RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.01 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil1-il-1000000.txt Download as CSV file: xf-amsoil1-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN 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
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1743 0.04854 0.04568 -0.0566 1.0000 0.0198
-15.250 -1.1924 0.04287 0.03981 -0.0601 1.0000 0.0199
-15.000 -1.2018 0.03909 0.03586 -0.0614 1.0000 0.0200
-14.750 -1.2058 0.03630 0.03292 -0.0615 1.0000 0.0201
-14.500 -1.2068 0.03409 0.03056 -0.0608 1.0000 0.0203
-14.250 -1.2045 0.03238 0.02871 -0.0595 1.0000 0.0204
-14.000 -1.1986 0.03104 0.02724 -0.0578 1.0000 0.0205
-13.750 -1.1915 0.02929 0.02532 -0.0565 1.0000 0.0207
-13.500 -1.1858 0.02717 0.02304 -0.0551 1.0000 0.0211
-13.250 -1.1692 0.02612 0.02193 -0.0544 1.0000 0.0214
-13.000 -1.1497 0.02534 0.02111 -0.0538 1.0000 0.0216
-12.750 -1.1289 0.02463 0.02035 -0.0534 1.0000 0.0219
-12.500 -1.1076 0.02392 0.01959 -0.0530 1.0000 0.0222
-12.250 -1.0858 0.02318 0.01878 -0.0527 1.0000 0.0226
-12.000 -1.0636 0.02243 0.01793 -0.0524 1.0000 0.0230
-11.750 -1.0407 0.02169 0.01711 -0.0522 1.0000 0.0233
-11.500 -1.0128 0.02107 0.01639 -0.0529 0.9885 0.0237
-11.250 -0.9841 0.02059 0.01581 -0.0535 0.9748 0.0240
-11.000 -0.9657 0.01922 0.01430 -0.0526 0.9597 0.0246
-10.750 -0.9446 0.01866 0.01368 -0.0517 0.9475 0.0250
-10.500 -0.9220 0.01823 0.01319 -0.0509 0.9376 0.0254
-10.250 -0.8989 0.01781 0.01271 -0.0501 0.9286 0.0258
-10.000 -0.8744 0.01737 0.01219 -0.0497 0.9211 0.0262
-9.750 -0.8501 0.01692 0.01165 -0.0492 0.9136 0.0267
-9.500 -0.8250 0.01648 0.01112 -0.0489 0.9070 0.0272
-9.250 -0.7992 0.01613 0.01068 -0.0486 0.9002 0.0276
-9.000 -0.7749 0.01552 0.00996 -0.0481 0.8939 0.0281
-8.750 -0.7499 0.01482 0.00923 -0.0479 0.8883 0.0288
-8.500 -0.7237 0.01444 0.00882 -0.0477 0.8823 0.0293
-8.250 -0.6975 0.01411 0.00844 -0.0474 0.8766 0.0299
-8.000 -0.6705 0.01376 0.00804 -0.0474 0.8714 0.0305
-7.750 -0.6434 0.01343 0.00766 -0.0473 0.8660 0.0311
-7.500 -0.6163 0.01319 0.00734 -0.0471 0.8608 0.0317
-7.250 -0.5897 0.01271 0.00680 -0.0470 0.8558 0.0324
-7.000 -0.5631 0.01218 0.00627 -0.0469 0.8508 0.0332
-6.750 -0.5357 0.01189 0.00595 -0.0468 0.8458 0.0339
-6.500 -0.5083 0.01164 0.00565 -0.0467 0.8409 0.0347
-6.250 -0.4803 0.01137 0.00536 -0.0468 0.8364 0.0356
-6.000 -0.4520 0.01116 0.00512 -0.0468 0.8316 0.0364
-5.750 -0.4248 0.01076 0.00468 -0.0468 0.8267 0.0374
-5.500 -0.3972 0.01049 0.00438 -0.0467 0.8218 0.0385
-5.250 -0.3687 0.01025 0.00415 -0.0468 0.8176 0.0396
-5.000 -0.3403 0.01005 0.00393 -0.0469 0.8129 0.0408
-4.750 -0.3118 0.00989 0.00373 -0.0470 0.8082 0.0417
-4.500 -0.2839 0.00959 0.00342 -0.0470 0.8035 0.0438
-4.250 -0.2551 0.00941 0.00325 -0.0471 0.7993 0.0455
-4.000 -0.2263 0.00925 0.00308 -0.0473 0.7949 0.0472
-3.750 -0.1978 0.00903 0.00285 -0.0474 0.7906 0.0498
-3.500 -0.1691 0.00891 0.00272 -0.0475 0.7860 0.0525
-3.250 -0.1401 0.00872 0.00256 -0.0477 0.7820 0.0563
-3.000 -0.1111 0.00859 0.00245 -0.0478 0.7775 0.0604
-2.750 -0.0822 0.00843 0.00231 -0.0480 0.7731 0.0658
-2.500 -0.0534 0.00834 0.00220 -0.0481 0.7686 0.0712
-2.250 -0.0242 0.00821 0.00212 -0.0483 0.7647 0.0777
-2.000 0.0050 0.00807 0.00202 -0.0486 0.7601 0.0853
-1.750 0.0341 0.00796 0.00194 -0.0487 0.7553 0.0929
-1.500 0.0631 0.00790 0.00187 -0.0489 0.7503 0.1018
-1.250 0.0924 0.00776 0.00181 -0.0492 0.7462 0.1154
-1.000 0.1217 0.00761 0.00175 -0.0494 0.7418 0.1352
-0.750 0.1508 0.00747 0.00170 -0.0497 0.7375 0.1623
-0.500 0.1797 0.00728 0.00165 -0.0499 0.7328 0.2121
-0.250 0.2071 0.00621 0.00153 -0.0506 0.7287 0.5034
0.000 0.2348 0.00562 0.00154 -0.0507 0.7236 0.6903
0.250 0.2630 0.00552 0.00155 -0.0506 0.7138 0.7450
0.500 0.2916 0.00545 0.00155 -0.0506 0.7023 0.7739
0.750 0.3203 0.00544 0.00157 -0.0505 0.6923 0.7959
1.000 0.3490 0.00544 0.00158 -0.0505 0.6822 0.8122
1.250 0.3777 0.00545 0.00161 -0.0505 0.6715 0.8280
1.500 0.4063 0.00548 0.00163 -0.0505 0.6587 0.8414
2.000 0.4624 0.00556 0.00171 -0.0502 0.6314 0.8692
2.250 0.4905 0.00562 0.00175 -0.0500 0.6159 0.8808
2.500 0.5176 0.00573 0.00181 -0.0497 0.5924 0.8950
2.750 0.5437 0.00589 0.00188 -0.0492 0.5606 0.9089
3.000 0.5692 0.00612 0.00199 -0.0486 0.5146 0.9187
3.250 0.5931 0.00672 0.00220 -0.0481 0.4247 0.9277
3.500 0.6131 0.00763 0.00258 -0.0469 0.2992 0.9382
3.750 0.6340 0.00833 0.00291 -0.0458 0.2117 0.9499
4.000 0.6570 0.00874 0.00313 -0.0449 0.1684 0.9633
4.250 0.6838 0.00906 0.00331 -0.0448 0.1397 0.9775
4.500 0.7155 0.00936 0.00351 -0.0458 0.1195 0.9910
4.750 0.7462 0.00965 0.00370 -0.0466 0.1049 1.0000
5.000 0.7737 0.00992 0.00390 -0.0468 0.0943 1.0000
5.250 0.8011 0.01019 0.00411 -0.0468 0.0858 1.0000
5.500 0.8280 0.01049 0.00435 -0.0468 0.0782 1.0000
5.750 0.8552 0.01073 0.00456 -0.0469 0.0730 1.0000
6.000 0.8818 0.01102 0.00481 -0.0468 0.0675 1.0000
6.250 0.9082 0.01132 0.00506 -0.0467 0.0625 1.0000
6.500 0.9346 0.01161 0.00533 -0.0465 0.0586 1.0000
6.750 0.9605 0.01193 0.00562 -0.0463 0.0550 1.0000
7.000 0.9862 0.01225 0.00593 -0.0461 0.0522 1.0000
7.250 1.0120 0.01254 0.00621 -0.0458 0.0498 1.0000
7.500 1.0362 0.01298 0.00661 -0.0454 0.0470 1.0000
7.750 1.0619 0.01326 0.00690 -0.0451 0.0457 1.0000
8.000 1.0869 0.01358 0.00723 -0.0448 0.0442 1.0000
8.250 1.1110 0.01396 0.00760 -0.0443 0.0426 1.0000
8.500 1.1334 0.01449 0.00813 -0.0436 0.0409 1.0000
8.750 1.1579 0.01480 0.00846 -0.0432 0.0401 1.0000
9.000 1.1816 0.01516 0.00884 -0.0426 0.0390 1.0000
9.250 1.2047 0.01556 0.00924 -0.0420 0.0380 1.0000
9.500 1.2264 0.01603 0.00972 -0.0412 0.0370 1.0000
9.750 1.2449 0.01675 0.01045 -0.0400 0.0358 1.0000
10.000 1.2675 0.01710 0.01083 -0.0393 0.0352 1.0000
10.250 1.2887 0.01753 0.01129 -0.0384 0.0345 1.0000
10.500 1.3087 0.01800 0.01179 -0.0374 0.0338 1.0000
10.750 1.3267 0.01847 0.01229 -0.0360 0.0331 1.0000
11.000 1.3430 0.01904 0.01288 -0.0344 0.0323 1.0000
11.250 1.3556 0.01989 0.01374 -0.0324 0.0315 1.0000
11.500 1.3701 0.02066 0.01456 -0.0308 0.0309 1.0000
11.750 1.3877 0.02124 0.01520 -0.0297 0.0305 1.0000
12.000 1.4042 0.02190 0.01591 -0.0284 0.0300 1.0000
12.250 1.4203 0.02261 0.01667 -0.0273 0.0294 1.0000
12.500 1.4359 0.02336 0.01746 -0.0261 0.0289 1.0000
12.750 1.4509 0.02418 0.01831 -0.0249 0.0284 1.0000
13.000 1.4646 0.02510 0.01926 -0.0237 0.0279 1.0000
13.250 1.4738 0.02639 0.02058 -0.0221 0.0273 1.0000
13.500 1.4834 0.02769 0.02195 -0.0207 0.0268 1.0000
13.750 1.4981 0.02858 0.02291 -0.0197 0.0265 1.0000
14.000 1.5116 0.02958 0.02397 -0.0188 0.0261 1.0000
14.250 1.5239 0.03069 0.02515 -0.0178 0.0257 1.0000
14.500 1.5355 0.03188 0.02640 -0.0168 0.0253 1.0000
14.750 1.5465 0.03313 0.02771 -0.0158 0.0249 1.0000
15.000 1.5568 0.03445 0.02908 -0.0149 0.0245 1.0000
15.250 1.5655 0.03595 0.03062 -0.0140 0.0241 1.0000
15.500 1.5713 0.03773 0.03246 -0.0130 0.0238 1.0000
15.750 1.5710 0.04009 0.03489 -0.0119 0.0234 1.0000
16.000 1.5728 0.04234 0.03723 -0.0109 0.0231 1.0000
16.250 1.5803 0.04408 0.03907 -0.0104 0.0229 1.0000
16.500 1.5859 0.04603 0.04111 -0.0098 0.0226 1.0000
16.750 1.5902 0.04819 0.04336 -0.0094 0.0224 1.0000
17.000 1.5939 0.05049 0.04575 -0.0091 0.0221 1.0000
17.250 1.5969 0.05292 0.04828 -0.0089 0.0218 1.0000
17.500 1.5989 0.05554 0.05097 -0.0089 0.0216 1.0000
17.750 1.6008 0.05824 0.05376 -0.0091 0.0213 1.0000
18.000 1.6010 0.06124 0.05683 -0.0094 0.0210 1.0000
18.250 1.6002 0.06446 0.06014 -0.0099 0.0208 1.0000
18.500 1.5966 0.06811 0.06387 -0.0106 0.0206 1.0000
18.750 1.5896 0.07233 0.06818 -0.0116 0.0204 1.0000
19.000 1.5793 0.07713 0.07308 -0.0130 0.0202 1.0000
19.250 1.5644 0.08275 0.07881 -0.0148 0.0200 1.0000
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