RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 500,000 Max Cl/Cd: 101.39 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1046-il-500000.txt Download as CSV file: xf-r1046-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.0602 0.09549 0.09108 -0.1140 0.6215 0.0227
-10.500 0.0405 0.08800 0.08366 -0.1190 0.6209 0.0237
-10.250 0.0439 0.08464 0.08033 -0.1202 0.6198 0.0237
-10.000 0.0556 0.08317 0.07887 -0.1199 0.6183 0.0240
-9.750 0.0636 0.08104 0.07676 -0.1205 0.6169 0.0243
-9.500 0.0699 0.07865 0.07438 -0.1214 0.6155 0.0247
-9.250 0.0732 0.07581 0.07156 -0.1225 0.6141 0.0250
-9.000 0.0739 0.07256 0.06833 -0.1240 0.6128 0.0252
-8.750 0.0712 0.06879 0.06459 -0.1259 0.6116 0.0264
-8.250 -0.1386 0.03279 0.02752 -0.1332 0.6115 0.0168
-8.000 -0.1353 0.02981 0.02428 -0.1314 0.6101 0.0167
-7.750 -0.1278 0.02720 0.02137 -0.1297 0.6087 0.0166
-7.500 -0.1169 0.02497 0.01872 -0.1279 0.6072 0.0167
-7.250 -0.1008 0.02335 0.01673 -0.1266 0.6055 0.0168
-7.000 -0.0831 0.02158 0.01469 -0.1255 0.6039 0.0170
-6.750 -0.0620 0.02033 0.01334 -0.1248 0.6028 0.0173
-6.500 -0.0387 0.01960 0.01253 -0.1244 0.6015 0.0177
-6.250 -0.0142 0.01911 0.01200 -0.1241 0.6001 0.0184
-6.000 0.0099 0.01839 0.01113 -0.1236 0.5987 0.0192
-5.750 0.0346 0.01775 0.01032 -0.1231 0.5974 0.0198
-5.500 0.0585 0.01685 0.00932 -0.1225 0.5960 0.0205
-5.250 0.0833 0.01629 0.00874 -0.1222 0.5947 0.0212
-5.000 0.1087 0.01587 0.00827 -0.1219 0.5935 0.0222
-4.750 0.1343 0.01548 0.00779 -0.1216 0.5922 0.0232
-4.500 0.1588 0.01497 0.00725 -0.1211 0.5909 0.0247
-4.250 0.1848 0.01474 0.00697 -0.1209 0.5895 0.0265
-4.000 0.2103 0.01450 0.00669 -0.1207 0.5878 0.0288
-3.750 0.2362 0.01426 0.00646 -0.1205 0.5869 0.0319
-3.500 0.2612 0.01392 0.00615 -0.1201 0.5859 0.0358
-3.250 0.2869 0.01366 0.00590 -0.1198 0.5848 0.0407
-3.000 0.3129 0.01346 0.00572 -0.1197 0.5836 0.0475
-2.750 0.3392 0.01329 0.00557 -0.1195 0.5824 0.0568
-2.500 0.3651 0.01306 0.00542 -0.1193 0.5812 0.0751
-2.250 0.3906 0.01279 0.00531 -0.1192 0.5800 0.1151
-2.000 0.4156 0.01245 0.00522 -0.1190 0.5788 0.1870
-1.750 0.4403 0.01210 0.00516 -0.1187 0.5775 0.2838
-1.500 0.4644 0.01173 0.00514 -0.1184 0.5763 0.3972
-1.250 0.4886 0.01145 0.00517 -0.1180 0.5752 0.5097
-1.000 0.5137 0.01132 0.00524 -0.1177 0.5742 0.5869
-0.750 0.5389 0.01127 0.00535 -0.1173 0.5730 0.6547
-0.500 0.5630 0.01132 0.00559 -0.1166 0.5717 0.7261
-0.250 0.5863 0.01120 0.00569 -0.1157 0.5709 0.7885
0.000 0.6106 0.01114 0.00580 -0.1148 0.5700 0.8492
0.250 0.6417 0.01119 0.00597 -0.1153 0.5689 0.9099
0.500 0.6810 0.01133 0.00612 -0.1176 0.5676 0.9484
0.750 0.7204 0.01150 0.00625 -0.1201 0.5663 0.9704
1.000 0.7686 0.01164 0.00635 -0.1246 0.5651 0.9773
1.250 0.8121 0.01178 0.00643 -0.1282 0.5640 0.9846
1.500 0.8588 0.01189 0.00650 -0.1325 0.5629 0.9901
1.750 0.9066 0.01199 0.00655 -0.1370 0.5618 0.9959
2.000 0.9515 0.01207 0.00658 -0.1410 0.5607 1.0000
2.250 0.9734 0.01218 0.00665 -0.1402 0.5597 1.0000
2.500 0.9962 0.01230 0.00673 -0.1396 0.5585 1.0000
2.750 1.0196 0.01247 0.00686 -0.1390 0.5574 1.0000
3.000 1.0428 0.01275 0.00710 -0.1385 0.5562 1.0000
3.250 1.0641 0.01302 0.00738 -0.1376 0.5551 1.0000
3.500 1.0844 0.01317 0.00757 -0.1365 0.5542 1.0000
3.750 1.1048 0.01335 0.00777 -0.1354 0.5531 1.0000
4.000 1.1251 0.01352 0.00797 -0.1343 0.5519 1.0000
4.250 1.1456 0.01369 0.00817 -0.1332 0.5504 1.0000
4.500 1.1667 0.01386 0.00836 -0.1322 0.5490 1.0000
4.750 1.1883 0.01405 0.00856 -0.1314 0.5478 1.0000
5.000 1.2106 0.01422 0.00876 -0.1307 0.5466 1.0000
5.250 1.2339 0.01437 0.00892 -0.1301 0.5454 1.0000
5.500 1.2582 0.01450 0.00905 -0.1298 0.5442 1.0000
5.750 1.2834 0.01464 0.00918 -0.1296 0.5430 1.0000
6.000 1.3090 0.01483 0.00936 -0.1296 0.5420 1.0000
6.250 1.3353 0.01509 0.00961 -0.1297 0.5408 1.0000
6.500 1.3579 0.01544 0.01000 -0.1292 0.5393 1.0000
6.750 1.3754 0.01559 0.01023 -0.1276 0.5377 1.0000
7.000 1.3937 0.01578 0.01049 -0.1263 0.5358 1.0000
7.250 1.4133 0.01598 0.01075 -0.1252 0.5340 1.0000
7.500 1.4344 0.01617 0.01099 -0.1243 0.5323 1.0000
7.750 1.4567 0.01630 0.01116 -0.1237 0.5307 1.0000
8.000 1.4813 0.01641 0.01129 -0.1236 0.5292 1.0000
8.250 1.5081 0.01648 0.01138 -0.1238 0.5278 1.0000
8.500 1.5385 0.01648 0.01137 -0.1246 0.5261 1.0000
8.750 1.5648 0.01663 0.01154 -0.1248 0.5237 1.0000
9.000 1.5730 0.01678 0.01181 -0.1216 0.5208 1.0000
9.250 1.5865 0.01686 0.01197 -0.1194 0.5178 1.0000
9.500 1.6073 0.01671 0.01185 -0.1184 0.5148 1.0000
9.750 1.6358 0.01644 0.01156 -0.1187 0.5118 1.0000
10.000 1.6618 0.01639 0.01150 -0.1188 0.5087 1.0000
10.250 1.6520 0.01662 0.01186 -0.1122 0.5050 1.0000
10.500 1.6578 0.01668 0.01199 -0.1086 0.5009 1.0000
10.750 1.6755 0.01655 0.01185 -0.1072 0.4969 1.0000
11.000 1.6880 0.01672 0.01206 -0.1050 0.4931 1.0000
11.250 1.6830 0.01735 0.01282 -0.1003 0.4887 1.0000
11.500 1.6901 0.01775 0.01329 -0.0977 0.4843 1.0000
11.750 1.7083 0.01791 0.01344 -0.0967 0.4805 1.0000
12.000 1.7006 0.01909 0.01476 -0.0925 0.4754 1.0000
12.250 1.7011 0.02012 0.01587 -0.0897 0.4699 1.0000
12.500 1.7084 0.02091 0.01668 -0.0878 0.4641 1.0000
12.750 1.6985 0.02283 0.01872 -0.0844 0.4567 1.0000
13.000 1.6990 0.02426 0.02019 -0.0822 0.4492 1.0000
13.250 1.6897 0.02651 0.02250 -0.0795 0.4397 1.0000
13.500 1.6773 0.02917 0.02521 -0.0767 0.4290 1.0000
13.750 1.6668 0.03179 0.02785 -0.0742 0.4175 1.0000
14.000 1.6528 0.03482 0.03087 -0.0717 0.4037 1.0000
14.250 1.6361 0.03817 0.03420 -0.0692 0.3879 1.0000
14.500 1.6207 0.04154 0.03753 -0.0669 0.3720 1.0000
14.750 1.6007 0.04538 0.04129 -0.0644 0.3530 1.0000
15.000 1.5825 0.04919 0.04501 -0.0623 0.3353 1.0000
15.250 1.5660 0.05298 0.04874 -0.0604 0.3167 1.0000
15.500 1.5506 0.05678 0.05246 -0.0588 0.2979 1.0000
15.750 1.5336 0.06085 0.05645 -0.0573 0.2802 1.0000
16.000 1.5188 0.06480 0.06032 -0.0559 0.2630 1.0000
16.250 1.5101 0.06820 0.06367 -0.0550 0.2480 1.0000
16.500 1.4963 0.07227 0.06765 -0.0540 0.2298 1.0000
16.750 1.4875 0.07585 0.07117 -0.0533 0.2137 1.0000
17.000 1.4778 0.07961 0.07487 -0.0527 0.1974 1.0000
17.250 1.4682 0.08344 0.07863 -0.0522 0.1809 1.0000
17.500 1.4609 0.08708 0.08220 -0.0519 0.1661 1.0000
17.750 1.4555 0.09055 0.08562 -0.0518 0.1532 1.0000
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