RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Reynolds number: 200,000 Max Cl/Cd: 54.17 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1046-il-200000-n5.txt Download as CSV file: xf-r1046-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0378 0.09944 0.09371 -0.1095 0.6317 0.0185
-10.750 0.0393 0.09570 0.08998 -0.1110 0.6301 0.0179
-10.250 0.0298 0.08558 0.07991 -0.1151 0.6275 0.0167
-10.000 0.0398 0.08421 0.07853 -0.1158 0.6256 0.0175
-9.750 0.0393 0.08053 0.07485 -0.1174 0.6241 0.0177
-9.500 0.0412 0.07748 0.07180 -0.1188 0.6227 0.0182
-9.000 -0.0459 0.05184 0.04627 -0.1341 0.6215 0.0167
-8.750 -0.0841 0.04588 0.04015 -0.1361 0.6201 0.0166
-8.500 -0.1095 0.04181 0.03583 -0.1345 0.6186 0.0166
-8.250 -0.1258 0.03762 0.03125 -0.1325 0.6170 0.0166
-8.000 -0.1313 0.03401 0.02717 -0.1304 0.6154 0.0167
-7.750 -0.1279 0.03105 0.02370 -0.1284 0.6138 0.0168
-7.500 -0.1131 0.02955 0.02201 -0.1273 0.6121 0.0171
-7.250 -0.0960 0.02828 0.02055 -0.1264 0.6105 0.0174
-7.000 -0.0779 0.02700 0.01903 -0.1255 0.6090 0.0177
-6.750 -0.0583 0.02579 0.01758 -0.1247 0.6076 0.0182
-6.500 -0.0377 0.02460 0.01612 -0.1239 0.6063 0.0187
-6.250 -0.0159 0.02348 0.01471 -0.1231 0.6051 0.0194
-6.000 0.0066 0.02251 0.01350 -0.1224 0.6037 0.0202
-5.750 0.0297 0.02201 0.01301 -0.1220 0.6020 0.0211
-5.500 0.0533 0.02150 0.01240 -0.1215 0.6002 0.0225
-5.250 0.0769 0.02084 0.01160 -0.1209 0.5984 0.0238
-5.000 0.1005 0.02032 0.01108 -0.1204 0.5968 0.0249
-4.750 0.1244 0.01983 0.01051 -0.1199 0.5954 0.0263
-4.500 0.1483 0.01934 0.00994 -0.1194 0.5940 0.0281
-4.250 0.1728 0.01900 0.00957 -0.1190 0.5927 0.0306
-4.000 0.1974 0.01866 0.00918 -0.1186 0.5915 0.0335
-3.750 0.2224 0.01836 0.00880 -0.1183 0.5903 0.0371
-3.500 0.2475 0.01808 0.00850 -0.1180 0.5892 0.0415
-3.250 0.2732 0.01786 0.00823 -0.1178 0.5882 0.0475
-3.000 0.2974 0.01767 0.00806 -0.1173 0.5868 0.0558
-2.750 0.3213 0.01748 0.00792 -0.1169 0.5852 0.0671
-2.500 0.3453 0.01728 0.00779 -0.1164 0.5835 0.0848
-2.250 0.3694 0.01709 0.00770 -0.1160 0.5820 0.1133
-2.000 0.3932 0.01686 0.00765 -0.1156 0.5807 0.1594
-1.750 0.4166 0.01658 0.00762 -0.1152 0.5794 0.2337
-1.500 0.4391 0.01625 0.00762 -0.1146 0.5781 0.3338
-1.250 0.4602 0.01588 0.00770 -0.1137 0.5769 0.4641
-1.000 0.4822 0.01567 0.00778 -0.1127 0.5758 0.5676
-0.750 0.5056 0.01555 0.00784 -0.1119 0.5747 0.6395
-0.500 0.5296 0.01546 0.00790 -0.1110 0.5736 0.7035
-0.250 0.5547 0.01539 0.00798 -0.1103 0.5725 0.7722
0.000 0.5880 0.01542 0.00815 -0.1110 0.5714 0.8548
0.250 0.6349 0.01566 0.00844 -0.1149 0.5700 0.9171
0.500 0.6733 0.01592 0.00866 -0.1173 0.5686 0.9476
0.750 0.7111 0.01618 0.00887 -0.1197 0.5672 0.9692
1.000 0.7559 0.01642 0.00906 -0.1236 0.5658 0.9845
1.250 0.8026 0.01663 0.00920 -0.1280 0.5644 0.9961
1.500 0.8321 0.01682 0.00934 -0.1290 0.5630 1.0000
1.750 0.8510 0.01701 0.00948 -0.1276 0.5615 1.0000
2.000 0.8711 0.01719 0.00962 -0.1265 0.5603 1.0000
2.250 0.8919 0.01739 0.00976 -0.1255 0.5592 1.0000
2.500 0.9136 0.01759 0.00991 -0.1247 0.5582 1.0000
2.750 0.9362 0.01779 0.01006 -0.1240 0.5572 1.0000
3.000 0.9597 0.01800 0.01021 -0.1235 0.5563 1.0000
3.250 0.9824 0.01824 0.01042 -0.1229 0.5553 1.0000
3.500 0.9920 0.01873 0.01099 -0.1200 0.5533 1.0000
3.750 1.0040 0.01919 0.01150 -0.1176 0.5512 1.0000
4.000 1.0187 0.01962 0.01196 -0.1156 0.5494 1.0000
4.250 1.0349 0.02002 0.01239 -0.1140 0.5478 1.0000
4.500 1.0527 0.02039 0.01277 -0.1126 0.5463 1.0000
4.750 1.0723 0.02070 0.01308 -0.1116 0.5449 1.0000
5.000 1.0940 0.02094 0.01332 -0.1109 0.5436 1.0000
5.250 1.1176 0.02115 0.01352 -0.1105 0.5424 1.0000
5.500 1.1427 0.02135 0.01371 -0.1104 0.5414 1.0000
5.750 1.1689 0.02158 0.01394 -0.1104 0.5405 1.0000
6.000 1.1878 0.02199 0.01438 -0.1094 0.5392 1.0000
6.250 1.1482 0.02374 0.01634 -0.0990 0.5342 1.0000
6.500 1.1400 0.02484 0.01751 -0.0939 0.5311 1.0000
6.750 1.1504 0.02549 0.01819 -0.0918 0.5291 1.0000
7.000 1.1717 0.02576 0.01848 -0.0912 0.5277 1.0000
7.250 1.1965 0.02593 0.01866 -0.0911 0.5265 1.0000
7.500 1.2249 0.02597 0.01872 -0.0916 0.5256 1.0000
7.750 1.2583 0.02587 0.01863 -0.0926 0.5247 1.0000
11.250 1.1359 0.06061 0.05422 -0.0581 0.4358 1.0000
12.250 1.1692 0.06678 0.06064 -0.0558 0.4117 1.0000
12.500 1.1967 0.06622 0.06014 -0.0558 0.4101 1.0000
12.750 1.2274 0.06526 0.05924 -0.0559 0.4087 1.0000
13.250 1.2234 0.07086 0.06499 -0.0544 0.3891 1.0000
13.500 1.2410 0.07144 0.06562 -0.0542 0.3831 1.0000
13.750 1.2763 0.06989 0.06412 -0.0544 0.3802 1.0000
14.000 1.2755 0.07265 0.06695 -0.0538 0.3690 1.0000
14.250 1.2976 0.07265 0.06698 -0.0537 0.3610 1.0000
14.500 1.3228 0.07226 0.06660 -0.0537 0.3521 1.0000
14.750 1.3367 0.07324 0.06761 -0.0534 0.3408 1.0000
15.000 1.3574 0.07337 0.06772 -0.0532 0.3291 1.0000
15.250 1.3751 0.07382 0.06815 -0.0529 0.3166 1.0000
15.500 1.3860 0.07507 0.06936 -0.0526 0.3014 1.0000
15.750 1.3955 0.07647 0.07070 -0.0522 0.2861 1.0000
16.000 1.4011 0.07836 0.07253 -0.0517 0.2712 1.0000
16.250 1.4031 0.08075 0.07487 -0.0513 0.2559 1.0000
16.500 1.4026 0.08348 0.07755 -0.0510 0.2405 1.0000
16.750 1.4017 0.08631 0.08035 -0.0507 0.2258 1.0000
17.000 1.3996 0.08934 0.08333 -0.0505 0.2115 1.0000
17.250 1.3967 0.09251 0.08646 -0.0504 0.1975 1.0000
17.500 1.3943 0.09568 0.08960 -0.0503 0.1845 1.0000
17.750 1.3912 0.09899 0.09289 -0.0504 0.1720 1.0000
18.000 1.3883 0.10231 0.09618 -0.0505 0.1603 1.0000
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Polar data table (+)
Polar graphs
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