RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.84 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1046-il-1000000.txt Download as CSV file: xf-r1046-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 0.0277 0.10016 0.09647 -0.1130 0.5979 0.0139
-11.500 -0.2947 0.03773 0.03379 -0.1426 0.6034 0.0090
-11.250 -0.3254 0.03315 0.02906 -0.1442 0.6022 0.0091
-11.000 -0.3485 0.03038 0.02610 -0.1415 0.6009 0.0091
-10.750 -0.3632 0.02856 0.02412 -0.1375 0.5994 0.0091
-10.500 -0.3576 0.02736 0.02284 -0.1357 0.5978 0.0093
-10.250 -0.3598 0.02512 0.02032 -0.1331 0.5962 0.0093
-10.000 -0.3430 0.02451 0.01966 -0.1321 0.5945 0.0095
-9.750 -0.3309 0.02327 0.01825 -0.1307 0.5928 0.0096
-9.500 -0.3151 0.02232 0.01716 -0.1295 0.5909 0.0098
-9.250 -0.2983 0.02139 0.01607 -0.1284 0.5887 0.0100
-9.000 -0.2823 0.02016 0.01465 -0.1271 0.5874 0.0101
-8.750 -0.2616 0.01943 0.01382 -0.1264 0.5864 0.0103
-8.500 -0.2414 0.01856 0.01280 -0.1255 0.5853 0.0106
-8.250 -0.2204 0.01771 0.01182 -0.1247 0.5840 0.0107
-8.000 -0.1978 0.01708 0.01107 -0.1241 0.5827 0.0109
-7.750 -0.1750 0.01642 0.01029 -0.1235 0.5813 0.0111
-7.500 -0.1506 0.01597 0.00975 -0.1231 0.5798 0.0112
-7.250 -0.1302 0.01495 0.00859 -0.1221 0.5784 0.0115
-7.000 -0.1073 0.01433 0.00789 -0.1215 0.5770 0.0117
-6.750 -0.0827 0.01393 0.00744 -0.1211 0.5756 0.0121
-6.500 -0.0578 0.01359 0.00704 -0.1207 0.5740 0.0123
-6.250 -0.0324 0.01331 0.00670 -0.1204 0.5722 0.0127
-6.000 -0.0068 0.01299 0.00633 -0.1201 0.5712 0.0132
-5.750 0.0197 0.01274 0.00604 -0.1200 0.5704 0.0137
-5.500 0.0446 0.01231 0.00557 -0.1196 0.5696 0.0144
-5.250 0.0709 0.01205 0.00530 -0.1194 0.5686 0.0151
-5.000 0.0976 0.01184 0.00507 -0.1193 0.5675 0.0159
-4.750 0.1243 0.01163 0.00481 -0.1192 0.5664 0.0166
-4.500 0.1502 0.01131 0.00448 -0.1189 0.5652 0.0178
-4.250 0.1772 0.01114 0.00429 -0.1189 0.5640 0.0192
-4.000 0.2038 0.01093 0.00405 -0.1187 0.5628 0.0207
-3.750 0.2309 0.01077 0.00388 -0.1187 0.5618 0.0231
-3.500 0.2578 0.01060 0.00371 -0.1186 0.5607 0.0266
-3.250 0.2849 0.01047 0.00357 -0.1186 0.5595 0.0306
-3.000 0.3120 0.01036 0.00346 -0.1186 0.5582 0.0353
-2.750 0.3394 0.01029 0.00338 -0.1187 0.5568 0.0412
-2.500 0.3667 0.01022 0.00333 -0.1187 0.5554 0.0514
-2.250 0.3937 0.01004 0.00324 -0.1187 0.5548 0.0711
-2.000 0.4205 0.00986 0.00317 -0.1187 0.5541 0.1001
-1.750 0.4470 0.00964 0.00310 -0.1187 0.5532 0.1437
-1.500 0.4729 0.00938 0.00306 -0.1186 0.5523 0.2123
-1.250 0.4986 0.00911 0.00303 -0.1185 0.5513 0.2921
-1.000 0.5243 0.00885 0.00301 -0.1184 0.5504 0.3777
-0.750 0.5495 0.00858 0.00303 -0.1182 0.5494 0.4768
-0.500 0.5757 0.00844 0.00305 -0.1181 0.5484 0.5437
-0.250 0.6017 0.00831 0.00309 -0.1179 0.5474 0.6086
0.000 0.6272 0.00818 0.00313 -0.1176 0.5465 0.6731
0.250 0.6533 0.00810 0.00316 -0.1173 0.5454 0.7180
0.500 0.6787 0.00802 0.00320 -0.1170 0.5444 0.7671
0.750 0.7029 0.00793 0.00327 -0.1163 0.5432 0.8308
1.000 0.7273 0.00789 0.00342 -0.1154 0.5420 0.9085
1.250 0.7598 0.00805 0.00361 -0.1164 0.5406 0.9536
1.500 0.7929 0.00821 0.00374 -0.1176 0.5395 0.9709
1.750 0.8333 0.00830 0.00382 -0.1205 0.5390 0.9777
2.000 0.8717 0.00839 0.00389 -0.1230 0.5383 0.9837
2.250 0.9160 0.00847 0.00396 -0.1268 0.5374 0.9868
2.500 0.9597 0.00855 0.00402 -0.1305 0.5364 0.9913
2.750 1.0016 0.00862 0.00408 -0.1338 0.5354 0.9948
3.000 1.0422 0.00868 0.00413 -0.1369 0.5344 0.9973
3.250 1.0812 0.00875 0.00419 -0.1397 0.5334 0.9994
3.500 1.1090 0.00882 0.00425 -0.1400 0.5324 1.0000
3.750 1.1315 0.00889 0.00432 -0.1393 0.5314 1.0000
4.000 1.1542 0.00896 0.00439 -0.1385 0.5304 1.0000
4.250 1.1768 0.00904 0.00446 -0.1378 0.5293 1.0000
4.500 1.1994 0.00913 0.00454 -0.1371 0.5282 1.0000
4.750 1.2226 0.00924 0.00465 -0.1364 0.5271 1.0000
5.000 1.2465 0.00940 0.00480 -0.1360 0.5258 1.0000
5.250 1.2710 0.00962 0.00501 -0.1357 0.5242 1.0000
5.500 1.2924 0.00968 0.00511 -0.1348 0.5235 1.0000
5.750 1.3138 0.00974 0.00521 -0.1338 0.5225 1.0000
6.000 1.3354 0.00981 0.00531 -0.1329 0.5214 1.0000
6.250 1.3572 0.00987 0.00540 -0.1320 0.5200 1.0000
6.500 1.3793 0.00994 0.00550 -0.1312 0.5185 1.0000
6.750 1.4017 0.01001 0.00558 -0.1305 0.5170 1.0000
7.000 1.4245 0.01007 0.00566 -0.1298 0.5156 1.0000
7.250 1.4475 0.01016 0.00577 -0.1293 0.5142 1.0000
7.500 1.4706 0.01025 0.00587 -0.1287 0.5129 1.0000
7.750 1.4948 0.01038 0.00600 -0.1284 0.5108 1.0000
8.000 1.5179 0.01053 0.00618 -0.1279 0.5086 1.0000
8.250 1.5356 0.01056 0.00627 -0.1263 0.5066 1.0000
8.500 1.5531 0.01057 0.00633 -0.1246 0.5038 1.0000
8.750 1.5686 0.01058 0.00637 -0.1225 0.5006 1.0000
9.000 1.5837 0.01064 0.00644 -0.1204 0.4977 1.0000
9.250 1.6024 0.01080 0.00658 -0.1191 0.4942 1.0000
9.500 1.6149 0.01090 0.00677 -0.1166 0.4914 1.0000
9.750 1.6280 0.01101 0.00694 -0.1143 0.4868 1.0000
10.000 1.6429 0.01119 0.00713 -0.1124 0.4827 1.0000
10.250 1.6581 0.01144 0.00741 -0.1107 0.4788 1.0000
10.500 1.6744 0.01166 0.00771 -0.1092 0.4745 1.0000
10.750 1.6896 0.01195 0.00804 -0.1076 0.4702 1.0000
11.000 1.7012 0.01237 0.00845 -0.1055 0.4658 1.0000
11.250 1.7172 0.01271 0.00887 -0.1042 0.4603 1.0000
11.500 1.7276 0.01324 0.00943 -0.1021 0.4539 1.0000
11.750 1.7381 0.01385 0.01008 -0.1001 0.4472 1.0000
12.000 1.7416 0.01480 0.01103 -0.0974 0.4378 1.0000
12.250 1.7472 0.01578 0.01204 -0.0951 0.4276 1.0000
12.500 1.7440 0.01732 0.01358 -0.0920 0.4146 1.0000
12.750 1.7345 0.01941 0.01564 -0.0886 0.3995 1.0000
13.000 1.7190 0.02208 0.01828 -0.0850 0.3833 1.0000
13.250 1.6886 0.02601 0.02216 -0.0805 0.3629 1.0000
13.500 1.6619 0.02992 0.02603 -0.0767 0.3446 1.0000
13.750 1.6394 0.03368 0.02976 -0.0735 0.3294 1.0000
14.000 1.6092 0.03824 0.03426 -0.0700 0.3097 1.0000
14.250 1.5849 0.04246 0.03843 -0.0672 0.2928 1.0000
14.500 1.5621 0.04666 0.04256 -0.0647 0.2761 1.0000
14.750 1.5501 0.05001 0.04587 -0.0629 0.2624 1.0000
15.000 1.5342 0.05376 0.04956 -0.0610 0.2444 1.0000
15.250 1.5190 0.05753 0.05325 -0.0593 0.2261 1.0000
15.500 1.5080 0.06100 0.05665 -0.0580 0.2105 1.0000
15.750 1.5001 0.06420 0.05979 -0.0568 0.1950 1.0000
16.000 1.4919 0.06750 0.06304 -0.0558 0.1805 1.0000
16.250 1.4836 0.07085 0.06630 -0.0548 0.1640 1.0000
16.500 1.4793 0.07388 0.06928 -0.0541 0.1516 1.0000
16.750 1.4739 0.07706 0.07239 -0.0534 0.1375 1.0000
17.000 1.4742 0.07963 0.07493 -0.0530 0.1277 1.0000
17.250 1.4710 0.08268 0.07795 -0.0526 0.1175 1.0000
17.500 1.4695 0.08555 0.08077 -0.0523 0.1066 1.0000
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Polar data table (+)
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