RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Reynolds number: 500,000 Max Cl/Cd: 101.58 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1082t-il-500000-n5.txt Download as CSV file: xf-r1082t-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6094 0.06931 0.06660 -0.0711 1.0000 0.0086
-13.250 -0.6530 0.05716 0.05417 -0.0799 1.0000 0.0086
-13.000 -0.6544 0.05306 0.04999 -0.0828 0.9872 0.0087
-12.750 -0.6634 0.04253 0.03887 -0.0966 0.9349 0.0086
-12.500 -0.6265 0.03708 0.03292 -0.1094 0.8950 0.0087
-12.250 -0.6172 0.03502 0.03047 -0.1108 0.8444 0.0089
-12.000 -0.6203 0.03335 0.02852 -0.1087 0.8136 0.0090
-11.750 -0.6214 0.03190 0.02682 -0.1064 0.7907 0.0091
-11.500 -0.6232 0.03028 0.02495 -0.1039 0.7735 0.0092
-11.250 -0.6221 0.02880 0.02323 -0.1013 0.7588 0.0092
-11.000 -0.6189 0.02743 0.02163 -0.0987 0.7466 0.0093
-10.750 -0.6130 0.02620 0.02018 -0.0963 0.7360 0.0094
-10.500 -0.6052 0.02503 0.01883 -0.0940 0.7264 0.0095
-10.250 -0.5956 0.02400 0.01761 -0.0917 0.7179 0.0096
-10.000 -0.5843 0.02304 0.01648 -0.0896 0.7098 0.0097
-9.750 -0.5719 0.02222 0.01550 -0.0875 0.7028 0.0098
-9.500 -0.5576 0.02144 0.01458 -0.0856 0.6959 0.0100
-9.250 -0.5417 0.02065 0.01364 -0.0840 0.6895 0.0101
-9.000 -0.5239 0.01999 0.01285 -0.0827 0.6839 0.0103
-8.750 -0.5053 0.01938 0.01213 -0.0814 0.6780 0.0104
-8.250 -0.4686 0.01801 0.01057 -0.0789 0.6676 0.0106
-8.000 -0.4509 0.01728 0.00978 -0.0775 0.6626 0.0109
-7.750 -0.4315 0.01678 0.00921 -0.0764 0.6581 0.0111
-7.500 -0.4113 0.01630 0.00868 -0.0753 0.6542 0.0114
-7.250 -0.3904 0.01586 0.00819 -0.0744 0.6503 0.0117
-7.000 -0.3694 0.01542 0.00769 -0.0734 0.6464 0.0119
-6.750 -0.3480 0.01503 0.00724 -0.0724 0.6429 0.0123
-6.500 -0.3262 0.01467 0.00681 -0.0715 0.6397 0.0127
-6.250 -0.3034 0.01434 0.00643 -0.0708 0.6367 0.0131
-6.000 -0.2809 0.01397 0.00602 -0.0701 0.6335 0.0136
-5.750 -0.2587 0.01359 0.00561 -0.0693 0.6305 0.0144
-5.500 -0.2355 0.01331 0.00528 -0.0686 0.6275 0.0149
-5.250 -0.2119 0.01306 0.00497 -0.0679 0.6248 0.0156
-5.000 -0.1877 0.01281 0.00468 -0.0674 0.6222 0.0164
-4.750 -0.1637 0.01253 0.00439 -0.0669 0.6195 0.0180
-4.500 -0.1392 0.01231 0.00414 -0.0664 0.6170 0.0201
-4.250 -0.1150 0.01205 0.00390 -0.0659 0.6146 0.0257
-4.000 -0.0920 0.01171 0.00366 -0.0652 0.6124 0.0483
-3.750 -0.0684 0.01143 0.00347 -0.0646 0.6103 0.0740
-3.250 -0.0204 0.01089 0.00315 -0.0637 0.6066 0.1372
-3.000 0.0032 0.01055 0.00300 -0.0632 0.6047 0.1860
-2.750 0.0248 0.01006 0.00282 -0.0625 0.6028 0.2692
-2.500 0.0442 0.00940 0.00262 -0.0614 0.6008 0.3914
-2.250 0.0617 0.00862 0.00240 -0.0599 0.5987 0.5405
-2.000 0.0819 0.00819 0.00243 -0.0585 0.5968 0.6623
-1.750 0.1082 0.00822 0.00253 -0.0581 0.5950 0.7070
-1.500 0.1360 0.00828 0.00255 -0.0582 0.5934 0.7253
-1.250 0.1640 0.00835 0.00259 -0.0582 0.5919 0.7379
-1.000 0.1920 0.00841 0.00264 -0.0583 0.5904 0.7481
-0.750 0.2200 0.00848 0.00269 -0.0583 0.5888 0.7593
-0.500 0.2477 0.00858 0.00278 -0.0583 0.5872 0.7709
-0.250 0.2753 0.00867 0.00288 -0.0582 0.5856 0.7790
0.000 0.3033 0.00874 0.00293 -0.0582 0.5838 0.7854
0.250 0.3316 0.00880 0.00294 -0.0585 0.5820 0.7898
0.500 0.3596 0.00884 0.00298 -0.0586 0.5805 0.7926
0.750 0.3879 0.00890 0.00302 -0.0588 0.5791 0.7953
1.000 0.4162 0.00897 0.00306 -0.0590 0.5777 0.7980
1.250 0.4447 0.00904 0.00310 -0.0593 0.5762 0.8007
1.500 0.4730 0.00907 0.00314 -0.0595 0.5746 0.8031
1.750 0.5014 0.00911 0.00318 -0.0598 0.5729 0.8052
2.000 0.5296 0.00915 0.00322 -0.0601 0.5712 0.8068
2.250 0.5576 0.00918 0.00328 -0.0603 0.5692 0.8082
2.500 0.5856 0.00922 0.00333 -0.0605 0.5672 0.8097
2.750 0.6135 0.00927 0.00338 -0.0607 0.5650 0.8112
3.000 0.6416 0.00933 0.00343 -0.0609 0.5627 0.8126
3.250 0.6695 0.00940 0.00350 -0.0611 0.5603 0.8141
3.500 0.6970 0.00943 0.00358 -0.0612 0.5576 0.8159
3.750 0.7244 0.00946 0.00365 -0.0613 0.5544 0.8177
4.000 0.7518 0.00950 0.00371 -0.0614 0.5512 0.8193
4.250 0.7792 0.00956 0.00376 -0.0616 0.5477 0.8208
4.500 0.8064 0.00962 0.00383 -0.0616 0.5441 0.8222
4.750 0.8328 0.00963 0.00393 -0.0616 0.5396 0.8235
5.000 0.8590 0.00966 0.00400 -0.0614 0.5345 0.8250
5.250 0.8849 0.00973 0.00407 -0.0612 0.5294 0.8267
5.500 0.9108 0.00975 0.00418 -0.0610 0.5229 0.8286
5.750 0.9359 0.00981 0.00425 -0.0606 0.5158 0.8303
6.000 0.9615 0.00986 0.00436 -0.0604 0.5079 0.8321
6.250 0.9858 0.00994 0.00446 -0.0599 0.4987 0.8340
6.500 1.0097 0.01003 0.00457 -0.0594 0.4864 0.8359
6.750 1.0320 0.01016 0.00469 -0.0586 0.4692 0.8378
7.000 1.0497 0.01039 0.00486 -0.0568 0.4414 0.8398
7.250 1.0593 0.01090 0.00519 -0.0536 0.4007 0.8424
7.500 1.0647 0.01156 0.00567 -0.0498 0.3614 0.8458
7.750 1.0682 0.01216 0.00615 -0.0456 0.3295 0.8494
8.000 1.0714 0.01287 0.00672 -0.0415 0.2990 0.8530
8.250 1.0748 0.01358 0.00735 -0.0376 0.2725 0.8564
8.500 1.0779 0.01432 0.00803 -0.0339 0.2479 0.8604
8.750 1.0794 0.01519 0.00881 -0.0301 0.2232 0.8653
9.000 1.0828 0.01606 0.00963 -0.0269 0.2039 0.8701
9.250 1.0843 0.01704 0.01058 -0.0235 0.1855 0.8758
9.500 1.0875 0.01806 0.01158 -0.0207 0.1693 0.8829
9.750 1.0885 0.01926 0.01275 -0.0178 0.1512 0.8910
10.250 1.0930 0.02179 0.01528 -0.0129 0.1211 0.9146
10.500 1.0998 0.02318 0.01668 -0.0117 0.1068 0.9364
10.750 1.1172 0.02490 0.01836 -0.0134 0.0897 0.9880
11.000 1.1216 0.02636 0.01978 -0.0117 0.0793 1.0000
11.250 1.1286 0.02780 0.02122 -0.0107 0.0706 1.0000
11.500 1.1359 0.02926 0.02266 -0.0096 0.0635 1.0000
11.750 1.1425 0.03078 0.02416 -0.0086 0.0572 1.0000
12.000 1.1512 0.03217 0.02557 -0.0078 0.0523 1.0000
12.250 1.1583 0.03370 0.02710 -0.0069 0.0476 1.0000
12.500 1.1664 0.03518 0.02861 -0.0062 0.0435 1.0000
13.000 1.1813 0.03834 0.03180 -0.0048 0.0359 1.0000
13.250 1.1878 0.04006 0.03352 -0.0041 0.0324 1.0000
13.500 1.1960 0.04165 0.03515 -0.0036 0.0294 1.0000
13.750 1.2025 0.04344 0.03696 -0.0031 0.0266 1.0000
14.000 1.2102 0.04514 0.03870 -0.0027 0.0240 1.0000
14.250 1.2157 0.04709 0.04067 -0.0023 0.0212 1.0000
14.500 1.2230 0.04890 0.04252 -0.0019 0.0190 1.0000
14.750 1.2282 0.05094 0.04460 -0.0016 0.0170 1.0000
15.000 1.2345 0.05292 0.04662 -0.0014 0.0153 1.0000
15.250 1.2386 0.05516 0.04890 -0.0012 0.0137 1.0000
15.500 1.2444 0.05728 0.05107 -0.0011 0.0126 1.0000
15.750 1.2486 0.05959 0.05344 -0.0011 0.0117 1.0000
16.000 1.2523 0.06200 0.05591 -0.0011 0.0111 1.0000
16.250 1.2564 0.06444 0.05842 -0.0012 0.0105 1.0000
16.500 1.2608 0.06687 0.06093 -0.0014 0.0100 1.0000
16.750 1.2637 0.06953 0.06367 -0.0017 0.0096 1.0000
17.000 1.2659 0.07229 0.06650 -0.0020 0.0091 1.0000
17.250 1.2663 0.07537 0.06966 -0.0025 0.0088 1.0000
17.500 1.2673 0.07843 0.07279 -0.0031 0.0086 1.0000
17.750 1.2674 0.08169 0.07615 -0.0038 0.0083 1.0000
18.000 1.2674 0.08501 0.07957 -0.0046 0.0081 1.0000
18.250 1.2675 0.08836 0.08303 -0.0055 0.0080 1.0000
18.500 1.2664 0.09196 0.08673 -0.0066 0.0078 1.0000
18.750 1.2648 0.09571 0.09058 -0.0078 0.0077 1.0000
19.000 1.2617 0.09975 0.09473 -0.0092 0.0075 1.0000
19.250 1.2584 0.10388 0.09896 -0.0108 0.0074 1.0000
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Polar data table (+)
Polar graphs
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