RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Reynolds number: 200,000 Max Cl/Cd: 61.19 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1082-il-200000-n5.txt Download as CSV file: xf-r1082-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4470 0.08863 0.08493 -0.0739 0.9589 0.0168
-13.250 -0.5067 0.06810 0.06402 -0.0911 0.9408 0.0162
-13.000 -0.5289 0.05662 0.05205 -0.1043 0.9163 0.0159
-12.750 -0.5305 0.04951 0.04442 -0.1136 0.8863 0.0160
-12.500 -0.5330 0.04472 0.03912 -0.1179 0.8559 0.0163
-12.250 -0.5369 0.04138 0.03535 -0.1188 0.8308 0.0165
-12.000 -0.5389 0.03880 0.03241 -0.1182 0.8117 0.0166
-11.750 -0.5382 0.03682 0.03011 -0.1168 0.7958 0.0166
-11.500 -0.5370 0.03495 0.02793 -0.1149 0.7823 0.0168
-11.250 -0.5330 0.03331 0.02600 -0.1130 0.7708 0.0170
-11.000 -0.5257 0.03180 0.02419 -0.1112 0.7607 0.0171
-10.750 -0.5156 0.03045 0.02262 -0.1096 0.7515 0.0173
-10.500 -0.5026 0.02927 0.02129 -0.1082 0.7431 0.0175
-10.250 -0.4893 0.02820 0.02013 -0.1068 0.7353 0.0178
-10.000 -0.4750 0.02726 0.01905 -0.1055 0.7280 0.0180
-9.750 -0.4601 0.02635 0.01803 -0.1041 0.7217 0.0184
-9.500 -0.4447 0.02548 0.01704 -0.1027 0.7151 0.0189
-9.250 -0.4285 0.02467 0.01610 -0.1014 0.7097 0.0192
-9.000 -0.4121 0.02387 0.01518 -0.1000 0.7047 0.0197
-8.750 -0.3957 0.02314 0.01434 -0.0986 0.6996 0.0203
-8.500 -0.3798 0.02245 0.01354 -0.0971 0.6950 0.0210
-8.250 -0.3648 0.02183 0.01287 -0.0955 0.6911 0.0218
-8.000 -0.3488 0.02132 0.01231 -0.0939 0.6870 0.0228
-7.750 -0.3334 0.02078 0.01169 -0.0922 0.6829 0.0237
-7.500 -0.3179 0.02029 0.01110 -0.0903 0.6791 0.0248
-7.250 -0.3028 0.01978 0.01054 -0.0885 0.6758 0.0259
-7.000 -0.2852 0.01934 0.01002 -0.0870 0.6727 0.0272
-6.750 -0.2674 0.01888 0.00951 -0.0855 0.6690 0.0294
-6.500 -0.2495 0.01843 0.00904 -0.0841 0.6654 0.0323
-6.250 -0.2309 0.01800 0.00860 -0.0827 0.6623 0.0372
-6.000 -0.2121 0.01759 0.00818 -0.0814 0.6596 0.0462
-5.750 -0.1930 0.01719 0.00780 -0.0802 0.6573 0.0593
-5.500 -0.1732 0.01685 0.00750 -0.0790 0.6548 0.0749
-5.250 -0.1536 0.01652 0.00724 -0.0779 0.6521 0.0919
-5.000 -0.1337 0.01620 0.00699 -0.0768 0.6495 0.1142
-4.750 -0.1152 0.01580 0.00675 -0.0755 0.6470 0.1472
-4.500 -0.0984 0.01531 0.00649 -0.0739 0.6448 0.1972
-4.250 -0.0820 0.01481 0.00623 -0.0723 0.6427 0.2557
-4.000 -0.0660 0.01431 0.00596 -0.0706 0.6408 0.3241
-3.750 -0.0518 0.01373 0.00574 -0.0684 0.6387 0.4096
-3.500 -0.0386 0.01315 0.00562 -0.0660 0.6362 0.5119
-3.250 -0.0206 0.01293 0.00592 -0.0637 0.6340 0.6185
-3.000 0.0048 0.01324 0.00639 -0.0625 0.6319 0.6816
-2.750 0.0299 0.01344 0.00654 -0.0618 0.6300 0.7106
-2.500 0.0547 0.01359 0.00658 -0.0612 0.6281 0.7304
-2.250 0.0809 0.01380 0.00671 -0.0607 0.6265 0.7443
-2.000 0.1074 0.01401 0.00684 -0.0602 0.6249 0.7555
-1.750 0.1333 0.01420 0.00693 -0.0598 0.6235 0.7674
-1.500 0.1592 0.01452 0.00723 -0.0590 0.6219 0.7782
-1.250 0.1839 0.01484 0.00755 -0.0580 0.6198 0.7888
-1.000 0.2070 0.01502 0.00768 -0.0571 0.6177 0.7999
-0.750 0.2337 0.01524 0.00789 -0.0565 0.6158 0.8044
-0.500 0.2597 0.01536 0.00798 -0.0562 0.6141 0.8090
-0.250 0.2849 0.01541 0.00797 -0.0559 0.6125 0.8143
0.000 0.3108 0.01545 0.00795 -0.0558 0.6109 0.8183
0.250 0.3379 0.01554 0.00801 -0.0557 0.6096 0.8208
0.500 0.3650 0.01561 0.00804 -0.0557 0.6082 0.8236
0.750 0.3924 0.01568 0.00805 -0.0558 0.6068 0.8266
1.000 0.4168 0.01574 0.00810 -0.0555 0.6050 0.8302
1.250 0.4407 0.01578 0.00814 -0.0552 0.6031 0.8339
1.500 0.4655 0.01588 0.00826 -0.0548 0.6013 0.8358
1.750 0.4906 0.01597 0.00837 -0.0545 0.5995 0.8378
2.000 0.5160 0.01605 0.00846 -0.0543 0.5975 0.8400
2.250 0.5420 0.01612 0.00853 -0.0543 0.5957 0.8422
2.500 0.5684 0.01619 0.00859 -0.0544 0.5941 0.8446
2.750 0.5957 0.01625 0.00863 -0.0546 0.5925 0.8470
3.000 0.6240 0.01631 0.00866 -0.0551 0.5910 0.8491
3.250 0.6512 0.01641 0.00876 -0.0554 0.5894 0.8511
3.500 0.6720 0.01655 0.00900 -0.0544 0.5869 0.8529
3.750 0.6945 0.01669 0.00921 -0.0537 0.5843 0.8548
4.000 0.7183 0.01680 0.00937 -0.0533 0.5818 0.8565
4.250 0.7436 0.01689 0.00949 -0.0531 0.5794 0.8584
4.500 0.7704 0.01695 0.00957 -0.0533 0.5772 0.8604
4.750 0.7987 0.01700 0.00963 -0.0537 0.5752 0.8626
5.000 0.8277 0.01708 0.00970 -0.0543 0.5732 0.8646
5.250 0.8451 0.01728 0.01002 -0.0529 0.5694 0.8671
5.500 0.8655 0.01740 0.01025 -0.0518 0.5659 0.8688
5.750 0.8896 0.01746 0.01035 -0.0514 0.5626 0.8705
6.000 0.9172 0.01744 0.01036 -0.0516 0.5597 0.8722
6.250 0.9468 0.01742 0.01035 -0.0521 0.5569 0.8741
6.500 0.9584 0.01765 0.01074 -0.0495 0.5519 0.8776
6.750 0.9790 0.01770 0.01087 -0.0485 0.5473 0.8804
7.000 1.0066 0.01761 0.01080 -0.0487 0.5433 0.8825
7.250 1.0256 0.01765 0.01093 -0.0474 0.5384 0.8848
7.500 1.0378 0.01776 0.01116 -0.0448 0.5323 0.8878
7.750 1.0608 0.01764 0.01108 -0.0440 0.5270 0.8904
8.000 1.0709 0.01777 0.01133 -0.0411 0.5204 0.8944
8.250 1.0817 0.01782 0.01147 -0.0383 0.5136 0.8989
8.500 1.0935 0.01787 0.01160 -0.0356 0.5068 0.9032
8.750 1.0990 0.01813 0.01198 -0.0321 0.4982 0.9089
9.000 1.1075 0.01843 0.01237 -0.0293 0.4892 0.9148
9.250 1.1188 0.01859 0.01260 -0.0269 0.4793 0.9206
9.500 1.1215 0.01918 0.01329 -0.0236 0.4665 0.9297
9.750 1.1303 0.01971 0.01389 -0.0215 0.4510 0.9398
10.000 1.1437 0.02031 0.01451 -0.0205 0.4310 0.9528
10.250 1.1595 0.02112 0.01523 -0.0205 0.4047 0.9750
10.500 1.1607 0.02236 0.01636 -0.0183 0.3809 1.0000
11.000 1.1540 0.02579 0.01954 -0.0136 0.3347 1.0000
11.250 1.1490 0.02780 0.02145 -0.0114 0.3131 1.0000
11.500 1.1446 0.02987 0.02342 -0.0095 0.2931 1.0000
11.750 1.1406 0.03201 0.02548 -0.0077 0.2732 1.0000
12.000 1.1378 0.03414 0.02754 -0.0062 0.2552 1.0000
12.250 1.1350 0.03636 0.02969 -0.0048 0.2376 1.0000
12.500 1.1330 0.03860 0.03186 -0.0035 0.2208 1.0000
12.750 1.1325 0.04079 0.03400 -0.0025 0.2054 1.0000
13.000 1.1325 0.04300 0.03617 -0.0016 0.1904 1.0000
13.250 1.1334 0.04520 0.03833 -0.0008 0.1766 1.0000
13.500 1.1355 0.04736 0.04046 -0.0002 0.1637 1.0000
13.750 1.1377 0.04956 0.04264 0.0004 0.1518 1.0000
14.000 1.1402 0.05177 0.04482 0.0009 0.1410 1.0000
14.250 1.1417 0.05413 0.04715 0.0013 0.1309 1.0000
14.500 1.1464 0.05622 0.04927 0.0016 0.1213 1.0000
14.750 1.1500 0.05848 0.05154 0.0018 0.1131 1.0000
15.250 1.1565 0.06315 0.05623 0.0021 0.0970 1.0000
15.500 1.1591 0.06563 0.05871 0.0021 0.0897 1.0000
15.750 1.1618 0.06815 0.06124 0.0020 0.0827 1.0000
16.000 1.1652 0.07063 0.06375 0.0019 0.0761 1.0000
16.250 1.1665 0.07338 0.06651 0.0017 0.0706 1.0000
16.500 1.1708 0.07584 0.06903 0.0014 0.0654 1.0000
16.750 1.1718 0.07874 0.07193 0.0011 0.0608 1.0000
17.000 1.1759 0.08131 0.07459 0.0007 0.0569 1.0000
17.250 1.1775 0.08422 0.07754 0.0002 0.0531 1.0000
17.500 1.1794 0.08714 0.08052 -0.0004 0.0499 1.0000
17.750 1.1817 0.09002 0.08348 -0.0010 0.0467 1.0000
18.000 1.1808 0.09342 0.08692 -0.0019 0.0439 1.0000
18.250 1.1835 0.09635 0.08996 -0.0027 0.0414 1.0000
18.500 1.1835 0.09970 0.09338 -0.0036 0.0387 1.0000
18.750 1.1823 0.10324 0.09699 -0.0047 0.0367 1.0000
19.000 1.1831 0.10653 0.10039 -0.0058 0.0344 1.0000
19.250 1.1813 0.11026 0.10420 -0.0072 0.0326 1.0000
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Polar data table (+)
Polar graphs
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