RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 127.14 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1082-il-1000000-n5.txt Download as CSV file: xf-r1082-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7019 0.11051 0.10807 -0.0577 1.0000 0.0070
-17.750 -0.7481 0.09801 0.09539 -0.0641 1.0000 0.0070
-17.500 -0.7894 0.08665 0.08386 -0.0701 1.0000 0.0069
-17.250 -0.8181 0.07763 0.07467 -0.0750 1.0000 0.0068
-17.000 -0.8402 0.06923 0.06612 -0.0806 0.9998 0.0068
-16.750 -0.8577 0.06083 0.05753 -0.0874 0.9988 0.0069
-16.500 -0.8762 0.05530 0.05187 -0.0891 0.9924 0.0068
-16.250 -0.8697 0.04962 0.04602 -0.0962 0.9516 0.0069
-16.000 -0.8159 0.04295 0.03906 -0.1143 0.9225 0.0070
-15.750 -0.7757 0.03800 0.03360 -0.1273 0.8591 0.0070
-15.500 -0.7713 0.03628 0.03161 -0.1273 0.8144 0.0071
-15.250 -0.7691 0.03457 0.02973 -0.1267 0.7892 0.0072
-15.000 -0.7712 0.03261 0.02759 -0.1258 0.7704 0.0071
-14.750 -0.7667 0.03121 0.02605 -0.1248 0.7545 0.0072
-14.500 -0.7628 0.02982 0.02454 -0.1237 0.7410 0.0073
-14.250 -0.7593 0.02844 0.02303 -0.1223 0.7288 0.0073
-14.000 -0.7525 0.02730 0.02179 -0.1210 0.7188 0.0073
-13.500 -0.7357 0.02535 0.01963 -0.1183 0.6985 0.0075
-13.250 -0.7261 0.02448 0.01866 -0.1169 0.6902 0.0076
-13.000 -0.7181 0.02349 0.01758 -0.1152 0.6833 0.0076
-12.750 -0.7072 0.02271 0.01670 -0.1137 0.6762 0.0076
-12.500 -0.6950 0.02200 0.01592 -0.1123 0.6704 0.0078
-12.250 -0.6824 0.02132 0.01517 -0.1108 0.6644 0.0079
-12.000 -0.6713 0.02057 0.01433 -0.1091 0.6587 0.0080
-11.750 -0.6579 0.01995 0.01364 -0.1076 0.6540 0.0080
-11.500 -0.6439 0.01935 0.01297 -0.1061 0.6491 0.0081
-11.250 -0.6302 0.01876 0.01231 -0.1045 0.6442 0.0082
-10.750 -0.5990 0.01778 0.01120 -0.1016 0.6363 0.0085
-10.500 -0.5843 0.01724 0.01060 -0.1000 0.6323 0.0085
-10.250 -0.5682 0.01678 0.01008 -0.0985 0.6284 0.0086
-10.000 -0.5517 0.01638 0.00962 -0.0970 0.6248 0.0087
-9.750 -0.5350 0.01597 0.00916 -0.0955 0.6215 0.0088
-9.500 -0.5199 0.01546 0.00860 -0.0937 0.6185 0.0090
-9.250 -0.5040 0.01504 0.00814 -0.0920 0.6151 0.0092
-9.000 -0.4881 0.01464 0.00769 -0.0902 0.6119 0.0094
-8.750 -0.4715 0.01434 0.00736 -0.0884 0.6088 0.0097
-8.500 -0.4551 0.01407 0.00705 -0.0865 0.6061 0.0099
-8.250 -0.4375 0.01380 0.00675 -0.0849 0.6041 0.0101
-8.000 -0.4177 0.01353 0.00646 -0.0836 0.6018 0.0103
-7.750 -0.3973 0.01326 0.00615 -0.0825 0.5995 0.0105
-7.500 -0.3762 0.01301 0.00587 -0.0814 0.5972 0.0108
-7.250 -0.3547 0.01278 0.00560 -0.0805 0.5949 0.0111
-7.000 -0.3328 0.01256 0.00535 -0.0796 0.5927 0.0113
-6.500 -0.2892 0.01206 0.00481 -0.0777 0.5889 0.0123
-6.250 -0.2661 0.01185 0.00459 -0.0770 0.5874 0.0128
-6.000 -0.2427 0.01165 0.00438 -0.0763 0.5857 0.0135
-5.750 -0.2189 0.01147 0.00418 -0.0757 0.5839 0.0142
-5.500 -0.1956 0.01126 0.00397 -0.0751 0.5819 0.0158
-5.250 -0.1717 0.01109 0.00379 -0.0745 0.5799 0.0176
-5.000 -0.1484 0.01088 0.00360 -0.0738 0.5781 0.0226
-4.750 -0.1254 0.01066 0.00342 -0.0731 0.5764 0.0339
-4.500 -0.1020 0.01045 0.00326 -0.0724 0.5747 0.0456
-4.250 -0.0779 0.01028 0.00312 -0.0719 0.5732 0.0570
-4.000 -0.0534 0.01008 0.00299 -0.0715 0.5722 0.0700
-3.750 -0.0286 0.00990 0.00287 -0.0711 0.5711 0.0854
-3.500 -0.0044 0.00968 0.00274 -0.0706 0.5699 0.1083
-3.250 0.0199 0.00946 0.00263 -0.0702 0.5686 0.1348
-3.000 0.0436 0.00921 0.00251 -0.0696 0.5673 0.1717
-2.750 0.0674 0.00895 0.00239 -0.0691 0.5660 0.2139
-2.500 0.0902 0.00862 0.00227 -0.0685 0.5647 0.2719
-2.250 0.1122 0.00823 0.00214 -0.0677 0.5633 0.3484
-2.000 0.1344 0.00784 0.00201 -0.0670 0.5619 0.4279
-1.750 0.1572 0.00748 0.00190 -0.0664 0.5605 0.5040
-1.500 0.1801 0.00713 0.00179 -0.0657 0.5590 0.5826
-1.250 0.2037 0.00686 0.00178 -0.0650 0.5575 0.6622
-1.000 0.2311 0.00683 0.00183 -0.0651 0.5566 0.6937
-0.750 0.2595 0.00685 0.00187 -0.0653 0.5558 0.7102
-0.500 0.2880 0.00687 0.00190 -0.0655 0.5549 0.7213
-0.250 0.3168 0.00692 0.00193 -0.0658 0.5539 0.7318
0.000 0.3451 0.00696 0.00199 -0.0660 0.5528 0.7412
0.250 0.3738 0.00702 0.00203 -0.0663 0.5517 0.7490
0.500 0.4020 0.00706 0.00209 -0.0664 0.5504 0.7548
0.750 0.4305 0.00711 0.00214 -0.0667 0.5491 0.7590
1.000 0.4590 0.00716 0.00217 -0.0670 0.5479 0.7623
1.250 0.4876 0.00721 0.00220 -0.0673 0.5467 0.7649
1.500 0.5159 0.00725 0.00224 -0.0675 0.5455 0.7672
1.750 0.5439 0.00730 0.00228 -0.0677 0.5440 0.7695
2.000 0.5719 0.00736 0.00234 -0.0679 0.5424 0.7716
2.250 0.6001 0.00742 0.00239 -0.0682 0.5408 0.7732
2.500 0.6286 0.00744 0.00243 -0.0685 0.5394 0.7746
2.750 0.6569 0.00747 0.00247 -0.0688 0.5376 0.7759
3.000 0.6852 0.00750 0.00251 -0.0691 0.5356 0.7772
3.250 0.7132 0.00754 0.00256 -0.0693 0.5334 0.7784
3.500 0.7410 0.00758 0.00260 -0.0695 0.5311 0.7795
3.750 0.7684 0.00763 0.00265 -0.0697 0.5286 0.7805
4.000 0.7954 0.00771 0.00270 -0.0697 0.5258 0.7815
4.250 0.8233 0.00775 0.00277 -0.0699 0.5235 0.7825
4.500 0.8510 0.00777 0.00283 -0.0701 0.5206 0.7838
4.750 0.8782 0.00781 0.00288 -0.0702 0.5171 0.7850
5.000 0.9045 0.00786 0.00295 -0.0702 0.5132 0.7861
5.250 0.9303 0.00793 0.00302 -0.0700 0.5092 0.7873
5.500 0.9575 0.00797 0.00310 -0.0701 0.5046 0.7884
5.750 0.9831 0.00803 0.00318 -0.0699 0.4983 0.7896
6.000 1.0081 0.00811 0.00327 -0.0696 0.4925 0.7908
6.250 1.0332 0.00819 0.00336 -0.0693 0.4837 0.7920
6.500 1.0565 0.00831 0.00347 -0.0687 0.4731 0.7934
6.750 1.0778 0.00848 0.00360 -0.0677 0.4582 0.7949
7.000 1.0937 0.00877 0.00381 -0.0656 0.4348 0.7966
7.250 1.1020 0.00918 0.00409 -0.0621 0.4063 0.7982
7.500 1.1096 0.00966 0.00445 -0.0585 0.3806 0.7996
7.750 1.1158 0.01021 0.00490 -0.0548 0.3554 0.8014
8.000 1.1210 0.01079 0.00539 -0.0509 0.3299 0.8034
8.250 1.1247 0.01143 0.00593 -0.0470 0.3061 0.8055
8.500 1.1270 0.01213 0.00655 -0.0430 0.2829 0.8077
8.750 1.1285 0.01290 0.00724 -0.0390 0.2623 0.8101
9.000 1.1307 0.01371 0.00799 -0.0354 0.2436 0.8125
9.250 1.1339 0.01457 0.00880 -0.0322 0.2282 0.8150
9.750 1.1356 0.01675 0.01089 -0.0257 0.1957 0.8202
10.000 1.1383 0.01789 0.01202 -0.0231 0.1832 0.8230
10.250 1.1394 0.01921 0.01331 -0.0205 0.1695 0.8260
10.500 1.1413 0.02058 0.01465 -0.0181 0.1573 0.8291
10.750 1.1427 0.02206 0.01609 -0.0159 0.1449 0.8321
11.000 1.1464 0.02345 0.01747 -0.0140 0.1343 0.8351
11.250 1.1493 0.02492 0.01894 -0.0121 0.1238 0.8386
11.500 1.1500 0.02655 0.02055 -0.0102 0.1118 0.8425
11.750 1.1545 0.02802 0.02202 -0.0087 0.1047 0.8465
12.000 1.1562 0.02972 0.02368 -0.0071 0.0939 0.8505
12.250 1.1639 0.03100 0.02501 -0.0059 0.0891 0.8555
12.500 1.1655 0.03275 0.02673 -0.0044 0.0789 0.8614
13.000 1.1749 0.03591 0.02992 -0.0020 0.0650 0.8749
13.500 1.1865 0.03896 0.03304 0.0000 0.0550 0.8957
13.750 1.1912 0.04057 0.03473 0.0011 0.0502 0.9175
14.000 1.2126 0.04233 0.03660 -0.0014 0.0456 0.9518
15.000 1.2537 0.04948 0.04380 -0.0026 0.0330 1.0000
15.250 1.2612 0.05121 0.04555 -0.0022 0.0306 1.0000
15.500 1.2676 0.05308 0.04743 -0.0019 0.0280 1.0000
15.750 1.2742 0.05496 0.04934 -0.0017 0.0265 1.0000
16.000 1.2823 0.05671 0.05112 -0.0015 0.0246 1.0000
16.250 1.2863 0.05891 0.05332 -0.0013 0.0219 1.0000
16.500 1.2926 0.06089 0.05533 -0.0012 0.0199 1.0000
16.750 1.2983 0.06295 0.05742 -0.0011 0.0184 1.0000
17.000 1.3031 0.06515 0.05966 -0.0011 0.0167 1.0000
17.250 1.3072 0.06746 0.06199 -0.0011 0.0145 1.0000
17.500 1.3107 0.06987 0.06442 -0.0012 0.0130 1.0000
17.750 1.3150 0.07223 0.06682 -0.0014 0.0120 1.0000
18.000 1.3185 0.07469 0.06932 -0.0016 0.0108 1.0000
18.250 1.3216 0.07726 0.07194 -0.0019 0.0102 1.0000
18.500 1.3248 0.07983 0.07456 -0.0023 0.0093 1.0000
18.750 1.3274 0.08255 0.07734 -0.0027 0.0090 1.0000
19.000 1.3298 0.08530 0.08014 -0.0033 0.0084 1.0000
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