RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.76 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1082-il-1000000.txt Download as CSV file: xf-r1082-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.4827 0.07980 0.07775 -0.0802 0.9579 0.0109
-15.250 -0.6426 0.07654 0.07431 -0.0771 1.0000 0.0106
-15.000 -0.6837 0.06516 0.06270 -0.0845 1.0000 0.0103
-14.750 -0.7106 0.05776 0.05512 -0.0888 1.0000 0.0103
-14.500 -0.7274 0.05074 0.04787 -0.0944 0.9987 0.0103
-14.250 -0.7487 0.04545 0.04237 -0.0956 0.9671 0.0102
-14.000 -0.7190 0.03937 0.03593 -0.1080 0.9401 0.0103
-13.750 -0.6592 0.03393 0.03000 -0.1251 0.9076 0.0107
-13.500 -0.6439 0.03169 0.02727 -0.1278 0.8392 0.0107
-13.250 -0.6443 0.03032 0.02564 -0.1258 0.8067 0.0108
-13.000 -0.6444 0.02873 0.02383 -0.1236 0.7845 0.0107
-12.750 -0.6399 0.02761 0.02253 -0.1217 0.7670 0.0108
-12.500 -0.6339 0.02666 0.02141 -0.1198 0.7523 0.0110
-12.250 -0.6271 0.02569 0.02028 -0.1178 0.7395 0.0111
-12.000 -0.6194 0.02455 0.01899 -0.1159 0.7281 0.0111
-11.750 -0.6090 0.02372 0.01805 -0.1142 0.7183 0.0112
-11.500 -0.5981 0.02307 0.01726 -0.1124 0.7087 0.0113
-11.250 -0.5862 0.02211 0.01620 -0.1107 0.7008 0.0113
-11.000 -0.5741 0.02134 0.01530 -0.1089 0.6931 0.0114
-10.750 -0.5629 0.02000 0.01385 -0.1071 0.6867 0.0116
-10.500 -0.5491 0.01924 0.01301 -0.1055 0.6801 0.0116
-10.250 -0.5375 0.01838 0.01207 -0.1035 0.6738 0.0119
-10.000 -0.5224 0.01779 0.01143 -0.1019 0.6691 0.0119
-9.750 -0.5082 0.01717 0.01075 -0.1001 0.6636 0.0121
-9.500 -0.4936 0.01665 0.01017 -0.0983 0.6585 0.0124
-9.250 -0.4777 0.01617 0.00965 -0.0966 0.6542 0.0125
-9.000 -0.4624 0.01567 0.00910 -0.0948 0.6502 0.0127
-8.750 -0.4467 0.01524 0.00862 -0.0930 0.6462 0.0130
-8.500 -0.4316 0.01485 0.00816 -0.0910 0.6424 0.0133
-8.250 -0.4168 0.01451 0.00776 -0.0889 0.6388 0.0135
-8.000 -0.3991 0.01424 0.00747 -0.0872 0.6361 0.0139
-7.750 -0.3802 0.01396 0.00715 -0.0858 0.6331 0.0141
-7.500 -0.3647 0.01342 0.00655 -0.0838 0.6302 0.0145
-7.250 -0.3465 0.01303 0.00612 -0.0823 0.6273 0.0151
-7.000 -0.3262 0.01276 0.00581 -0.0811 0.6242 0.0155
-6.750 -0.3049 0.01249 0.00550 -0.0801 0.6219 0.0161
-6.500 -0.2827 0.01222 0.00522 -0.0792 0.6198 0.0168
-6.250 -0.2600 0.01199 0.00497 -0.0784 0.6177 0.0172
-6.000 -0.2389 0.01166 0.00462 -0.0774 0.6153 0.0185
-5.750 -0.2161 0.01144 0.00437 -0.0766 0.6130 0.0201
-5.500 -0.1937 0.01119 0.00412 -0.0757 0.6107 0.0231
-5.250 -0.1719 0.01093 0.00389 -0.0748 0.6083 0.0315
-5.000 -0.1510 0.01060 0.00367 -0.0737 0.6061 0.0559
-4.750 -0.1281 0.01033 0.00349 -0.0730 0.6048 0.0757
-4.500 -0.1048 0.01007 0.00334 -0.0724 0.6033 0.0961
-4.250 -0.0809 0.00985 0.00320 -0.0718 0.6017 0.1172
-4.000 -0.0573 0.00962 0.00306 -0.0713 0.6001 0.1440
-3.750 -0.0340 0.00935 0.00292 -0.0706 0.5985 0.1789
-3.500 -0.0123 0.00899 0.00277 -0.0698 0.5969 0.2332
-3.250 0.0084 0.00856 0.00261 -0.0688 0.5954 0.3087
-3.000 0.0274 0.00802 0.00243 -0.0676 0.5938 0.4113
-2.750 0.0466 0.00747 0.00226 -0.0663 0.5919 0.5228
-2.500 0.0660 0.00697 0.00218 -0.0650 0.5898 0.6444
-2.250 0.0919 0.00689 0.00226 -0.0646 0.5888 0.7022
-2.000 0.1201 0.00693 0.00232 -0.0647 0.5877 0.7217
-1.750 0.1488 0.00698 0.00234 -0.0650 0.5865 0.7332
-1.500 0.1773 0.00704 0.00240 -0.0651 0.5852 0.7415
-1.250 0.2062 0.00712 0.00243 -0.0654 0.5840 0.7488
-1.000 0.2348 0.00716 0.00249 -0.0656 0.5827 0.7542
-0.750 0.2635 0.00724 0.00255 -0.0659 0.5814 0.7597
-0.500 0.2923 0.00733 0.00259 -0.0662 0.5802 0.7650
-0.250 0.3207 0.00739 0.00266 -0.0663 0.5789 0.7704
0.000 0.3492 0.00751 0.00278 -0.0665 0.5775 0.7765
0.250 0.3779 0.00767 0.00289 -0.0667 0.5758 0.7820
0.500 0.4067 0.00777 0.00299 -0.0670 0.5741 0.7864
0.750 0.4355 0.00786 0.00309 -0.0673 0.5730 0.7897
1.000 0.4640 0.00791 0.00315 -0.0676 0.5722 0.7925
1.250 0.4925 0.00795 0.00320 -0.0679 0.5711 0.7951
1.500 0.5211 0.00799 0.00324 -0.0682 0.5698 0.7973
1.750 0.5498 0.00804 0.00328 -0.0685 0.5685 0.7991
2.000 0.5782 0.00806 0.00329 -0.0689 0.5670 0.8009
2.250 0.6064 0.00805 0.00329 -0.0691 0.5653 0.8029
2.500 0.6347 0.00808 0.00332 -0.0694 0.5636 0.8045
2.750 0.6629 0.00811 0.00336 -0.0697 0.5619 0.8059
3.000 0.6914 0.00818 0.00341 -0.0700 0.5599 0.8073
3.250 0.7208 0.00832 0.00353 -0.0706 0.5574 0.8086
3.500 0.7483 0.00831 0.00356 -0.0708 0.5559 0.8098
3.750 0.7758 0.00832 0.00359 -0.0709 0.5542 0.8112
4.000 0.8033 0.00833 0.00362 -0.0711 0.5520 0.8126
4.250 0.8309 0.00834 0.00365 -0.0712 0.5496 0.8138
4.500 0.8585 0.00835 0.00367 -0.0714 0.5472 0.8149
4.750 0.8859 0.00839 0.00370 -0.0716 0.5446 0.8159
5.000 0.9143 0.00852 0.00380 -0.0720 0.5411 0.8167
5.250 0.9402 0.00847 0.00381 -0.0718 0.5388 0.8182
5.500 0.9662 0.00844 0.00383 -0.0717 0.5356 0.8198
5.750 0.9922 0.00843 0.00385 -0.0715 0.5321 0.8211
6.000 1.0182 0.00845 0.00389 -0.0714 0.5286 0.8224
6.250 1.0440 0.00853 0.00397 -0.0713 0.5245 0.8236
6.500 1.0694 0.00852 0.00403 -0.0710 0.5206 0.8250
6.750 1.0946 0.00853 0.00408 -0.0707 0.5159 0.8264
7.000 1.1185 0.00860 0.00414 -0.0702 0.5107 0.8278
7.250 1.1436 0.00862 0.00423 -0.0699 0.5054 0.8293
7.500 1.1675 0.00867 0.00431 -0.0694 0.4987 0.8308
7.750 1.1902 0.00875 0.00440 -0.0687 0.4908 0.8324
8.000 1.2100 0.00887 0.00450 -0.0673 0.4792 0.8337
8.250 1.2267 0.00897 0.00460 -0.0654 0.4646 0.8359
8.500 1.2387 0.00920 0.00479 -0.0626 0.4429 0.8381
8.750 1.2433 0.00967 0.00515 -0.0584 0.4156 0.8406
9.000 1.2453 0.01027 0.00564 -0.0539 0.3890 0.8432
9.250 1.2445 0.01099 0.00624 -0.0491 0.3601 0.8462
9.500 1.2456 0.01170 0.00686 -0.0449 0.3375 0.8490
9.750 1.2433 0.01254 0.00762 -0.0403 0.3136 0.8523
10.000 1.2393 0.01350 0.00851 -0.0357 0.2915 0.8564
10.250 1.2362 0.01456 0.00952 -0.0316 0.2712 0.8608
10.500 1.2294 0.01592 0.01080 -0.0274 0.2501 0.8653
10.750 1.2246 0.01733 0.01217 -0.0237 0.2314 0.8702
11.000 1.2203 0.01884 0.01365 -0.0204 0.2139 0.8758
11.250 1.2168 0.02046 0.01522 -0.0174 0.1972 0.8820
11.500 1.2120 0.02218 0.01693 -0.0145 0.1809 0.8895
11.750 1.2110 0.02378 0.01853 -0.0121 0.1686 0.8988
12.000 1.2052 0.02564 0.02038 -0.0093 0.1522 0.9142
12.250 1.2119 0.02725 0.02209 -0.0087 0.1409 0.9464
12.500 1.2296 0.02956 0.02435 -0.0116 0.1225 1.0000
12.750 1.2312 0.03145 0.02619 -0.0103 0.1108 1.0000
13.000 1.2350 0.03320 0.02791 -0.0092 0.1019 1.0000
13.250 1.2381 0.03506 0.02972 -0.0082 0.0934 1.0000
13.500 1.2443 0.03670 0.03136 -0.0074 0.0866 1.0000
13.750 1.2485 0.03852 0.03316 -0.0065 0.0795 1.0000
14.000 1.2544 0.04024 0.03488 -0.0058 0.0738 1.0000
14.250 1.2600 0.04201 0.03664 -0.0052 0.0679 1.0000
14.500 1.2652 0.04383 0.03844 -0.0045 0.0627 1.0000
14.750 1.2713 0.04562 0.04023 -0.0040 0.0580 1.0000
15.000 1.2771 0.04744 0.04206 -0.0035 0.0537 1.0000
15.250 1.2832 0.04930 0.04393 -0.0031 0.0500 1.0000
15.500 1.2888 0.05119 0.04582 -0.0026 0.0460 1.0000
15.750 1.2946 0.05311 0.04775 -0.0023 0.0432 1.0000
16.000 1.3008 0.05501 0.04968 -0.0021 0.0402 1.0000
16.250 1.3057 0.05706 0.05172 -0.0018 0.0369 1.0000
16.500 1.3114 0.05909 0.05378 -0.0016 0.0344 1.0000
16.750 1.3152 0.06131 0.05602 -0.0015 0.0316 1.0000
17.000 1.3216 0.06329 0.05804 -0.0014 0.0295 1.0000
17.250 1.3236 0.06578 0.06053 -0.0014 0.0264 1.0000
17.500 1.3287 0.06797 0.06274 -0.0014 0.0238 1.0000
17.750 1.3307 0.07054 0.06535 -0.0015 0.0216 1.0000
18.000 1.3319 0.07325 0.06805 -0.0016 0.0187 1.0000
18.250 1.3346 0.07581 0.07067 -0.0019 0.0172 1.0000
18.500 1.3337 0.07884 0.07373 -0.0022 0.0149 1.0000
18.750 1.3351 0.08169 0.07663 -0.0026 0.0139 1.0000
19.000 1.3346 0.08479 0.07977 -0.0031 0.0129 1.0000
19.250 1.3346 0.08791 0.08295 -0.0037 0.0122 1.0000
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