RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.29 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1080-il-1000000.txt Download as CSV file: xf-r1080-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4965 0.08238 0.07925 -0.1004 0.7546 0.0100
-15.500 -0.5797 0.06292 0.05941 -0.1128 0.7552 0.0095
-15.250 -0.6249 0.05322 0.04938 -0.1181 0.7483 0.0093
-15.000 -0.6132 0.05205 0.04818 -0.1187 0.7371 0.0096
-14.750 -0.6518 0.04520 0.04102 -0.1204 0.7307 0.0094
-14.500 -0.6636 0.04196 0.03758 -0.1204 0.7229 0.0094
-14.250 -0.6847 0.03800 0.03335 -0.1194 0.7171 0.0092
-14.000 -0.6799 0.03671 0.03201 -0.1187 0.7103 0.0094
-13.750 -0.6793 0.03511 0.03029 -0.1176 0.7041 0.0096
-13.500 -0.6836 0.03298 0.02800 -0.1160 0.6993 0.0096
-13.250 -0.6788 0.03181 0.02675 -0.1147 0.6945 0.0099
-13.000 -0.6830 0.02961 0.02434 -0.1125 0.6898 0.0097
-12.750 -0.6775 0.02849 0.02309 -0.1108 0.6852 0.0099
-12.500 -0.6727 0.02706 0.02154 -0.1090 0.6821 0.0099
-12.250 -0.6639 0.02612 0.02051 -0.1074 0.6788 0.0101
-12.000 -0.6554 0.02507 0.01934 -0.1056 0.6753 0.0102
-11.750 -0.6462 0.02397 0.01811 -0.1039 0.6722 0.0102
-11.500 -0.6346 0.02321 0.01724 -0.1022 0.6686 0.0104
-11.250 -0.6222 0.02232 0.01625 -0.1006 0.6665 0.0105
-11.000 -0.6091 0.02139 0.01525 -0.0990 0.6644 0.0105
-10.750 -0.5942 0.02079 0.01457 -0.0976 0.6620 0.0107
-10.500 -0.5784 0.02032 0.01403 -0.0962 0.6597 0.0108
-10.250 -0.5634 0.01957 0.01318 -0.0947 0.6574 0.0109
-10.000 -0.5507 0.01850 0.01203 -0.0928 0.6551 0.0110
-9.750 -0.5362 0.01781 0.01127 -0.0912 0.6527 0.0111
-9.500 -0.5229 0.01706 0.01047 -0.0893 0.6507 0.0113
-9.250 -0.5077 0.01646 0.00983 -0.0875 0.6493 0.0115
-9.000 -0.4919 0.01593 0.00928 -0.0859 0.6478 0.0118
-8.750 -0.4754 0.01547 0.00880 -0.0842 0.6461 0.0119
-8.500 -0.4591 0.01505 0.00833 -0.0824 0.6444 0.0121
-8.250 -0.4432 0.01468 0.00793 -0.0805 0.6427 0.0124
-8.000 -0.4265 0.01435 0.00756 -0.0787 0.6411 0.0128
-7.750 -0.4072 0.01409 0.00725 -0.0774 0.6396 0.0131
-7.500 -0.3865 0.01382 0.00694 -0.0763 0.6380 0.0134
-7.250 -0.3697 0.01331 0.00638 -0.0745 0.6362 0.0141
-7.000 -0.3491 0.01302 0.00605 -0.0735 0.6343 0.0146
-6.750 -0.3272 0.01273 0.00576 -0.0726 0.6334 0.0152
-6.500 -0.3047 0.01247 0.00548 -0.0717 0.6326 0.0159
-6.250 -0.2818 0.01222 0.00521 -0.0710 0.6316 0.0166
-6.000 -0.2601 0.01188 0.00487 -0.0700 0.6305 0.0177
-5.750 -0.2367 0.01166 0.00463 -0.0694 0.6294 0.0193
-5.500 -0.2138 0.01139 0.00438 -0.0686 0.6282 0.0219
-5.250 -0.1909 0.01112 0.00413 -0.0679 0.6271 0.0282
-5.000 -0.1693 0.01077 0.00389 -0.0669 0.6260 0.0464
-4.750 -0.1467 0.01048 0.00370 -0.0662 0.6249 0.0677
-4.500 -0.1234 0.01023 0.00354 -0.0656 0.6237 0.0883
-4.250 -0.0999 0.00999 0.00339 -0.0650 0.6225 0.1119
-4.000 -0.0762 0.00977 0.00326 -0.0644 0.6213 0.1393
-3.750 -0.0531 0.00950 0.00313 -0.0638 0.6201 0.1773
-3.500 -0.0307 0.00920 0.00301 -0.0631 0.6188 0.2303
-3.250 -0.0099 0.00881 0.00290 -0.0622 0.6173 0.3070
-3.000 0.0079 0.00816 0.00270 -0.0607 0.6168 0.4228
-2.750 0.0241 0.00740 0.00247 -0.0590 0.6162 0.5649
-2.500 0.0443 0.00699 0.00248 -0.0576 0.6155 0.6823
-2.250 0.0724 0.00703 0.00254 -0.0577 0.6147 0.7114
-2.000 0.1010 0.00709 0.00260 -0.0578 0.6138 0.7257
-1.750 0.1298 0.00714 0.00265 -0.0581 0.6129 0.7339
-1.500 0.1587 0.00721 0.00269 -0.0584 0.6119 0.7413
-1.250 0.1876 0.00726 0.00272 -0.0587 0.6109 0.7475
-1.000 0.2166 0.00733 0.00279 -0.0589 0.6099 0.7531
-0.750 0.2457 0.00741 0.00284 -0.0593 0.6090 0.7585
-0.500 0.2746 0.00748 0.00289 -0.0596 0.6081 0.7637
-0.250 0.3034 0.00757 0.00300 -0.0598 0.6072 0.7696
0.000 0.3324 0.00769 0.00310 -0.0601 0.6062 0.7756
0.250 0.3613 0.00779 0.00317 -0.0604 0.6052 0.7803
0.500 0.3899 0.00785 0.00326 -0.0606 0.6041 0.7848
0.750 0.4191 0.00797 0.00337 -0.0610 0.6029 0.7881
1.000 0.4485 0.00812 0.00350 -0.0615 0.6012 0.7905
1.250 0.4773 0.00816 0.00354 -0.0619 0.6002 0.7924
1.500 0.5060 0.00817 0.00355 -0.0622 0.5992 0.7941
1.750 0.5346 0.00818 0.00356 -0.0626 0.5979 0.7956
2.000 0.5633 0.00820 0.00359 -0.0630 0.5965 0.7967
2.250 0.5918 0.00815 0.00355 -0.0633 0.5950 0.7985
2.500 0.6204 0.00814 0.00355 -0.0637 0.5933 0.8000
2.750 0.6491 0.00813 0.00354 -0.0640 0.5914 0.8013
3.000 0.6778 0.00812 0.00353 -0.0644 0.5894 0.8026
3.250 0.7065 0.00815 0.00355 -0.0648 0.5873 0.8037
3.500 0.7357 0.00829 0.00367 -0.0653 0.5844 0.8051
3.750 0.7630 0.00823 0.00366 -0.0654 0.5827 0.8064
4.000 0.7905 0.00819 0.00365 -0.0655 0.5802 0.8076
4.250 0.8183 0.00816 0.00364 -0.0657 0.5775 0.8088
4.500 0.8462 0.00814 0.00362 -0.0660 0.5746 0.8100
4.750 0.8741 0.00814 0.00362 -0.0662 0.5718 0.8111
5.000 0.9026 0.00823 0.00369 -0.0666 0.5684 0.8123
5.250 0.9292 0.00820 0.00371 -0.0666 0.5660 0.8134
5.500 0.9561 0.00817 0.00373 -0.0666 0.5626 0.8146
5.750 0.9828 0.00811 0.00371 -0.0666 0.5587 0.8161
6.000 1.0093 0.00812 0.00372 -0.0666 0.5547 0.8175
6.250 1.0355 0.00812 0.00377 -0.0665 0.5503 0.8188
6.500 1.0616 0.00811 0.00381 -0.0664 0.5448 0.8201
6.750 1.0862 0.00813 0.00383 -0.0660 0.5380 0.8215
7.000 1.1120 0.00815 0.00391 -0.0659 0.5300 0.8230
7.250 1.1355 0.00821 0.00397 -0.0653 0.5196 0.8245
7.500 1.1575 0.00831 0.00406 -0.0644 0.5049 0.8263
7.750 1.1736 0.00855 0.00422 -0.0624 0.4789 0.8283
8.000 1.1808 0.00903 0.00454 -0.0588 0.4462 0.8302
8.250 1.1794 0.00955 0.00493 -0.0535 0.4160 0.8327
8.500 1.1789 0.01015 0.00544 -0.0485 0.3882 0.8357
8.750 1.1788 0.01080 0.00600 -0.0438 0.3644 0.8385
9.000 1.1770 0.01155 0.00667 -0.0391 0.3410 0.8417
9.250 1.1721 0.01248 0.00752 -0.0342 0.3182 0.8452
9.500 1.1686 0.01352 0.00848 -0.0300 0.2973 0.8484
9.750 1.1654 0.01464 0.00957 -0.0261 0.2790 0.8531
10.000 1.1622 0.01593 0.01083 -0.0225 0.2615 0.8578
10.250 1.1599 0.01734 0.01219 -0.0193 0.2447 0.8626
10.500 1.1596 0.01873 0.01355 -0.0166 0.2298 0.8677
10.750 1.1569 0.02027 0.01507 -0.0137 0.2132 0.8740
11.000 1.1587 0.02166 0.01644 -0.0115 0.2000 0.8806
11.250 1.1600 0.02304 0.01782 -0.0092 0.1873 0.8895
11.500 1.1611 0.02445 0.01925 -0.0069 0.1749 0.9016
11.750 1.1633 0.02580 0.02066 -0.0049 0.1636 0.9260
12.000 1.1878 0.02746 0.02235 -0.0079 0.1480 0.9608
12.250 1.2010 0.02920 0.02404 -0.0088 0.1338 1.0000
12.500 1.2073 0.03067 0.02546 -0.0077 0.1250 1.0000
12.750 1.2132 0.03220 0.02695 -0.0067 0.1149 1.0000
13.000 1.2201 0.03366 0.02838 -0.0057 0.1056 1.0000
13.250 1.2261 0.03525 0.02993 -0.0047 0.0982 1.0000
13.500 1.2336 0.03672 0.03137 -0.0039 0.0905 1.0000
13.750 1.2411 0.03823 0.03287 -0.0031 0.0837 1.0000
14.000 1.2471 0.03988 0.03448 -0.0023 0.0772 1.0000
14.250 1.2571 0.04123 0.03586 -0.0018 0.0728 1.0000
14.500 1.2633 0.04292 0.03752 -0.0011 0.0678 1.0000
14.750 1.2724 0.04439 0.03901 -0.0006 0.0641 1.0000
15.000 1.2808 0.04592 0.04055 -0.0001 0.0607 1.0000
15.250 1.2870 0.04769 0.04232 0.0005 0.0569 1.0000
15.500 1.2961 0.04923 0.04388 0.0008 0.0538 1.0000
15.750 1.3035 0.05093 0.04558 0.0012 0.0509 1.0000
16.000 1.3107 0.05267 0.04736 0.0016 0.0485 1.0000
16.250 1.3191 0.05434 0.04906 0.0018 0.0465 1.0000
16.500 1.3260 0.05615 0.05088 0.0021 0.0441 1.0000
16.750 1.3312 0.05817 0.05293 0.0023 0.0418 1.0000
17.000 1.3396 0.05991 0.05472 0.0024 0.0402 1.0000
17.250 1.3457 0.06186 0.05669 0.0026 0.0379 1.0000
17.500 1.3487 0.06421 0.05905 0.0027 0.0360 1.0000
17.750 1.3567 0.06604 0.06095 0.0026 0.0347 1.0000
18.000 1.3622 0.06817 0.06311 0.0026 0.0327 1.0000
18.250 1.3641 0.07074 0.06570 0.0025 0.0308 1.0000
18.500 1.3706 0.07281 0.06782 0.0023 0.0293 1.0000
18.750 1.3736 0.07532 0.07037 0.0021 0.0276 1.0000
19.000 1.3747 0.07807 0.07316 0.0018 0.0258 1.0000
19.250 1.3782 0.08062 0.07576 0.0014 0.0241 1.0000
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