RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.39 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1082t-il-1000000-n5.txt Download as CSV file: xf-r1082t-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7438 0.07664 0.07433 -0.0653 1.0000 0.0063
-15.250 -0.7971 0.06143 0.05882 -0.0755 1.0000 0.0063
-15.000 -0.8341 0.05187 0.04900 -0.0816 1.0000 0.0062
-14.750 -0.8451 0.04750 0.04450 -0.0835 1.0000 0.0062
-14.500 -0.8467 0.04311 0.03996 -0.0871 0.9982 0.0062
-14.250 -0.8545 0.03901 0.03567 -0.0886 0.9577 0.0062
-14.000 -0.7974 0.03466 0.03103 -0.1031 0.9331 0.0064
-13.750 -0.7501 0.03144 0.02731 -0.1140 0.8619 0.0064
-13.250 -0.7496 0.02879 0.02417 -0.1100 0.7900 0.0066
-13.000 -0.7437 0.02777 0.02300 -0.1083 0.7716 0.0066
-12.750 -0.7452 0.02617 0.02119 -0.1058 0.7543 0.0066
-12.500 -0.7394 0.02508 0.01996 -0.1039 0.7409 0.0066
-12.250 -0.7305 0.02424 0.01899 -0.1021 0.7294 0.0067
-12.000 -0.7214 0.02339 0.01802 -0.1002 0.7190 0.0068
-11.750 -0.7110 0.02260 0.01712 -0.0984 0.7094 0.0069
-11.500 -0.7003 0.02183 0.01623 -0.0965 0.7011 0.0070
-11.250 -0.6902 0.02098 0.01527 -0.0945 0.6930 0.0070
-11.000 -0.6784 0.02026 0.01444 -0.0925 0.6860 0.0072
-10.750 -0.6662 0.01955 0.01363 -0.0905 0.6792 0.0072
-10.500 -0.6535 0.01891 0.01287 -0.0885 0.6728 0.0074
-10.250 -0.6400 0.01832 0.01220 -0.0864 0.6672 0.0074
-10.000 -0.6267 0.01777 0.01156 -0.0843 0.6612 0.0075
-9.750 -0.6120 0.01732 0.01101 -0.0823 0.6556 0.0076
-9.500 -0.5939 0.01687 0.01049 -0.0809 0.6506 0.0077
-9.250 -0.5762 0.01633 0.00987 -0.0795 0.6455 0.0077
-8.750 -0.5357 0.01557 0.00898 -0.0774 0.6372 0.0079
-8.500 -0.5178 0.01495 0.00829 -0.0760 0.6333 0.0081
-8.250 -0.4983 0.01445 0.00773 -0.0748 0.6294 0.0082
-8.000 -0.4780 0.01401 0.00723 -0.0737 0.6258 0.0084
-7.750 -0.4562 0.01366 0.00683 -0.0728 0.6227 0.0086
-7.500 -0.4336 0.01333 0.00648 -0.0721 0.6197 0.0088
-7.250 -0.4106 0.01304 0.00615 -0.0714 0.6166 0.0090
-7.000 -0.3878 0.01272 0.00579 -0.0707 0.6136 0.0091
-6.750 -0.3644 0.01246 0.00549 -0.0701 0.6106 0.0094
-6.500 -0.3409 0.01219 0.00518 -0.0694 0.6078 0.0096
-6.250 -0.3168 0.01193 0.00488 -0.0689 0.6054 0.0099
-6.000 -0.2925 0.01168 0.00461 -0.0684 0.6028 0.0101
-5.750 -0.2678 0.01147 0.00436 -0.0680 0.6002 0.0104
-5.500 -0.2433 0.01124 0.00410 -0.0675 0.5977 0.0107
-5.250 -0.2190 0.01100 0.00384 -0.0670 0.5954 0.0113
-5.000 -0.1942 0.01081 0.00363 -0.0666 0.5932 0.0120
-4.750 -0.1687 0.01063 0.00343 -0.0663 0.5914 0.0128
-4.500 -0.1428 0.01046 0.00325 -0.0660 0.5897 0.0133
-4.250 -0.1172 0.01028 0.00306 -0.0657 0.5879 0.0144
-4.000 -0.0914 0.01012 0.00289 -0.0655 0.5860 0.0164
-3.750 -0.0659 0.00992 0.00273 -0.0652 0.5842 0.0226
-3.500 -0.0412 0.00968 0.00256 -0.0648 0.5823 0.0425
-3.250 -0.0162 0.00945 0.00242 -0.0644 0.5805 0.0652
-3.000 0.0087 0.00923 0.00230 -0.0641 0.5785 0.0939
-2.750 0.0335 0.00900 0.00218 -0.0637 0.5766 0.1289
-2.500 0.0588 0.00875 0.00207 -0.0635 0.5753 0.1681
-2.250 0.0838 0.00847 0.00197 -0.0632 0.5740 0.2183
-2.000 0.1078 0.00810 0.00185 -0.0628 0.5726 0.2933
-1.750 0.1292 0.00750 0.00170 -0.0621 0.5711 0.4217
-1.500 0.1506 0.00688 0.00154 -0.0613 0.5696 0.5568
-1.250 0.1744 0.00651 0.00149 -0.0607 0.5682 0.6506
-1.000 0.2014 0.00645 0.00153 -0.0606 0.5667 0.6943
-0.750 0.2294 0.00646 0.00156 -0.0607 0.5653 0.7133
-0.500 0.2577 0.00650 0.00158 -0.0609 0.5638 0.7265
-0.250 0.2859 0.00655 0.00162 -0.0610 0.5621 0.7378
0.000 0.3141 0.00660 0.00168 -0.0611 0.5606 0.7481
0.250 0.3429 0.00665 0.00171 -0.0614 0.5596 0.7566
0.500 0.3713 0.00667 0.00177 -0.0616 0.5584 0.7626
0.750 0.4000 0.00671 0.00181 -0.0619 0.5571 0.7671
1.000 0.4287 0.00675 0.00183 -0.0622 0.5557 0.7707
1.250 0.4575 0.00680 0.00186 -0.0625 0.5541 0.7734
1.500 0.4859 0.00682 0.00190 -0.0627 0.5525 0.7761
1.750 0.5142 0.00686 0.00194 -0.0629 0.5507 0.7786
2.000 0.5423 0.00691 0.00198 -0.0631 0.5485 0.7807
2.250 0.5703 0.00698 0.00202 -0.0633 0.5459 0.7823
2.500 0.5989 0.00700 0.00206 -0.0636 0.5439 0.7839
2.750 0.6275 0.00703 0.00210 -0.0639 0.5414 0.7853
3.000 0.6559 0.00706 0.00214 -0.0642 0.5385 0.7866
3.250 0.6840 0.00710 0.00218 -0.0644 0.5354 0.7878
3.500 0.7117 0.00716 0.00223 -0.0646 0.5320 0.7890
3.750 0.7396 0.00721 0.00229 -0.0648 0.5288 0.7903
4.000 0.7677 0.00723 0.00234 -0.0650 0.5249 0.7917
4.250 0.7953 0.00727 0.00240 -0.0651 0.5200 0.7929
4.500 0.8220 0.00734 0.00246 -0.0651 0.5147 0.7942
4.750 0.8499 0.00737 0.00254 -0.0653 0.5087 0.7954
5.000 0.8763 0.00745 0.00261 -0.0652 0.5010 0.7968
5.250 0.9032 0.00752 0.00269 -0.0652 0.4919 0.7982
5.500 0.9290 0.00762 0.00279 -0.0650 0.4803 0.7999
5.750 0.9534 0.00779 0.00290 -0.0646 0.4617 0.8015
6.000 0.9740 0.00810 0.00309 -0.0634 0.4302 0.8030
6.250 0.9910 0.00859 0.00340 -0.0617 0.3923 0.8046
6.500 1.0050 0.00920 0.00381 -0.0594 0.3503 0.8061
6.750 1.0186 0.00977 0.00421 -0.0571 0.3120 0.8080
7.000 1.0316 0.01031 0.00462 -0.0546 0.2788 0.8100
7.250 1.0433 0.01082 0.00501 -0.0519 0.2502 0.8120
7.500 1.0523 0.01128 0.00538 -0.0487 0.2268 0.8144
7.750 1.0611 0.01180 0.00581 -0.0455 0.2042 0.8171
8.000 1.0701 0.01234 0.00627 -0.0424 0.1850 0.8198
8.500 1.0880 0.01345 0.00727 -0.0366 0.1512 0.8248
8.750 1.0897 0.01428 0.00800 -0.0327 0.1289 0.8280
9.000 1.0950 0.01505 0.00872 -0.0296 0.1129 0.8314
9.250 1.1019 0.01583 0.00947 -0.0270 0.1010 0.8348
9.500 1.1084 0.01670 0.01032 -0.0245 0.0901 0.8382
9.750 1.1161 0.01756 0.01118 -0.0222 0.0811 0.8420
10.000 1.1224 0.01855 0.01217 -0.0200 0.0714 0.8466
10.250 1.1292 0.01960 0.01320 -0.0180 0.0633 0.8516
10.500 1.1356 0.02072 0.01432 -0.0161 0.0560 0.8567
10.750 1.1432 0.02180 0.01543 -0.0144 0.0497 0.8627
11.000 1.1515 0.02290 0.01655 -0.0128 0.0452 0.8689
11.250 1.1595 0.02402 0.01771 -0.0113 0.0411 0.8765
11.750 1.1750 0.02632 0.02011 -0.0084 0.0344 0.8986
12.000 1.1817 0.02750 0.02138 -0.0068 0.0312 0.9216
12.250 1.2043 0.02885 0.02284 -0.0088 0.0275 0.9607
12.750 1.2250 0.03173 0.02574 -0.0081 0.0216 1.0000
13.000 1.2341 0.03310 0.02713 -0.0074 0.0194 1.0000
13.250 1.2410 0.03467 0.02871 -0.0065 0.0168 1.0000
13.500 1.2483 0.03624 0.03029 -0.0058 0.0144 1.0000
13.750 1.2546 0.03793 0.03200 -0.0051 0.0119 1.0000
14.000 1.2619 0.03957 0.03367 -0.0045 0.0109 1.0000
14.250 1.2694 0.04122 0.03535 -0.0039 0.0096 1.0000
14.500 1.2762 0.04297 0.03713 -0.0034 0.0089 1.0000
14.750 1.2837 0.04468 0.03888 -0.0030 0.0082 1.0000
15.000 1.2908 0.04647 0.04072 -0.0026 0.0078 1.0000
15.250 1.2980 0.04828 0.04257 -0.0023 0.0073 1.0000
15.500 1.3036 0.05027 0.04461 -0.0020 0.0069 1.0000
15.750 1.3093 0.05228 0.04666 -0.0018 0.0066 1.0000
16.000 1.3149 0.05436 0.04880 -0.0016 0.0064 1.0000
16.250 1.3215 0.05635 0.05085 -0.0016 0.0063 1.0000
16.500 1.3277 0.05843 0.05299 -0.0015 0.0061 1.0000
16.750 1.3326 0.06066 0.05528 -0.0016 0.0060 1.0000
17.000 1.3372 0.06297 0.05765 -0.0017 0.0058 1.0000
17.250 1.3411 0.06542 0.06018 -0.0018 0.0057 1.0000
17.500 1.3453 0.06785 0.06267 -0.0021 0.0056 1.0000
17.750 1.3473 0.07061 0.06550 -0.0024 0.0054 1.0000
18.000 1.3495 0.07337 0.06833 -0.0028 0.0053 1.0000
18.250 1.3515 0.07621 0.07124 -0.0033 0.0053 1.0000
18.500 1.3516 0.07937 0.07447 -0.0040 0.0051 1.0000
18.750 1.3517 0.08258 0.07775 -0.0047 0.0050 1.0000
19.000 1.3476 0.08646 0.08172 -0.0057 0.0048 1.0000
19.250 1.3465 0.08995 0.08530 -0.0067 0.0048 1.0000
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Polar data table (+)
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