 0.1852 0.9643
5.000 0.5751 0.00893 0.00348 0.0394 0.1834 0.9674
5.250 0.6031 0.00904 0.00359 0.0394 0.1810 0.9705
5.500 0.6372 0.00920 0.00373 0.0380 0.1782 0.9714
5.750 0.6713 0.00940 0.00390 0.0366 0.1749 0.9721
6.000 0.7045 0.00966 0.00414 0.0353 0.1717 0.9730
6.250 0.7382 0.00977 0.00428 0.0340 0.1704 0.9739
6.500 0.7715 0.00991 0.00443 0.0328 0.1685 0.9751
6.750 0.8040 0.01006 0.00459 0.0318 0.1665 0.9765
7.000 0.8352 0.01024 0.00476 0.0309 0.1644 0.9784
7.250 0.8629 0.01044 0.00496 0.0309 0.1622 0.9814
7.500 0.8922 0.01071 0.00522 0.0303 0.1594 0.9833
7.750 0.9253 0.01093 0.00546 0.0290 0.1575 0.9841
8.000 0.9589 0.01106 0.00563 0.0277 0.1562 0.9850
8.250 0.9921 0.01120 0.00579 0.0264 0.1541 0.9861
8.500 1.0246 0.01135 0.00595 0.0252 0.1515 0.9874
8.750 1.0561 0.01155 0.00615 0.0242 0.1489 0.9889
9.000 1.0854 0.01190 0.00649 0.0235 0.1450 0.9909
9.250 1.1156 0.01204 0.00668 0.0228 0.1437 0.9927
9.500 1.1469 0.01219 0.00687 0.0219 0.1419 0.9941
9.750 1.1798 0.01234 0.00705 0.0205 0.1393 0.9951
10.000 1.2120 0.01255 0.00726 0.0193 0.1363 0.9963
10.250 1.2426 0.01290 0.00760 0.0182 0.1322 0.9977
10.500 1.2748 0.01301 0.00777 0.0170 0.1302 0.9989
10.750 1.3063 0.01320 0.00799 0.0159 0.1272 0.9998
11.000 1.3260 0.01343 0.00824 0.0172 0.1245 1.0000
11.250 1.3417 0.01374 0.00855 0.0192 0.1212 1.0000
11.500 1.3591 0.01396 0.00881 0.0209 0.1189 1.0000
11.750 1.3765 0.01418 0.00907 0.0227 0.1163 1.0000
12.000 1.3928 0.01447 0.00936 0.0245 0.1124 1.0000
12.250 1.4080 0.01483 0.00973 0.0265 0.1085 1.0000
12.500 1.4252 0.01510 0.01004 0.0282 0.1055 1.0000
12.750 1.4404 0.01549 0.01042 0.0301 0.1010 1.0000
13.000 1.4552 0.01590 0.01085 0.0321 0.0969 1.0000
13.250 1.4702 0.01631 0.01128 0.0339 0.0930 1.0000
13.500 1.4822 0.01689 0.01185 0.0362 0.0882 1.0000
13.750 1.4962 0.01734 0.01233 0.0381 0.0844 1.0000
14.000 1.5063 0.01799 0.01299 0.0405 0.0798 1.0000
14.250 1.5136 0.01855 0.01358 0.0435 0.0757 1.0000
14.500 1.5169 0.01931 0.01434 0.0468 0.0707 1.0000
14.750 1.5219 0.02013 0.01518 0.0495 0.0652 1.0000
15.000 1.5238 0.02125 0.01630 0.0521 0.0595 1.0000
15.250 1.5228 0.02271 0.01777 0.0544 0.0534 1.0000
15.500 1.5213 0.02443 0.01952 0.0559 0.0484 1.0000
15.750 1.5199 0.02641 0.02155 0.0568 0.0451 1.0000
16.000 1.5154 0.02898 0.02418 0.0570 0.0423 1.0000
16.250 1.5109 0.03181 0.02710 0.0566 0.0404 1.0000
16.500 1.5063 0.03485 0.03023 0.0558 0.0390 1.0000
16.750 1.4971 0.03861 0.03410 0.0545 0.0379 1.0000
17.000 1.4809 0.04350 0.03912 0.0524 0.0370 1.0000
17.250 1.4581 0.04959 0.04536 0.0495 0.0365 1.0000
17.500 1.4252 0.05739 0.05332 0.0456 0.0361 1.0000
17.750 1.3887 0.06584 0.06196 0.0415 0.0365 1.0000
18.000 1.3415 0.07595 0.07226 0.0367 0.0369 1.0000
18.250 1.2949 0.08606 0.08254 0.0319 0.0372 1.0000
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Polar data table (+)
Polar graphs
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