RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 500,000 Max Cl/Cd: 86.18 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil1-il-500000.txt Download as CSV file: xf-amsoil1-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5208 0.13101 0.12851 -0.0053 1.0000 0.0341
-11.750 -0.5182 0.12685 0.12435 -0.0074 1.0000 0.0353
-10.250 -0.8329 0.03333 0.02922 -0.0557 0.9999 0.0310
-10.000 -0.8176 0.02895 0.02417 -0.0572 0.9893 0.0317
-9.750 -0.7952 0.02604 0.02089 -0.0584 0.9815 0.0324
-9.500 -0.7672 0.02514 0.01996 -0.0593 0.9735 0.0330
-9.250 -0.7414 0.02454 0.01932 -0.0594 0.9644 0.0337
-9.000 -0.7185 0.02377 0.01844 -0.0589 0.9556 0.0344
-8.750 -0.6984 0.02263 0.01709 -0.0579 0.9462 0.0352
-8.500 -0.6776 0.02150 0.01572 -0.0569 0.9378 0.0359
-8.250 -0.6557 0.02068 0.01465 -0.0559 0.9300 0.0365
-8.000 -0.6338 0.01929 0.01314 -0.0552 0.9232 0.0373
-7.750 -0.6094 0.01875 0.01259 -0.0547 0.9164 0.0381
-7.500 -0.5854 0.01827 0.01202 -0.0540 0.9105 0.0390
-7.250 -0.5596 0.01764 0.01130 -0.0538 0.9040 0.0399
-7.000 -0.5343 0.01702 0.01056 -0.0533 0.8981 0.0408
-6.750 -0.5089 0.01653 0.00992 -0.0528 0.8929 0.0416
-6.500 -0.4832 0.01560 0.00896 -0.0526 0.8872 0.0427
-6.250 -0.4569 0.01518 0.00854 -0.0523 0.8816 0.0438
-6.000 -0.4308 0.01481 0.00810 -0.0519 0.8766 0.0450
-5.750 -0.4036 0.01438 0.00762 -0.0518 0.8716 0.0462
-5.500 -0.3763 0.01401 0.00718 -0.0517 0.8662 0.0473
-5.250 -0.3505 0.01336 0.00652 -0.0513 0.8613 0.0488
-5.000 -0.3235 0.01307 0.00623 -0.0511 0.8567 0.0504
-4.750 -0.2956 0.01277 0.00592 -0.0511 0.8515 0.0522
-4.500 -0.2679 0.01250 0.00559 -0.0510 0.8465 0.0538
-4.250 -0.2415 0.01201 0.00510 -0.0508 0.8420 0.0560
-4.000 -0.2136 0.01179 0.00489 -0.0507 0.8374 0.0585
-3.750 -0.1852 0.01160 0.00467 -0.0508 0.8324 0.0612
-3.500 -0.1579 0.01120 0.00431 -0.0507 0.8276 0.0649
-3.250 -0.1299 0.01104 0.00411 -0.0506 0.8233 0.0688
-3.000 -0.1019 0.01075 0.00387 -0.0507 0.8190 0.0740
-2.750 -0.0732 0.01056 0.00369 -0.0508 0.8142 0.0800
-2.500 -0.0450 0.01035 0.00351 -0.0508 0.8096 0.0872
-2.250 -0.0169 0.01015 0.00333 -0.0508 0.8054 0.0954
-2.000 0.0118 0.01000 0.00321 -0.0510 0.8009 0.1047
-1.750 0.0407 0.00984 0.00310 -0.0511 0.7962 0.1159
-1.500 0.0692 0.00964 0.00297 -0.0512 0.7916 0.1318
-1.250 0.0975 0.00944 0.00285 -0.0513 0.7873 0.1573
-1.000 0.1260 0.00915 0.00277 -0.0516 0.7826 0.2088
-0.750 0.1507 0.00766 0.00259 -0.0519 0.7775 0.5757
-0.500 0.1762 0.00724 0.00269 -0.0512 0.7729 0.7309
-0.250 0.2031 0.00720 0.00276 -0.0507 0.7687 0.7810
0.000 0.2307 0.00718 0.00283 -0.0503 0.7642 0.8100
0.250 0.2583 0.00718 0.00288 -0.0499 0.7593 0.8323
0.500 0.2856 0.00719 0.00291 -0.0495 0.7546 0.8505
0.750 0.3122 0.00719 0.00292 -0.0488 0.7472 0.8668
1.000 0.3385 0.00712 0.00284 -0.0480 0.7358 0.8813
1.250 0.3645 0.00710 0.00282 -0.0472 0.7257 0.8961
1.500 0.3898 0.00708 0.00278 -0.0462 0.7164 0.9110
1.750 0.4144 0.00704 0.00279 -0.0451 0.7063 0.9252
2.000 0.4374 0.00702 0.00274 -0.0435 0.6957 0.9408
2.250 0.4603 0.00697 0.00270 -0.0419 0.6831 0.9585
2.500 0.4890 0.00695 0.00268 -0.0418 0.6703 0.9714
2.750 0.5229 0.00697 0.00267 -0.0430 0.6563 0.9782
3.000 0.5575 0.00702 0.00268 -0.0443 0.6382 0.9850
3.250 0.5932 0.00713 0.00268 -0.0460 0.6124 0.9907
3.500 0.6291 0.00730 0.00273 -0.0478 0.5760 0.9958
3.750 0.6610 0.00768 0.00283 -0.0489 0.5110 1.0000
4.000 0.6757 0.00855 0.00313 -0.0470 0.3906 1.0000
4.250 0.6919 0.00986 0.00371 -0.0457 0.2468 1.0000
4.500 0.7140 0.01064 0.00413 -0.0452 0.1803 1.0000
4.750 0.7384 0.01117 0.00446 -0.0449 0.1462 1.0000
5.000 0.7635 0.01162 0.00477 -0.0447 0.1250 1.0000
5.250 0.7889 0.01202 0.00509 -0.0444 0.1109 1.0000
5.500 0.8139 0.01245 0.00543 -0.0441 0.1000 1.0000
5.750 0.8393 0.01281 0.00574 -0.0438 0.0917 1.0000
6.000 0.8645 0.01320 0.00610 -0.0435 0.0846 1.0000
6.250 0.8883 0.01370 0.00653 -0.0430 0.0781 1.0000
6.500 0.9136 0.01403 0.00687 -0.0427 0.0735 1.0000
6.750 0.9363 0.01460 0.00738 -0.0420 0.0688 1.0000
7.000 0.9611 0.01494 0.00774 -0.0416 0.0653 1.0000
7.250 0.9841 0.01544 0.00820 -0.0410 0.0621 1.0000
7.500 1.0062 0.01599 0.00877 -0.0402 0.0596 1.0000
7.750 1.0294 0.01643 0.00922 -0.0396 0.0573 1.0000
8.000 1.0517 0.01692 0.00969 -0.0389 0.0552 1.0000
8.250 1.0706 0.01769 0.01045 -0.0377 0.0532 1.0000
8.500 1.0931 0.01812 0.01094 -0.0370 0.0517 1.0000
8.750 1.1142 0.01865 0.01148 -0.0361 0.0502 1.0000
9.000 1.1346 0.01920 0.01204 -0.0351 0.0489 1.0000
9.250 1.1520 0.01997 0.01280 -0.0337 0.0475 1.0000
9.500 1.1686 0.02073 0.01359 -0.0322 0.0463 1.0000
9.750 1.1867 0.02128 0.01421 -0.0308 0.0453 1.0000
10.000 1.2040 0.02193 0.01491 -0.0295 0.0442 1.0000
10.250 1.2210 0.02261 0.01562 -0.0281 0.0433 1.0000
10.500 1.2374 0.02336 0.01636 -0.0268 0.0423 1.0000
10.750 1.2514 0.02451 0.01749 -0.0253 0.0412 1.0000
11.000 1.2678 0.02533 0.01840 -0.0241 0.0405 1.0000
11.250 1.2842 0.02612 0.01928 -0.0229 0.0397 1.0000
11.500 1.2999 0.02699 0.02022 -0.0217 0.0389 1.0000
11.750 1.3152 0.02788 0.02117 -0.0205 0.0381 1.0000
12.000 1.3299 0.02879 0.02211 -0.0194 0.0374 1.0000
12.250 1.3438 0.02982 0.02315 -0.0182 0.0366 1.0000
12.500 1.3568 0.03136 0.02470 -0.0168 0.0357 1.0000
12.750 1.3694 0.03239 0.02587 -0.0156 0.0353 1.0000
13.000 1.3814 0.03357 0.02716 -0.0144 0.0347 1.0000
13.250 1.3927 0.03483 0.02853 -0.0132 0.0341 1.0000
13.500 1.4033 0.03615 0.02994 -0.0121 0.0335 1.0000
13.750 1.4133 0.03751 0.03138 -0.0110 0.0329 1.0000
14.000 1.4229 0.03891 0.03284 -0.0100 0.0324 1.0000
14.250 1.4321 0.04038 0.03434 -0.0090 0.0320 1.0000
14.500 1.4403 0.04219 0.03617 -0.0079 0.0314 1.0000
14.750 1.4442 0.04435 0.03847 -0.0067 0.0309 1.0000
15.000 1.4470 0.04638 0.04067 -0.0058 0.0305 1.0000
15.250 1.4490 0.04859 0.04305 -0.0050 0.0301 1.0000
15.500 1.4503 0.05097 0.04557 -0.0043 0.0297 1.0000
15.750 1.4505 0.05350 0.04823 -0.0038 0.0293 1.0000
16.000 1.4494 0.05623 0.05110 -0.0034 0.0290 1.0000
16.250 1.4477 0.05908 0.05408 -0.0033 0.0286 1.0000
16.500 1.4459 0.06205 0.05715 -0.0033 0.0283 1.0000
16.750 1.4437 0.06516 0.06036 -0.0035 0.0281 1.0000
17.000 1.4414 0.06841 0.06370 -0.0039 0.0278 1.0000
17.250 1.4385 0.07183 0.06720 -0.0045 0.0276 1.0000
17.500 1.4334 0.07565 0.07111 -0.0052 0.0273 1.0000
17.750 1.4217 0.08048 0.07607 -0.0062 0.0271 1.0000
18.000 1.4030 0.08671 0.08249 -0.0084 0.0269 1.0000
18.250 1.3841 0.09342 0.08942 -0.0116 0.0268 1.0000
18.500 1.3619 0.10107 0.09728 -0.0155 0.0267 1.0000
18.750 1.3353 0.11002 0.10646 -0.0207 0.0267 1.0000
19.000 1.3021 0.12097 0.11766 -0.0275 0.0267 1.0000
19.250 1.2535 0.13619 0.13316 -0.0376 0.0267 1.0000
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