RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 100,000 Max Cl/Cd: 20.53 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1046-il-100000-n5.txt Download as CSV file: xf-r1046-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1046 VOYAGER CANARD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0250 0.11175 0.10513 -0.1102 0.6791 0.0570
-11.000 0.0267 0.10870 0.10209 -0.1121 0.6771 0.0571
-10.750 0.0289 0.10551 0.09889 -0.1138 0.6752 0.0571
-10.250 0.0519 0.09612 0.08937 -0.1142 0.6718 0.0364
-9.750 0.0483 0.08753 0.08088 -0.1181 0.6679 0.0319
-9.500 0.0536 0.08484 0.07822 -0.1190 0.6657 0.0315
-9.250 0.0556 0.08168 0.07509 -0.1202 0.6636 0.0309
-9.000 0.0547 0.07810 0.07154 -0.1218 0.6616 0.0305
-8.750 0.0508 0.07405 0.06752 -0.1237 0.6597 0.0300
-8.250 -0.0144 0.05678 0.05020 -0.1349 0.6569 0.0276
-8.000 -0.0282 0.05366 0.04693 -0.1345 0.6553 0.0274
-7.750 -0.0393 0.05043 0.04355 -0.1338 0.6531 0.0273
-7.500 -0.0474 0.04714 0.04002 -0.1327 0.6509 0.0273
-7.250 -0.0530 0.04368 0.03617 -0.1310 0.6489 0.0274
-7.000 -0.0474 0.04144 0.03365 -0.1297 0.6469 0.0280
-6.750 -0.0332 0.04033 0.03244 -0.1288 0.6449 0.0290
-6.500 -0.0219 0.03845 0.03023 -0.1276 0.6432 0.0300
-6.250 -0.0098 0.03625 0.02757 -0.1261 0.6416 0.0310
-6.000 0.0055 0.03410 0.02490 -0.1247 0.6401 0.0317
-5.750 0.0249 0.03239 0.02278 -0.1237 0.6387 0.0324
-5.500 0.0442 0.03145 0.02173 -0.1227 0.6366 0.0334
-5.250 0.0627 0.03062 0.02078 -0.1216 0.6341 0.0346
-5.000 0.0826 0.02977 0.01965 -0.1204 0.6318 0.0371
-4.750 0.1031 0.02923 0.01912 -0.1197 0.6298 0.0392
-4.500 0.1248 0.02857 0.01830 -0.1188 0.6280 0.0419
-4.250 0.1467 0.02793 0.01760 -0.1180 0.6264 0.0443
-4.000 0.1693 0.02749 0.01706 -0.1173 0.6249 0.0484
-3.750 0.1920 0.02702 0.01658 -0.1166 0.6236 0.0529
-3.500 0.2155 0.02659 0.01607 -0.1160 0.6223 0.0591
-3.250 0.2389 0.02623 0.01563 -0.1154 0.6211 0.0667
-3.000 0.2516 0.02638 0.01587 -0.1134 0.6181 0.0744
-2.750 0.2665 0.02643 0.01598 -0.1116 0.6155 0.0850
-2.500 0.2832 0.02643 0.01604 -0.1102 0.6133 0.1016
-2.250 0.3011 0.02634 0.01607 -0.1089 0.6115 0.1301
-2.000 0.3197 0.02613 0.01613 -0.1078 0.6098 0.1872
-1.750 0.3389 0.02578 0.01621 -0.1069 0.6083 0.2990
-1.500 0.3582 0.02532 0.01635 -0.1057 0.6070 0.4640
-1.250 0.3799 0.02504 0.01647 -0.1044 0.6058 0.6038
-1.000 0.4034 0.02490 0.01655 -0.1030 0.6047 0.7074
-0.750 0.3910 0.02652 0.01851 -0.0974 0.5997 0.7610
-0.500 0.4228 0.02734 0.01955 -0.0986 0.5971 0.8743
-0.250 0.4978 0.02785 0.01989 -0.1079 0.5958 0.9739
0.000 0.5458 0.02837 0.02021 -0.1127 0.5942 1.0000
0.250 0.5543 0.02887 0.02057 -0.1100 0.5921 1.0000
0.500 0.5700 0.02920 0.02073 -0.1083 0.5905 1.0000
0.750 0.5894 0.02947 0.02085 -0.1072 0.5893 1.0000
1.000 0.6108 0.02975 0.02098 -0.1063 0.5883 1.0000
2.000 0.5568 0.03711 0.02825 -0.0862 0.5716 1.0000
3.000 0.4876 0.04971 0.04086 -0.0732 0.5442 1.0000
3.250 0.5086 0.05037 0.04142 -0.0728 0.5426 1.0000
3.500 0.5318 0.05090 0.04186 -0.0725 0.5413 1.0000
3.750 0.5577 0.05124 0.04210 -0.0724 0.5404 1.0000
4.250 0.5471 0.05619 0.04704 -0.0687 0.5282 1.0000
4.500 0.5709 0.05666 0.04744 -0.0685 0.5266 1.0000
4.750 0.5961 0.05704 0.04775 -0.0684 0.5254 1.0000
5.000 0.6228 0.05733 0.04797 -0.0683 0.5244 1.0000
5.500 0.6180 0.06198 0.05264 -0.0653 0.5120 1.0000
5.750 0.6420 0.06247 0.05309 -0.0652 0.5106 1.0000
6.000 0.6672 0.06289 0.05347 -0.0651 0.5095 1.0000
6.500 0.6669 0.06741 0.05802 -0.0627 0.4974 1.0000
6.750 0.6911 0.06785 0.05845 -0.0626 0.4959 1.0000
7.000 0.7167 0.06819 0.05876 -0.0626 0.4948 1.0000
7.250 0.7002 0.07167 0.06230 -0.0608 0.4845 1.0000
7.500 0.7236 0.07210 0.06272 -0.0607 0.4824 1.0000
7.750 0.7488 0.07238 0.06300 -0.0606 0.4809 1.0000
8.250 0.7577 0.07635 0.06704 -0.0590 0.4691 1.0000
8.500 0.7819 0.07664 0.06733 -0.0589 0.4672 1.0000
8.750 0.8077 0.07683 0.06752 -0.0589 0.4659 1.0000
9.000 0.7950 0.08031 0.07108 -0.0577 0.4556 1.0000
9.250 0.8178 0.08070 0.07150 -0.0575 0.4534 1.0000
9.500 0.8435 0.08079 0.07161 -0.0575 0.4519 1.0000
10.000 0.8562 0.08446 0.07539 -0.0563 0.4394 1.0000
10.250 0.8817 0.08449 0.07546 -0.0563 0.4378 1.0000
10.750 0.8960 0.08807 0.07916 -0.0553 0.4251 1.0000
11.000 0.9214 0.08800 0.07915 -0.0552 0.4234 1.0000
11.250 0.9135 0.09140 0.08262 -0.0546 0.4127 1.0000
11.500 0.9367 0.09152 0.08280 -0.0545 0.4104 1.0000
11.750 0.9625 0.09130 0.08265 -0.0543 0.4088 1.0000
12.250 0.9786 0.09475 0.08625 -0.0537 0.3955 1.0000
12.750 0.9971 0.09800 0.08968 -0.0532 0.3823 1.0000
13.000 1.0234 0.09747 0.08923 -0.0530 0.3804 1.0000
13.500 1.0425 0.10058 0.09251 -0.0526 0.3668 1.0000
13.750 1.0697 0.09978 0.09181 -0.0524 0.3650 1.0000
14.000 1.0636 0.10346 0.09559 -0.0523 0.3533 1.0000
14.250 1.0899 0.10271 0.09494 -0.0521 0.3512 1.0000
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Polar data table (+)
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