RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 200,000 Max Cl/Cd: 42.83 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil2-il-200000-n5.txt Download as CSV file: xf-amsoil2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8857 0.06818 0.06367 -0.0390 1.0000 0.0310
-12.750 -0.9380 0.05674 0.05185 -0.0470 1.0000 0.0309
-12.500 -0.9724 0.05006 0.04479 -0.0492 1.0000 0.0310
-12.250 -0.9980 0.04523 0.03956 -0.0486 1.0000 0.0313
-12.000 -1.0166 0.04154 0.03544 -0.0461 1.0000 0.0316
-11.750 -1.0092 0.03988 0.03370 -0.0449 1.0000 0.0319
-11.500 -0.9984 0.03847 0.03222 -0.0439 1.0000 0.0322
-11.250 -0.9863 0.03711 0.03075 -0.0429 1.0000 0.0327
-11.000 -0.9730 0.03575 0.02927 -0.0420 1.0000 0.0332
-10.750 -0.9595 0.03423 0.02757 -0.0411 1.0000 0.0340
-10.500 -0.9459 0.03249 0.02556 -0.0400 1.0000 0.0349
-10.250 -0.9316 0.03062 0.02333 -0.0390 1.0000 0.0358
-10.000 -0.9138 0.02923 0.02177 -0.0382 1.0000 0.0365
-9.750 -0.8938 0.02830 0.02083 -0.0376 1.0000 0.0371
-9.500 -0.8738 0.02741 0.01988 -0.0369 1.0000 0.0378
-9.250 -0.8540 0.02652 0.01889 -0.0361 1.0000 0.0387
-9.000 -0.8351 0.02559 0.01781 -0.0350 1.0000 0.0398
-8.750 -0.8182 0.02464 0.01666 -0.0335 1.0000 0.0409
-8.500 -0.7953 0.02376 0.01572 -0.0333 0.9969 0.0419
-8.250 -0.7644 0.02299 0.01494 -0.0346 0.9909 0.0429
-8.000 -0.7333 0.02222 0.01411 -0.0358 0.9850 0.0442
-7.750 -0.7024 0.02145 0.01320 -0.0369 0.9790 0.0459
-7.500 -0.6715 0.02066 0.01230 -0.0379 0.9732 0.0474
-7.250 -0.6413 0.02003 0.01169 -0.0388 0.9673 0.0488
-7.000 -0.6117 0.01943 0.01105 -0.0395 0.9608 0.0504
-6.750 -0.5818 0.01885 0.01038 -0.0402 0.9551 0.0524
-6.500 -0.5546 0.01828 0.00978 -0.0403 0.9478 0.0543
-6.250 -0.5259 0.01780 0.00930 -0.0407 0.9423 0.0563
-6.000 -0.4998 0.01734 0.00881 -0.0405 0.9349 0.0585
-5.750 -0.4732 0.01689 0.00830 -0.0404 0.9287 0.0610
-5.500 -0.4471 0.01648 0.00792 -0.0402 0.9227 0.0637
-5.250 -0.4212 0.01612 0.00753 -0.0399 0.9161 0.0669
-5.000 -0.3954 0.01571 0.00711 -0.0395 0.9106 0.0701
-4.750 -0.3696 0.01538 0.00680 -0.0392 0.9044 0.0740
-4.500 -0.3435 0.01507 0.00647 -0.0388 0.8982 0.0786
-4.250 -0.3177 0.01475 0.00617 -0.0385 0.8934 0.0835
-4.000 -0.2912 0.01448 0.00588 -0.0382 0.8880 0.0892
-3.750 -0.2649 0.01418 0.00563 -0.0380 0.8820 0.0960
-3.500 -0.2386 0.01391 0.00537 -0.0377 0.8768 0.1035
-3.250 -0.2120 0.01368 0.00515 -0.0374 0.8720 0.1130
-3.000 -0.1851 0.01340 0.00496 -0.0373 0.8660 0.1248
-2.750 -0.1585 0.01314 0.00475 -0.0371 0.8606 0.1406
-2.500 -0.1321 0.01285 0.00455 -0.0368 0.8562 0.1625
-2.250 -0.1052 0.01252 0.00439 -0.0368 0.8504 0.1979
-2.000 -0.0795 0.01197 0.00419 -0.0367 0.8451 0.2742
-1.750 -0.0582 0.01080 0.00399 -0.0360 0.8405 0.5052
-1.500 -0.0344 0.01042 0.00412 -0.0349 0.8359 0.6324
-1.250 -0.0082 0.01035 0.00423 -0.0342 0.8303 0.6885
-1.000 0.0184 0.01034 0.00431 -0.0336 0.8256 0.7237
-0.750 0.0452 0.01036 0.00436 -0.0329 0.8214 0.7491
-0.500 0.0720 0.01040 0.00444 -0.0323 0.8166 0.7700
-0.250 0.0989 0.01044 0.00454 -0.0318 0.8111 0.7885
0.000 0.1255 0.01048 0.00461 -0.0311 0.8065 0.8060
0.250 0.1506 0.01052 0.00467 -0.0299 0.8013 0.8251
0.500 0.1751 0.01052 0.00473 -0.0286 0.7900 0.8425
0.750 0.2003 0.01047 0.00465 -0.0275 0.7776 0.8532
1.000 0.2270 0.01038 0.00452 -0.0267 0.7643 0.8600
1.250 0.2531 0.01032 0.00443 -0.0259 0.7485 0.8665
1.500 0.2800 0.01027 0.00436 -0.0254 0.7321 0.8742
1.750 0.3063 0.01024 0.00431 -0.0246 0.7151 0.8806
2.000 0.3327 0.01022 0.00426 -0.0240 0.6952 0.8876
2.250 0.3591 0.01022 0.00421 -0.0233 0.6670 0.8948
2.500 0.3840 0.01027 0.00412 -0.0222 0.6243 0.9018
2.750 0.4069 0.01055 0.00403 -0.0209 0.5391 0.9103
3.000 0.4213 0.01177 0.00428 -0.0187 0.3341 0.9186
3.250 0.4406 0.01278 0.00470 -0.0176 0.2154 0.9280
3.500 0.4650 0.01329 0.00500 -0.0172 0.1719 0.9370
3.750 0.4915 0.01370 0.00528 -0.0171 0.1461 0.9466
4.000 0.5193 0.01409 0.00556 -0.0173 0.1281 0.9572
4.250 0.5500 0.01446 0.00587 -0.0182 0.1144 0.9667
4.500 0.5817 0.01483 0.00620 -0.0193 0.1039 0.9769
4.750 0.6139 0.01522 0.00655 -0.0205 0.0957 0.9883
5.000 0.6427 0.01566 0.00691 -0.0211 0.0891 1.0000
5.250 0.6661 0.01600 0.00727 -0.0206 0.0841 1.0000
5.500 0.6896 0.01645 0.00765 -0.0201 0.0796 1.0000
5.750 0.7135 0.01689 0.00809 -0.0196 0.0756 1.0000
6.000 0.7377 0.01734 0.00852 -0.0192 0.0719 1.0000
6.250 0.7607 0.01791 0.00902 -0.0187 0.0689 1.0000
6.500 0.7849 0.01838 0.00954 -0.0182 0.0659 1.0000
6.750 0.8087 0.01888 0.01004 -0.0177 0.0631 1.0000
7.000 0.8313 0.01952 0.01061 -0.0171 0.0609 1.0000
7.250 0.8550 0.02007 0.01123 -0.0166 0.0586 1.0000
7.500 0.8783 0.02064 0.01182 -0.0161 0.0564 1.0000
7.750 0.9011 0.02122 0.01239 -0.0155 0.0545 1.0000
8.000 0.9235 0.02193 0.01310 -0.0149 0.0528 1.0000
8.250 0.9463 0.02259 0.01385 -0.0143 0.0510 1.0000
8.500 0.9688 0.02324 0.01454 -0.0136 0.0493 1.0000
8.750 0.9906 0.02389 0.01518 -0.0130 0.0479 1.0000
9.000 1.0119 0.02468 0.01599 -0.0123 0.0466 1.0000
9.250 1.0337 0.02550 0.01693 -0.0116 0.0452 1.0000
9.500 1.0548 0.02629 0.01780 -0.0108 0.0438 1.0000
9.750 1.0751 0.02703 0.01858 -0.0100 0.0426 1.0000
10.000 1.0945 0.02781 0.01935 -0.0092 0.0416 1.0000
10.250 1.1137 0.02880 0.02046 -0.0082 0.0405 1.0000
10.500 1.1325 0.02988 0.02169 -0.0073 0.0394 1.0000
10.750 1.1501 0.03092 0.02287 -0.0062 0.0385 1.0000
11.000 1.1661 0.03188 0.02391 -0.0049 0.0376 1.0000
11.250 1.1802 0.03279 0.02486 -0.0034 0.0369 1.0000
11.500 1.1938 0.03377 0.02586 -0.0020 0.0363 1.0000
11.750 1.2054 0.03519 0.02748 -0.0004 0.0355 1.0000
12.000 1.2152 0.03674 0.02926 0.0012 0.0346 1.0000
12.250 1.2239 0.03830 0.03101 0.0028 0.0339 1.0000
12.500 1.2314 0.03989 0.03276 0.0044 0.0333 1.0000
12.750 1.2380 0.04152 0.03452 0.0058 0.0328 1.0000
13.000 1.2440 0.04317 0.03628 0.0072 0.0324 1.0000
13.250 1.2495 0.04487 0.03807 0.0083 0.0320 1.0000
13.500 1.2543 0.04668 0.03994 0.0094 0.0317 1.0000
13.750 1.2546 0.04907 0.04247 0.0104 0.0314 1.0000
14.000 1.2447 0.05262 0.04637 0.0113 0.0310 1.0000
14.250 1.2320 0.05665 0.05070 0.0117 0.0306 1.0000
14.500 1.2162 0.06125 0.05560 0.0114 0.0303 1.0000
14.750 1.1962 0.06668 0.06131 0.0102 0.0300 1.0000
15.000 1.1705 0.07343 0.06834 0.0077 0.0298 1.0000
15.250 1.1333 0.08289 0.07812 0.0027 0.0298 1.0000
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