RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 500,000 Max Cl/Cd: 108.12 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1046-il-500000-n5.txt Download as CSV file: xf-r1046-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.0175 0.10628 0.10171 -0.1068 0.5955 0.0098
-11.500 -0.2825 0.04248 0.03783 -0.1365 0.6005 0.0086
-11.250 -0.3163 0.03604 0.03116 -0.1411 0.5992 0.0086
-11.000 -0.3378 0.03289 0.02781 -0.1400 0.5977 0.0086
-10.750 -0.3535 0.03083 0.02556 -0.1366 0.5960 0.0086
-10.500 -0.3575 0.02890 0.02337 -0.1341 0.5944 0.0087
-10.250 -0.3542 0.02720 0.02145 -0.1322 0.5927 0.0087
-10.000 -0.3463 0.02569 0.01970 -0.1304 0.5910 0.0089
-9.750 -0.3364 0.02426 0.01807 -0.1288 0.5893 0.0090
-9.500 -0.3207 0.02329 0.01695 -0.1277 0.5876 0.0091
-9.250 -0.3030 0.02239 0.01593 -0.1268 0.5862 0.0092
-9.000 -0.2845 0.02151 0.01493 -0.1258 0.5848 0.0094
-8.750 -0.2638 0.02084 0.01416 -0.1251 0.5833 0.0096
-8.500 -0.2430 0.02014 0.01335 -0.1244 0.5818 0.0098
-8.250 -0.2218 0.01943 0.01252 -0.1237 0.5803 0.0100
-8.000 -0.1997 0.01880 0.01176 -0.1231 0.5789 0.0102
-7.750 -0.1773 0.01819 0.01102 -0.1224 0.5775 0.0105
-7.500 -0.1540 0.01767 0.01038 -0.1219 0.5761 0.0109
-7.250 -0.1304 0.01718 0.00975 -0.1214 0.5748 0.0112
-7.000 -0.1075 0.01663 0.00913 -0.1208 0.5735 0.0116
-6.750 -0.0834 0.01625 0.00868 -0.1204 0.5722 0.0120
-6.500 -0.0588 0.01585 0.00823 -0.1200 0.5710 0.0123
-6.250 -0.0340 0.01546 0.00778 -0.1196 0.5698 0.0127
-6.000 -0.0090 0.01508 0.00734 -0.1193 0.5685 0.0132
-5.750 0.0161 0.01472 0.00692 -0.1189 0.5671 0.0137
-5.500 0.0412 0.01437 0.00653 -0.1186 0.5659 0.0143
-5.250 0.0669 0.01409 0.00622 -0.1184 0.5647 0.0149
-5.000 0.0928 0.01385 0.00594 -0.1181 0.5636 0.0158
-4.750 0.1188 0.01361 0.00564 -0.1179 0.5624 0.0167
-4.500 0.1449 0.01339 0.00541 -0.1177 0.5612 0.0182
-4.250 0.1713 0.01322 0.00519 -0.1176 0.5601 0.0199
-4.000 0.1974 0.01302 0.00497 -0.1174 0.5591 0.0216
-3.750 0.2239 0.01286 0.00476 -0.1173 0.5580 0.0239
-3.500 0.2504 0.01271 0.00459 -0.1172 0.5568 0.0267
-3.250 0.2770 0.01259 0.00444 -0.1171 0.5555 0.0301
-3.000 0.3037 0.01244 0.00430 -0.1170 0.5546 0.0344
-2.750 0.3304 0.01230 0.00418 -0.1170 0.5536 0.0402
-2.500 0.3572 0.01217 0.00408 -0.1169 0.5525 0.0489
-2.250 0.3837 0.01202 0.00399 -0.1168 0.5515 0.0640
-2.000 0.4102 0.01187 0.00392 -0.1168 0.5505 0.0854
-1.750 0.4367 0.01173 0.00385 -0.1167 0.5494 0.1118
-1.500 0.4629 0.01157 0.00380 -0.1167 0.5484 0.1487
-1.250 0.4888 0.01137 0.00376 -0.1166 0.5474 0.2018
-1.000 0.5144 0.01116 0.00373 -0.1165 0.5463 0.2678
-0.750 0.5394 0.01089 0.00372 -0.1163 0.5452 0.3537
-0.500 0.5630 0.01056 0.00374 -0.1158 0.5441 0.4738
-0.250 0.5881 0.01041 0.00377 -0.1155 0.5430 0.5463
0.000 0.6140 0.01035 0.00381 -0.1153 0.5420 0.5951
0.250 0.6396 0.01028 0.00386 -0.1150 0.5410 0.6449
0.500 0.6646 0.01021 0.00394 -0.1146 0.5400 0.7039
0.750 0.6878 0.01008 0.00403 -0.1137 0.5392 0.7734
1.000 0.7114 0.00998 0.00415 -0.1127 0.5384 0.8421
1.250 0.7415 0.00999 0.00429 -0.1131 0.5374 0.9007
1.500 0.7796 0.01010 0.00442 -0.1154 0.5363 0.9394
1.750 0.8174 0.01021 0.00451 -0.1177 0.5351 0.9606
2.000 0.8572 0.01033 0.00461 -0.1205 0.5339 0.9750
2.250 0.8961 0.01045 0.00471 -0.1231 0.5328 0.9839
2.500 0.9350 0.01056 0.00479 -0.1258 0.5318 0.9885
2.750 0.9709 0.01067 0.00488 -0.1279 0.5308 0.9933
3.000 1.0080 0.01077 0.00496 -0.1303 0.5298 0.9972
3.250 1.0425 0.01088 0.00504 -0.1321 0.5288 1.0000
3.500 1.0644 0.01097 0.00512 -0.1312 0.5277 1.0000
3.750 1.0867 0.01108 0.00521 -0.1304 0.5266 1.0000
4.000 1.1095 0.01121 0.00531 -0.1297 0.5255 1.0000
4.250 1.1330 0.01135 0.00544 -0.1292 0.5245 1.0000
4.500 1.1547 0.01148 0.00559 -0.1283 0.5236 1.0000
4.750 1.1759 0.01161 0.00575 -0.1273 0.5227 1.0000
5.000 1.1971 0.01173 0.00590 -0.1264 0.5215 1.0000
5.250 1.2184 0.01186 0.00607 -0.1254 0.5202 1.0000
5.500 1.2397 0.01199 0.00622 -0.1245 0.5188 1.0000
5.750 1.2616 0.01213 0.00639 -0.1237 0.5176 1.0000
6.000 1.2836 0.01226 0.00655 -0.1229 0.5164 1.0000
6.250 1.3058 0.01240 0.00671 -0.1222 0.5151 1.0000
6.500 1.3279 0.01252 0.00685 -0.1215 0.5138 1.0000
6.750 1.3505 0.01266 0.00702 -0.1208 0.5126 1.0000
7.000 1.3736 0.01279 0.00716 -0.1203 0.5113 1.0000
7.250 1.3977 0.01294 0.00730 -0.1200 0.5098 1.0000
7.500 1.4174 0.01311 0.00753 -0.1189 0.5081 1.0000
7.750 1.4345 0.01328 0.00778 -0.1173 0.5062 1.0000
8.000 1.4511 0.01346 0.00802 -0.1156 0.5044 1.0000
8.250 1.4672 0.01363 0.00825 -0.1138 0.5024 1.0000
8.500 1.4839 0.01381 0.00848 -0.1121 0.5005 1.0000
8.750 1.5008 0.01397 0.00868 -0.1106 0.4984 1.0000
9.000 1.5193 0.01409 0.00881 -0.1093 0.4957 1.0000
9.250 1.5320 0.01435 0.00912 -0.1071 0.4925 1.0000
9.500 1.5418 0.01467 0.00954 -0.1045 0.4887 1.0000
9.750 1.5530 0.01498 0.00989 -0.1022 0.4843 1.0000
10.000 1.5675 0.01524 0.01015 -0.1005 0.4802 1.0000
10.250 1.5749 0.01581 0.01084 -0.0979 0.4751 1.0000
10.500 1.5838 0.01638 0.01145 -0.0957 0.4697 1.0000
10.750 1.5914 0.01704 0.01215 -0.0934 0.4637 1.0000
11.000 1.5950 0.01800 0.01318 -0.0909 0.4556 1.0000
11.250 1.5982 0.01910 0.01431 -0.0884 0.4474 1.0000
11.500 1.5982 0.02048 0.01571 -0.0859 0.4380 1.0000
11.750 1.5975 0.02207 0.01734 -0.0835 0.4279 1.0000
12.000 1.5941 0.02392 0.01921 -0.0811 0.4176 1.0000
12.250 1.5823 0.02646 0.02173 -0.0781 0.4033 1.0000
12.500 1.5715 0.02906 0.02433 -0.0754 0.3907 1.0000
12.750 1.5522 0.03242 0.02765 -0.0722 0.3736 1.0000
13.000 1.5355 0.03574 0.03094 -0.0695 0.3581 1.0000
13.250 1.5144 0.03955 0.03469 -0.0668 0.3406 1.0000
13.500 1.4975 0.04317 0.03826 -0.0645 0.3250 1.0000
13.750 1.4819 0.04677 0.04181 -0.0624 0.3082 1.0000
14.000 1.4649 0.05061 0.04558 -0.0604 0.2908 1.0000
14.250 1.4520 0.05418 0.04910 -0.0588 0.2754 1.0000
14.500 1.4404 0.05772 0.05258 -0.0574 0.2590 1.0000
14.750 1.4345 0.06076 0.05558 -0.0563 0.2451 1.0000
15.000 1.4262 0.06412 0.05889 -0.0553 0.2305 1.0000
15.250 1.4206 0.06725 0.06197 -0.0544 0.2159 1.0000
15.500 1.4155 0.07040 0.06509 -0.0537 0.2031 1.0000
15.750 1.4112 0.07351 0.06814 -0.0530 0.1887 1.0000
16.000 1.4092 0.07643 0.07104 -0.0526 0.1769 1.0000
16.250 1.4079 0.07928 0.07387 -0.0521 0.1651 1.0000
16.500 1.4050 0.08238 0.07693 -0.0518 0.1528 1.0000
16.750 1.4025 0.08546 0.07998 -0.0515 0.1407 1.0000
17.000 1.4014 0.08843 0.08291 -0.0513 0.1294 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)