RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 200,000 Max Cl/Cd: 59.89 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil1-il-200000-n5.txt Download as CSV file: xf-amsoil1-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5649 0.08908 0.08512 -0.0305 1.0000 0.0315
-10.250 -0.6859 0.05692 0.05277 -0.0559 1.0000 0.0314
-10.000 -0.7879 0.03812 0.03255 -0.0563 1.0000 0.0321
-9.750 -0.7712 0.03715 0.03156 -0.0559 0.9964 0.0325
-9.500 -0.7449 0.03601 0.03035 -0.0572 0.9858 0.0331
-9.250 -0.7212 0.03423 0.02836 -0.0584 0.9762 0.0338
-9.000 -0.7001 0.03166 0.02541 -0.0593 0.9671 0.0348
-8.750 -0.6796 0.02875 0.02198 -0.0598 0.9587 0.0358
-8.500 -0.6583 0.02655 0.01930 -0.0597 0.9500 0.0367
-8.250 -0.6321 0.02575 0.01847 -0.0600 0.9433 0.0374
-8.000 -0.6078 0.02504 0.01769 -0.0598 0.9350 0.0382
-7.750 -0.5832 0.02415 0.01664 -0.0596 0.9283 0.0393
-7.500 -0.5594 0.02307 0.01533 -0.0592 0.9212 0.0404
-7.250 -0.5353 0.02197 0.01397 -0.0587 0.9145 0.0414
-7.000 -0.5108 0.02113 0.01303 -0.0582 0.9085 0.0423
-6.750 -0.4857 0.02059 0.01247 -0.0579 0.9017 0.0433
-6.500 -0.4606 0.02005 0.01186 -0.0575 0.8961 0.0446
-6.250 -0.4352 0.01941 0.01109 -0.0571 0.8906 0.0461
-6.000 -0.4094 0.01873 0.01025 -0.0567 0.8843 0.0474
-5.750 -0.3842 0.01814 0.00967 -0.0562 0.8789 0.0486
-5.500 -0.3584 0.01772 0.00922 -0.0559 0.8741 0.0501
-5.250 -0.3319 0.01727 0.00873 -0.0557 0.8682 0.0521
-5.000 -0.3057 0.01681 0.00816 -0.0553 0.8629 0.0541
-4.750 -0.2801 0.01636 0.00773 -0.0549 0.8584 0.0558
-4.500 -0.2532 0.01598 0.00735 -0.0548 0.8530 0.0581
-4.250 -0.2263 0.01563 0.00693 -0.0546 0.8477 0.0611
-4.000 -0.2001 0.01526 0.00660 -0.0543 0.8429 0.0640
-3.750 -0.1733 0.01495 0.00626 -0.0540 0.8386 0.0675
-3.500 -0.1461 0.01462 0.00595 -0.0540 0.8330 0.0713
-3.250 -0.1189 0.01436 0.00569 -0.0538 0.8279 0.0763
-3.000 -0.0920 0.01408 0.00542 -0.0536 0.8236 0.0817
-2.750 -0.0645 0.01385 0.00519 -0.0535 0.8190 0.0880
-2.500 -0.0369 0.01361 0.00500 -0.0535 0.8137 0.0954
-2.250 -0.0094 0.01339 0.00481 -0.0534 0.8088 0.1041
-2.000 0.0181 0.01320 0.00462 -0.0533 0.8048 0.1150
-1.750 0.0460 0.01299 0.00449 -0.0533 0.8002 0.1290
-1.500 0.0739 0.01279 0.00438 -0.0534 0.7951 0.1478
-1.250 0.1015 0.01253 0.00425 -0.0534 0.7905 0.1765
-1.000 0.1286 0.01218 0.00410 -0.0533 0.7866 0.2319
-0.750 0.1487 0.01065 0.00409 -0.0526 0.7817 0.6117
-0.500 0.1724 0.01043 0.00426 -0.0512 0.7766 0.7265
-0.250 0.1974 0.01039 0.00433 -0.0501 0.7719 0.7765
0.000 0.2228 0.01039 0.00436 -0.0489 0.7680 0.8104
0.250 0.2484 0.01043 0.00446 -0.0481 0.7622 0.8373
0.500 0.2734 0.01045 0.00453 -0.0471 0.7570 0.8603
0.750 0.2982 0.01046 0.00455 -0.0458 0.7526 0.8811
1.000 0.3231 0.01049 0.00460 -0.0447 0.7482 0.9010
1.250 0.3484 0.01053 0.00469 -0.0437 0.7426 0.9228
1.500 0.3763 0.01052 0.00469 -0.0431 0.7366 0.9436
1.750 0.4077 0.01045 0.00459 -0.0435 0.7240 0.9560
2.000 0.4402 0.01035 0.00444 -0.0441 0.7076 0.9630
2.250 0.4722 0.01030 0.00434 -0.0448 0.6929 0.9712
2.500 0.5065 0.01028 0.00427 -0.0460 0.6762 0.9779
2.750 0.5401 0.01027 0.00420 -0.0470 0.6543 0.9855
3.000 0.5737 0.01030 0.00413 -0.0481 0.6288 0.9935
3.250 0.6052 0.01037 0.00413 -0.0489 0.5984 1.0000
3.500 0.6273 0.01052 0.00413 -0.0478 0.5634 1.0000
3.750 0.6486 0.01083 0.00417 -0.0466 0.5039 1.0000
4.000 0.6648 0.01172 0.00442 -0.0447 0.3858 1.0000
4.250 0.6788 0.01302 0.00501 -0.0430 0.2587 1.0000
4.500 0.6981 0.01390 0.00553 -0.0420 0.1942 1.0000
4.750 0.7201 0.01453 0.00595 -0.0413 0.1609 1.0000
5.000 0.7429 0.01506 0.00635 -0.0408 0.1394 1.0000
5.250 0.7662 0.01555 0.00674 -0.0402 0.1237 1.0000
5.500 0.7893 0.01604 0.00717 -0.0396 0.1118 1.0000
5.750 0.8125 0.01653 0.00759 -0.0391 0.1022 1.0000
6.000 0.8357 0.01700 0.00804 -0.0385 0.0947 1.0000
6.250 0.8579 0.01754 0.00853 -0.0378 0.0883 1.0000
6.500 0.8808 0.01801 0.00901 -0.0371 0.0825 1.0000
6.750 0.9022 0.01860 0.00954 -0.0363 0.0778 1.0000
7.000 0.9243 0.01911 0.01010 -0.0356 0.0736 1.0000
7.250 0.9452 0.01971 0.01066 -0.0347 0.0700 1.0000
7.500 0.9660 0.02031 0.01128 -0.0338 0.0667 1.0000
7.750 0.9867 0.02090 0.01189 -0.0329 0.0637 1.0000
8.000 1.0058 0.02159 0.01255 -0.0318 0.0613 1.0000
8.250 1.0251 0.02227 0.01327 -0.0307 0.0592 1.0000
8.500 1.0444 0.02293 0.01398 -0.0296 0.0570 1.0000
8.750 1.0623 0.02361 0.01467 -0.0284 0.0550 1.0000
9.000 1.0777 0.02442 0.01545 -0.0268 0.0535 1.0000
9.250 1.0952 0.02517 0.01629 -0.0255 0.0520 1.0000
9.500 1.1123 0.02597 0.01716 -0.0242 0.0505 1.0000
9.750 1.1291 0.02679 0.01801 -0.0230 0.0491 1.0000
10.000 1.1452 0.02764 0.01888 -0.0218 0.0479 1.0000
10.250 1.1604 0.02863 0.01987 -0.0206 0.0468 1.0000
10.500 1.1773 0.02956 0.02092 -0.0194 0.0456 1.0000
10.750 1.1934 0.03056 0.02201 -0.0183 0.0444 1.0000
11.000 1.2088 0.03158 0.02310 -0.0171 0.0434 1.0000
11.250 1.2234 0.03261 0.02419 -0.0160 0.0425 1.0000
11.500 1.2372 0.03370 0.02530 -0.0149 0.0416 1.0000
11.750 1.2508 0.03493 0.02657 -0.0138 0.0408 1.0000
12.000 1.2642 0.03620 0.02802 -0.0126 0.0399 1.0000
12.250 1.2766 0.03755 0.02952 -0.0115 0.0390 1.0000
12.500 1.2882 0.03895 0.03103 -0.0104 0.0383 1.0000
12.750 1.2987 0.04037 0.03255 -0.0093 0.0375 1.0000
13.000 1.3084 0.04182 0.03407 -0.0082 0.0369 1.0000
13.250 1.3176 0.04332 0.03562 -0.0073 0.0363 1.0000
13.500 1.3264 0.04498 0.03731 -0.0063 0.0358 1.0000
13.750 1.3307 0.04711 0.03969 -0.0052 0.0351 1.0000
14.000 1.3340 0.04937 0.04218 -0.0042 0.0345 1.0000
14.250 1.3360 0.05177 0.04478 -0.0034 0.0340 1.0000
14.500 1.3367 0.05431 0.04750 -0.0027 0.0335 1.0000
14.750 1.3364 0.05698 0.05033 -0.0022 0.0330 1.0000
15.000 1.3354 0.05974 0.05323 -0.0019 0.0326 1.0000
15.250 1.3341 0.06259 0.05621 -0.0018 0.0322 1.0000
15.500 1.3325 0.06552 0.05923 -0.0018 0.0319 1.0000
15.750 1.3305 0.06856 0.06237 -0.0021 0.0315 1.0000
16.000 1.3280 0.07179 0.06567 -0.0025 0.0312 1.0000
16.250 1.3158 0.07658 0.07068 -0.0036 0.0310 1.0000
16.500 1.2964 0.08276 0.07716 -0.0058 0.0307 1.0000
16.750 1.2739 0.08993 0.08462 -0.0090 0.0305 1.0000
17.000 1.2463 0.09861 0.09358 -0.0135 0.0304 1.0000
17.250 1.2100 0.10983 0.10512 -0.0202 0.0304 1.0000
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