RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.63 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1046-il-1000000-n5.txt Download as CSV file: xf-r1046-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4784 0.03932 0.03505 -0.1392 0.5920 0.0062
-13.250 -0.5062 0.03336 0.02891 -0.1434 0.5904 0.0062
-12.750 -0.5331 0.02814 0.02340 -0.1421 0.5871 0.0063
-12.500 -0.5355 0.02677 0.02193 -0.1397 0.5857 0.0063
-12.250 -0.5407 0.02552 0.02057 -0.1363 0.5842 0.0063
-12.000 -0.5342 0.02450 0.01943 -0.1342 0.5826 0.0064
-11.750 -0.5229 0.02357 0.01838 -0.1326 0.5810 0.0065
-11.500 -0.5128 0.02245 0.01712 -0.1309 0.5792 0.0065
-11.250 -0.4967 0.02169 0.01625 -0.1297 0.5774 0.0065
-11.000 -0.4805 0.02088 0.01532 -0.1286 0.5755 0.0066
-10.750 -0.4623 0.02019 0.01452 -0.1276 0.5735 0.0066
-10.500 -0.4454 0.01934 0.01354 -0.1264 0.5716 0.0067
-10.250 -0.4272 0.01852 0.01261 -0.1254 0.5705 0.0068
-10.000 -0.4074 0.01780 0.01181 -0.1245 0.5694 0.0069
-9.750 -0.3862 0.01718 0.01110 -0.1238 0.5681 0.0071
-9.500 -0.3636 0.01669 0.01055 -0.1232 0.5668 0.0072
-9.250 -0.3406 0.01620 0.00999 -0.1227 0.5655 0.0072
-9.000 -0.3174 0.01573 0.00944 -0.1221 0.5641 0.0074
-8.750 -0.2932 0.01534 0.00899 -0.1217 0.5628 0.0075
-8.500 -0.2690 0.01495 0.00854 -0.1213 0.5614 0.0077
-8.250 -0.2447 0.01456 0.00808 -0.1208 0.5600 0.0078
-8.000 -0.2200 0.01422 0.00767 -0.1205 0.5587 0.0080
-7.750 -0.1953 0.01387 0.00725 -0.1201 0.5573 0.0082
-7.500 -0.1702 0.01357 0.00689 -0.1197 0.5558 0.0084
-7.250 -0.1446 0.01326 0.00653 -0.1195 0.5549 0.0086
-7.000 -0.1187 0.01297 0.00619 -0.1193 0.5539 0.0087
-6.750 -0.0929 0.01267 0.00585 -0.1190 0.5529 0.0089
-6.500 -0.0673 0.01234 0.00549 -0.1187 0.5518 0.0093
-6.250 -0.0411 0.01209 0.00521 -0.1186 0.5508 0.0096
-6.000 -0.0146 0.01187 0.00497 -0.1184 0.5497 0.0101
-5.750 0.0121 0.01168 0.00475 -0.1183 0.5486 0.0105
-5.500 0.0387 0.01148 0.00452 -0.1182 0.5475 0.0110
-5.250 0.0654 0.01129 0.00429 -0.1181 0.5465 0.0113
-5.000 0.0919 0.01109 0.00407 -0.1179 0.5454 0.0120
-4.750 0.1187 0.01093 0.00389 -0.1179 0.5443 0.0127
-4.500 0.1457 0.01079 0.00372 -0.1178 0.5432 0.0137
-4.250 0.1725 0.01065 0.00357 -0.1177 0.5421 0.0148
-4.000 0.1994 0.01054 0.00344 -0.1176 0.5407 0.0161
-3.750 0.2265 0.01043 0.00331 -0.1176 0.5395 0.0180
-3.500 0.2540 0.01031 0.00320 -0.1176 0.5388 0.0205
-3.250 0.2815 0.01019 0.00309 -0.1177 0.5380 0.0232
-3.000 0.3089 0.01008 0.00299 -0.1177 0.5373 0.0260
-2.750 0.3364 0.00998 0.00290 -0.1178 0.5364 0.0292
-2.500 0.3640 0.00989 0.00282 -0.1179 0.5356 0.0335
-2.250 0.3914 0.00979 0.00274 -0.1179 0.5347 0.0403
-2.000 0.4186 0.00968 0.00267 -0.1180 0.5337 0.0520
-1.750 0.4458 0.00956 0.00262 -0.1180 0.5328 0.0687
-1.500 0.4728 0.00945 0.00257 -0.1180 0.5317 0.0904
-1.250 0.4997 0.00933 0.00252 -0.1180 0.5306 0.1179
-1.000 0.5265 0.00920 0.00249 -0.1180 0.5295 0.1509
-0.750 0.5528 0.00905 0.00247 -0.1180 0.5284 0.1995
-0.500 0.5792 0.00892 0.00246 -0.1179 0.5275 0.2503
-0.250 0.6046 0.00870 0.00246 -0.1178 0.5264 0.3314
0.000 0.6292 0.00844 0.00249 -0.1175 0.5253 0.4360
0.250 0.6553 0.00835 0.00253 -0.1174 0.5243 0.4935
0.500 0.6821 0.00827 0.00257 -0.1174 0.5237 0.5404
0.750 0.7086 0.00818 0.00261 -0.1174 0.5230 0.5876
1.000 0.7346 0.00808 0.00266 -0.1172 0.5221 0.6402
1.250 0.7601 0.00797 0.00271 -0.1169 0.5212 0.6963
1.750 0.8107 0.00783 0.00283 -0.1162 0.5193 0.7890
2.000 0.8348 0.00774 0.00291 -0.1155 0.5184 0.8431
2.250 0.8592 0.00769 0.00303 -0.1148 0.5175 0.9113
2.500 0.8927 0.00776 0.00314 -0.1161 0.5165 0.9546
2.750 0.9296 0.00786 0.00323 -0.1183 0.5155 0.9723
3.000 0.9659 0.00795 0.00331 -0.1204 0.5144 0.9804
3.250 1.0008 0.00804 0.00338 -0.1222 0.5132 0.9847
3.500 1.0366 0.00814 0.00346 -0.1243 0.5121 0.9876
3.750 1.0705 0.00825 0.00355 -0.1260 0.5110 0.9909
4.000 1.1030 0.00837 0.00365 -0.1273 0.5099 0.9939
4.250 1.1374 0.00847 0.00375 -0.1292 0.5089 0.9966
4.500 1.1713 0.00855 0.00385 -0.1309 0.5081 0.9988
4.750 1.2017 0.00863 0.00394 -0.1318 0.5072 1.0000
5.000 1.2233 0.00870 0.00404 -0.1308 0.5061 1.0000
5.250 1.2451 0.00878 0.00413 -0.1299 0.5051 1.0000
5.500 1.2669 0.00885 0.00422 -0.1290 0.5040 1.0000
5.750 1.2886 0.00893 0.00432 -0.1281 0.5027 1.0000
6.000 1.3102 0.00901 0.00442 -0.1272 0.5012 1.0000
6.250 1.3313 0.00910 0.00452 -0.1262 0.4997 1.0000
6.500 1.3523 0.00920 0.00463 -0.1252 0.4982 1.0000
6.750 1.3727 0.00931 0.00474 -0.1240 0.4964 1.0000
7.000 1.3928 0.00945 0.00488 -0.1229 0.4944 1.0000
7.250 1.4130 0.00953 0.00500 -0.1217 0.4931 1.0000
7.500 1.4331 0.00963 0.00514 -0.1206 0.4917 1.0000
7.750 1.4530 0.00973 0.00529 -0.1194 0.4898 1.0000
8.000 1.4724 0.00984 0.00543 -0.1181 0.4873 1.0000
8.250 1.4905 0.00998 0.00559 -0.1167 0.4842 1.0000
8.500 1.5065 0.01017 0.00577 -0.1149 0.4808 1.0000
8.750 1.5259 0.01031 0.00596 -0.1138 0.4764 1.0000
9.000 1.5434 0.01050 0.00618 -0.1123 0.4711 1.0000
9.250 1.5567 0.01080 0.00646 -0.1102 0.4657 1.0000
9.500 1.5757 0.01101 0.00673 -0.1092 0.4605 1.0000
9.750 1.5858 0.01144 0.00714 -0.1066 0.4517 1.0000
10.000 1.5988 0.01186 0.00758 -0.1047 0.4420 1.0000
10.250 1.6058 0.01251 0.00821 -0.1020 0.4307 1.0000
10.500 1.6080 0.01343 0.00910 -0.0987 0.4170 1.0000
10.750 1.6101 0.01448 0.01014 -0.0957 0.4054 1.0000
11.000 1.6035 0.01612 0.01173 -0.0920 0.3878 1.0000
11.250 1.5991 0.01785 0.01345 -0.0888 0.3744 1.0000
11.500 1.5761 0.02096 0.01648 -0.0843 0.3522 1.0000
11.750 1.5597 0.02390 0.01939 -0.0808 0.3364 1.0000
12.000 1.5412 0.02714 0.02261 -0.0775 0.3212 1.0000
12.250 1.5245 0.03038 0.02583 -0.0745 0.3057 1.0000
12.500 1.5026 0.03417 0.02957 -0.0714 0.2888 1.0000
13.000 1.4733 0.04091 0.03625 -0.0667 0.2613 1.0000
13.250 1.4637 0.04396 0.03928 -0.0649 0.2478 1.0000
13.500 1.4496 0.04745 0.04271 -0.0629 0.2310 1.0000
13.750 1.4422 0.05044 0.04567 -0.0614 0.2184 1.0000
14.000 1.4360 0.05336 0.04853 -0.0600 0.2045 1.0000
14.250 1.4318 0.05612 0.05127 -0.0588 0.1923 1.0000
14.500 1.4310 0.05858 0.05370 -0.0578 0.1814 1.0000
14.750 1.4262 0.06152 0.05659 -0.0568 0.1690 1.0000
15.000 1.4249 0.06410 0.05913 -0.0559 0.1574 1.0000
15.250 1.4184 0.06726 0.06222 -0.0549 0.1421 1.0000
15.500 1.4196 0.06966 0.06461 -0.0543 0.1337 1.0000
15.750 1.4182 0.07237 0.06726 -0.0536 0.1216 1.0000
16.000 1.4160 0.07524 0.07009 -0.0530 0.1105 1.0000
16.250 1.4168 0.07780 0.07260 -0.0526 0.1001 1.0000
16.500 1.4178 0.08034 0.07513 -0.0522 0.0915 1.0000
16.750 1.4160 0.08327 0.07802 -0.0518 0.0814 1.0000
17.000 1.4181 0.08577 0.08049 -0.0516 0.0742 1.0000
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Polar data table (+)
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