RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.08 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil1-il-1000000-n5.txt Download as CSV file: xf-amsoil1-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.3219 0.05242 0.04935 -0.0541 1.0000 0.0154
-17.000 -1.3528 0.04447 0.04117 -0.0595 1.0000 0.0154
-16.750 -1.3643 0.04025 0.03679 -0.0613 1.0000 0.0155
-16.500 -1.3694 0.03717 0.03359 -0.0619 1.0000 0.0156
-16.250 -1.3707 0.03476 0.03106 -0.0617 1.0000 0.0157
-16.000 -1.3690 0.03281 0.02900 -0.0610 1.0000 0.0159
-15.750 -1.3651 0.03119 0.02728 -0.0598 1.0000 0.0160
-15.500 -1.3597 0.02982 0.02582 -0.0582 1.0000 0.0162
-15.250 -1.3509 0.02865 0.02455 -0.0566 1.0000 0.0164
-15.000 -1.3375 0.02755 0.02335 -0.0556 1.0000 0.0165
-14.750 -1.3222 0.02652 0.02223 -0.0547 1.0000 0.0168
-14.500 -1.3055 0.02555 0.02116 -0.0539 1.0000 0.0170
-14.250 -1.2874 0.02464 0.02016 -0.0532 1.0000 0.0172
-14.000 -1.2682 0.02379 0.01923 -0.0526 1.0000 0.0174
-13.750 -1.2481 0.02300 0.01834 -0.0521 1.0000 0.0175
-13.500 -1.2279 0.02216 0.01742 -0.0515 1.0000 0.0177
-13.250 -1.2062 0.02136 0.01656 -0.0512 0.9920 0.0180
-13.000 -1.1806 0.02067 0.01581 -0.0516 0.9685 0.0183
-12.750 -1.1588 0.02011 0.01517 -0.0509 0.9511 0.0186
-12.500 -1.1375 0.01959 0.01457 -0.0500 0.9379 0.0189
-12.250 -1.1156 0.01911 0.01400 -0.0493 0.9268 0.0192
-12.000 -1.0924 0.01862 0.01344 -0.0487 0.9171 0.0195
-11.750 -1.0691 0.01816 0.01288 -0.0482 0.9088 0.0199
-11.500 -1.0449 0.01769 0.01233 -0.0478 0.9008 0.0202
-11.000 -0.9958 0.01678 0.01124 -0.0470 0.8874 0.0207
-10.750 -0.9714 0.01625 0.01066 -0.0467 0.8808 0.0211
-10.500 -0.9462 0.01583 0.01018 -0.0464 0.8747 0.0215
-10.250 -0.9203 0.01544 0.00974 -0.0462 0.8689 0.0219
-10.000 -0.8943 0.01507 0.00933 -0.0461 0.8632 0.0222
-9.500 -0.8415 0.01441 0.00855 -0.0458 0.8529 0.0232
-9.250 -0.8148 0.01409 0.00817 -0.0457 0.8473 0.0236
-9.000 -0.7881 0.01378 0.00779 -0.0455 0.8420 0.0239
-8.750 -0.7614 0.01341 0.00737 -0.0454 0.8376 0.0243
-8.500 -0.7345 0.01304 0.00698 -0.0454 0.8327 0.0248
-8.250 -0.7074 0.01275 0.00666 -0.0453 0.8274 0.0253
-8.000 -0.6801 0.01249 0.00636 -0.0453 0.8224 0.0259
-7.750 -0.6524 0.01223 0.00607 -0.0453 0.8181 0.0265
-7.500 -0.6247 0.01197 0.00577 -0.0453 0.8133 0.0270
-7.250 -0.5970 0.01172 0.00548 -0.0453 0.8084 0.0275
-7.000 -0.5692 0.01150 0.00520 -0.0453 0.8036 0.0278
-6.750 -0.5415 0.01118 0.00488 -0.0453 0.7992 0.0286
-6.500 -0.5135 0.01094 0.00462 -0.0454 0.7947 0.0293
-6.250 -0.4854 0.01073 0.00439 -0.0454 0.7901 0.0301
-6.000 -0.4573 0.01054 0.00416 -0.0455 0.7856 0.0308
-5.750 -0.4288 0.01034 0.00394 -0.0456 0.7813 0.0315
-5.500 -0.4004 0.01015 0.00373 -0.0457 0.7766 0.0321
-5.250 -0.3721 0.00993 0.00350 -0.0458 0.7720 0.0331
-5.000 -0.3437 0.00976 0.00331 -0.0458 0.7676 0.0342
-4.750 -0.3150 0.00959 0.00314 -0.0460 0.7636 0.0354
-4.500 -0.2863 0.00944 0.00297 -0.0461 0.7591 0.0364
-4.250 -0.2576 0.00926 0.00279 -0.0463 0.7546 0.0378
-4.000 -0.2290 0.00912 0.00264 -0.0464 0.7504 0.0395
-3.750 -0.2000 0.00898 0.00251 -0.0466 0.7469 0.0412
-3.500 -0.1710 0.00883 0.00238 -0.0467 0.7429 0.0434
-3.250 -0.1421 0.00871 0.00226 -0.0469 0.7385 0.0464
-3.000 -0.1132 0.00859 0.00214 -0.0471 0.7341 0.0495
-2.750 -0.0841 0.00848 0.00205 -0.0473 0.7302 0.0532
-2.500 -0.0549 0.00836 0.00196 -0.0475 0.7261 0.0572
-2.250 -0.0258 0.00826 0.00187 -0.0477 0.7218 0.0616
-2.000 0.0033 0.00816 0.00179 -0.0479 0.7172 0.0670
-1.750 0.0325 0.00808 0.00172 -0.0481 0.7126 0.0720
-1.500 0.0618 0.00799 0.00166 -0.0483 0.7076 0.0777
-1.250 0.0910 0.00790 0.00161 -0.0485 0.7026 0.0852
-1.000 0.1201 0.00783 0.00155 -0.0487 0.6981 0.0932
-0.500 0.1788 0.00766 0.00148 -0.0492 0.6898 0.1148
-0.250 0.2080 0.00756 0.00145 -0.0495 0.6849 0.1337
0.000 0.2371 0.00746 0.00143 -0.0497 0.6792 0.1627
0.250 0.2660 0.00733 0.00139 -0.0499 0.6637 0.2035
0.500 0.2945 0.00710 0.00135 -0.0502 0.6454 0.2890
0.750 0.3214 0.00607 0.00129 -0.0508 0.6286 0.6216
1.000 0.3498 0.00597 0.00133 -0.0509 0.6110 0.6842
1.250 0.3783 0.00597 0.00138 -0.0509 0.5889 0.7253
1.500 0.4062 0.00609 0.00144 -0.0509 0.5544 0.7511
1.750 0.4337 0.00629 0.00154 -0.0508 0.5125 0.7752
2.000 0.4599 0.00669 0.00171 -0.0506 0.4432 0.7965
2.250 0.4852 0.00726 0.00196 -0.0503 0.3559 0.8123
2.500 0.5089 0.00800 0.00229 -0.0499 0.2475 0.8302
2.750 0.5340 0.00846 0.00253 -0.0495 0.1869 0.8484
3.000 0.5606 0.00875 0.00271 -0.0493 0.1561 0.8594
3.250 0.5876 0.00899 0.00286 -0.0492 0.1339 0.8665
3.500 0.6149 0.00921 0.00301 -0.0491 0.1183 0.8736
3.750 0.6418 0.00941 0.00317 -0.0489 0.1057 0.8807
4.000 0.6687 0.00962 0.00333 -0.0488 0.0952 0.8885
4.250 0.6955 0.00981 0.00350 -0.0486 0.0869 0.8961
4.500 0.7219 0.01000 0.00366 -0.0483 0.0801 0.9049
4.750 0.7483 0.01018 0.00383 -0.0480 0.0747 0.9135
5.000 0.7740 0.01039 0.00402 -0.0476 0.0689 0.9233
5.250 0.7995 0.01056 0.00420 -0.0471 0.0645 0.9337
5.500 0.8244 0.01076 0.00439 -0.0465 0.0604 0.9465
5.750 0.8499 0.01094 0.00457 -0.0460 0.0570 0.9626
6.000 0.8782 0.01117 0.00478 -0.0462 0.0532 0.9819
6.250 0.9073 0.01140 0.00499 -0.0467 0.0499 1.0000
6.500 0.9336 0.01169 0.00524 -0.0465 0.0467 1.0000
6.750 0.9601 0.01194 0.00548 -0.0464 0.0447 1.0000
7.000 0.9861 0.01222 0.00575 -0.0462 0.0425 1.0000
7.250 1.0118 0.01252 0.00603 -0.0460 0.0407 1.0000
7.500 1.0376 0.01280 0.00631 -0.0458 0.0392 1.0000
7.750 1.0629 0.01311 0.00661 -0.0455 0.0376 1.0000
8.000 1.0877 0.01345 0.00693 -0.0451 0.0362 1.0000
8.250 1.1126 0.01377 0.00726 -0.0448 0.0353 1.0000
8.500 1.1373 0.01409 0.00759 -0.0444 0.0344 1.0000
8.750 1.1615 0.01443 0.00793 -0.0439 0.0334 1.0000
9.000 1.1852 0.01480 0.00830 -0.0434 0.0324 1.0000
9.250 1.2081 0.01521 0.00871 -0.0428 0.0314 1.0000
9.500 1.2312 0.01559 0.00911 -0.0422 0.0308 1.0000
9.750 1.2541 0.01596 0.00950 -0.0415 0.0302 1.0000
10.000 1.2765 0.01635 0.00991 -0.0408 0.0295 1.0000
10.250 1.2983 0.01676 0.01034 -0.0401 0.0288 1.0000
10.500 1.3192 0.01721 0.01080 -0.0392 0.0281 1.0000
10.750 1.3388 0.01770 0.01130 -0.0381 0.0274 1.0000
11.000 1.3561 0.01822 0.01184 -0.0366 0.0269 1.0000
11.250 1.3740 0.01868 0.01235 -0.0352 0.0264 1.0000
11.500 1.3916 0.01919 0.01289 -0.0339 0.0259 1.0000
11.750 1.4089 0.01974 0.01348 -0.0326 0.0254 1.0000
12.000 1.4258 0.02034 0.01411 -0.0313 0.0249 1.0000
12.250 1.4423 0.02099 0.01479 -0.0301 0.0244 1.0000
12.500 1.4582 0.02169 0.01551 -0.0289 0.0240 1.0000
12.750 1.4732 0.02247 0.01633 -0.0276 0.0235 1.0000
13.000 1.4876 0.02331 0.01721 -0.0263 0.0231 1.0000
13.250 1.5031 0.02408 0.01803 -0.0252 0.0228 1.0000
13.500 1.5181 0.02490 0.01891 -0.0241 0.0224 1.0000
13.750 1.5324 0.02577 0.01983 -0.0230 0.0220 1.0000
14.000 1.5464 0.02669 0.02080 -0.0220 0.0216 1.0000
14.250 1.5596 0.02768 0.02184 -0.0209 0.0212 1.0000
14.500 1.5722 0.02873 0.02293 -0.0198 0.0208 1.0000
14.750 1.5837 0.02989 0.02413 -0.0188 0.0205 1.0000
15.000 1.5942 0.03116 0.02545 -0.0177 0.0201 1.0000
15.250 1.6032 0.03255 0.02690 -0.0166 0.0198 1.0000
15.500 1.6136 0.03386 0.02828 -0.0156 0.0196 1.0000
15.750 1.6230 0.03526 0.02976 -0.0147 0.0193 1.0000
16.000 1.6317 0.03675 0.03132 -0.0139 0.0191 1.0000
16.250 1.6396 0.03833 0.03297 -0.0130 0.0188 1.0000
16.500 1.6465 0.04003 0.03475 -0.0122 0.0185 1.0000
16.750 1.6527 0.04184 0.03663 -0.0115 0.0183 1.0000
17.000 1.6580 0.04376 0.03862 -0.0109 0.0180 1.0000
17.250 1.6622 0.04581 0.04075 -0.0103 0.0178 1.0000
17.500 1.6654 0.04807 0.04307 -0.0099 0.0176 1.0000
17.750 1.6675 0.05051 0.04559 -0.0096 0.0173 1.0000
18.000 1.6679 0.05323 0.04839 -0.0094 0.0171 1.0000
18.250 1.6658 0.05631 0.05155 -0.0094 0.0168 1.0000
18.500 1.6658 0.05924 0.05458 -0.0096 0.0167 1.0000
18.750 1.6646 0.06240 0.05784 -0.0099 0.0165 1.0000
19.000 1.6621 0.06581 0.06136 -0.0105 0.0164 1.0000
19.250 1.6576 0.06956 0.06522 -0.0112 0.0162 1.0000
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