RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 500,000 Max Cl/Cd: 56.86 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil2-il-500000.txt Download as CSV file: xf-amsoil2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4508 0.15542 0.15303 -0.0004 1.0000 0.0333
-15.000 -0.4484 0.15309 0.15070 -0.0015 1.0000 0.0342
-14.500 -1.0544 0.06083 0.05728 -0.0441 1.0000 0.0274
-14.000 -1.1080 0.04831 0.04427 -0.0495 1.0000 0.0276
-13.750 -1.1196 0.04458 0.04039 -0.0497 1.0000 0.0278
-13.500 -1.1203 0.04225 0.03799 -0.0492 1.0000 0.0281
-13.250 -1.1185 0.04040 0.03605 -0.0484 1.0000 0.0283
-13.000 -1.1155 0.03879 0.03436 -0.0472 1.0000 0.0286
-12.750 -1.1130 0.03726 0.03272 -0.0454 1.0000 0.0289
-12.500 -1.1071 0.03578 0.03113 -0.0438 1.0000 0.0292
-12.250 -1.0983 0.03417 0.02937 -0.0425 1.0000 0.0296
-12.000 -1.0883 0.03247 0.02748 -0.0412 1.0000 0.0301
-11.750 -1.0767 0.03077 0.02555 -0.0400 1.0000 0.0306
-11.500 -1.0628 0.02925 0.02379 -0.0389 1.0000 0.0312
-11.250 -1.0462 0.02811 0.02241 -0.0379 1.0000 0.0316
-11.000 -1.0297 0.02608 0.02031 -0.0372 1.0000 0.0323
-10.750 -1.0083 0.02531 0.01953 -0.0368 1.0000 0.0329
-10.500 -0.9864 0.02464 0.01881 -0.0364 1.0000 0.0335
-10.250 -0.9644 0.02388 0.01798 -0.0359 1.0000 0.0343
-10.000 -0.9426 0.02302 0.01698 -0.0354 1.0000 0.0351
-9.750 -0.9206 0.02221 0.01602 -0.0348 1.0000 0.0358
-9.500 -0.9007 0.02107 0.01477 -0.0340 1.0000 0.0365
-9.250 -0.8855 0.02028 0.01399 -0.0322 1.0000 0.0372
-9.000 -0.8589 0.01969 0.01339 -0.0325 0.9975 0.0381
-8.750 -0.8247 0.01909 0.01274 -0.0343 0.9946 0.0392
-8.500 -0.7913 0.01849 0.01205 -0.0358 0.9905 0.0405
-8.250 -0.7584 0.01778 0.01123 -0.0373 0.9860 0.0415
-8.000 -0.7266 0.01685 0.01032 -0.0386 0.9816 0.0427
-7.750 -0.6962 0.01636 0.00983 -0.0395 0.9750 0.0439
-7.500 -0.6660 0.01594 0.00936 -0.0401 0.9690 0.0453
-7.250 -0.6393 0.01560 0.00894 -0.0399 0.9607 0.0466
-7.000 -0.6152 0.01491 0.00824 -0.0394 0.9533 0.0480
-6.750 -0.5913 0.01452 0.00785 -0.0386 0.9455 0.0493
-6.500 -0.5668 0.01421 0.00752 -0.0380 0.9386 0.0509
-6.250 -0.5418 0.01393 0.00719 -0.0373 0.9313 0.0526
-6.000 -0.5182 0.01348 0.00670 -0.0365 0.9252 0.0543
-5.750 -0.4926 0.01310 0.00634 -0.0361 0.9186 0.0563
-5.500 -0.4670 0.01282 0.00605 -0.0356 0.9128 0.0585
-5.250 -0.4408 0.01262 0.00578 -0.0352 0.9076 0.0607
-5.000 -0.4150 0.01217 0.00538 -0.0349 0.9015 0.0640
-4.750 -0.3886 0.01194 0.00513 -0.0346 0.8959 0.0672
-4.500 -0.3627 0.01161 0.00480 -0.0342 0.8908 0.0711
-4.250 -0.3351 0.01138 0.00460 -0.0341 0.8851 0.0758
-4.000 -0.3083 0.01110 0.00432 -0.0339 0.8795 0.0813
-3.750 -0.2814 0.01093 0.00413 -0.0336 0.8746 0.0871
-3.500 -0.2537 0.01065 0.00391 -0.0336 0.8694 0.0944
-3.250 -0.2257 0.01045 0.00372 -0.0336 0.8642 0.1024
-3.000 -0.1982 0.01024 0.00355 -0.0335 0.8595 0.1124
-2.750 -0.1706 0.01003 0.00339 -0.0334 0.8549 0.1255
-2.500 -0.1423 0.00979 0.00324 -0.0336 0.8499 0.1440
-2.250 -0.1145 0.00950 0.00309 -0.0336 0.8450 0.1771
-2.000 -0.0876 0.00901 0.00291 -0.0337 0.8407 0.2526
-1.750 -0.0637 0.00775 0.00265 -0.0337 0.8362 0.5143
-1.500 -0.0372 0.00729 0.00268 -0.0335 0.8311 0.6427
-1.250 -0.0093 0.00719 0.00271 -0.0333 0.8263 0.6905
-1.000 0.0188 0.00716 0.00274 -0.0330 0.8222 0.7200
-0.750 0.0470 0.00717 0.00280 -0.0329 0.8177 0.7432
-0.500 0.0752 0.00714 0.00281 -0.0326 0.8101 0.7629
-0.250 0.1025 0.00714 0.00278 -0.0320 0.8019 0.7791
0.000 0.1305 0.00709 0.00278 -0.0317 0.7922 0.7920
0.250 0.1581 0.00708 0.00272 -0.0312 0.7814 0.8048
0.500 0.1857 0.00705 0.00272 -0.0308 0.7705 0.8170
0.750 0.2133 0.00705 0.00273 -0.0304 0.7616 0.8281
1.000 0.2410 0.00706 0.00275 -0.0300 0.7512 0.8411
1.250 0.2674 0.00708 0.00281 -0.0292 0.7405 0.8550
1.500 0.2944 0.00708 0.00279 -0.0287 0.7265 0.8634
1.750 0.3221 0.00708 0.00276 -0.0284 0.7080 0.8699
2.000 0.3502 0.00710 0.00273 -0.0282 0.6853 0.8766
2.250 0.3766 0.00714 0.00272 -0.0276 0.6578 0.8829
2.500 0.4032 0.00728 0.00272 -0.0271 0.6147 0.8904
2.750 0.4265 0.00772 0.00278 -0.0261 0.5201 0.8973
3.000 0.4426 0.00920 0.00326 -0.0246 0.2871 0.9053
3.250 0.4643 0.00999 0.00360 -0.0238 0.1879 0.9129
3.500 0.4879 0.01038 0.00383 -0.0229 0.1506 0.9211
3.750 0.5119 0.01071 0.00404 -0.0222 0.1280 0.9297
4.000 0.5355 0.01098 0.00424 -0.0213 0.1136 0.9393
4.250 0.5594 0.01120 0.00443 -0.0204 0.1034 0.9490
4.500 0.5844 0.01142 0.00464 -0.0197 0.0955 0.9599
4.750 0.6113 0.01175 0.00491 -0.0196 0.0883 0.9715
5.000 0.6435 0.01201 0.00517 -0.0207 0.0827 0.9818
5.250 0.6774 0.01243 0.00554 -0.0222 0.0770 0.9917
5.500 0.7096 0.01273 0.00582 -0.0234 0.0727 1.0000
5.750 0.7335 0.01324 0.00628 -0.0231 0.0688 1.0000
6.000 0.7604 0.01351 0.00656 -0.0231 0.0659 1.0000
6.250 0.7865 0.01388 0.00689 -0.0230 0.0630 1.0000
6.500 0.8107 0.01447 0.00746 -0.0227 0.0603 1.0000
6.750 0.8369 0.01480 0.00781 -0.0225 0.0582 1.0000
7.000 0.8626 0.01517 0.00816 -0.0223 0.0560 1.0000
7.250 0.8857 0.01583 0.00877 -0.0218 0.0538 1.0000
7.500 0.9107 0.01626 0.00924 -0.0214 0.0523 1.0000
7.750 0.9358 0.01665 0.00966 -0.0211 0.0505 1.0000
8.000 0.9604 0.01707 0.01006 -0.0207 0.0489 1.0000
8.250 0.9824 0.01782 0.01077 -0.0200 0.0473 1.0000
8.500 1.0061 0.01835 0.01136 -0.0195 0.0461 1.0000
8.750 1.0299 0.01884 0.01190 -0.0190 0.0448 1.0000
9.000 1.0534 0.01931 0.01239 -0.0184 0.0434 1.0000
9.250 1.0760 0.01984 0.01290 -0.0178 0.0422 1.0000
9.500 1.0966 0.02080 0.01386 -0.0170 0.0410 1.0000
9.750 1.1191 0.02133 0.01449 -0.0163 0.0400 1.0000
10.000 1.1408 0.02195 0.01517 -0.0156 0.0390 1.0000
10.250 1.1620 0.02255 0.01581 -0.0148 0.0380 1.0000
10.500 1.1825 0.02320 0.01646 -0.0139 0.0372 1.0000
10.750 1.2013 0.02434 0.01759 -0.0130 0.0362 1.0000
11.000 1.2203 0.02515 0.01851 -0.0119 0.0355 1.0000
11.250 1.2385 0.02587 0.01935 -0.0108 0.0347 1.0000
11.500 1.2547 0.02662 0.02018 -0.0093 0.0339 1.0000
11.750 1.2697 0.02738 0.02100 -0.0077 0.0332 1.0000
12.000 1.2844 0.02820 0.02185 -0.0062 0.0326 1.0000
12.250 1.2987 0.02919 0.02286 -0.0048 0.0321 1.0000
12.500 1.3116 0.03094 0.02467 -0.0035 0.0314 1.0000
12.750 1.3219 0.03203 0.02593 -0.0017 0.0310 1.0000
13.000 1.3312 0.03332 0.02738 0.0000 0.0306 1.0000
13.250 1.3397 0.03473 0.02894 0.0016 0.0301 1.0000
13.500 1.3472 0.03622 0.03056 0.0032 0.0297 1.0000
13.750 1.3535 0.03779 0.03226 0.0046 0.0292 1.0000
14.000 1.3596 0.03937 0.03395 0.0059 0.0289 1.0000
14.250 1.3656 0.04095 0.03560 0.0071 0.0285 1.0000
14.500 1.3714 0.04262 0.03733 0.0081 0.0282 1.0000
14.750 1.3760 0.04449 0.03925 0.0090 0.0278 1.0000
15.000 1.3760 0.04708 0.04192 0.0100 0.0275 1.0000
15.250 1.3680 0.05048 0.04551 0.0108 0.0272 1.0000
15.500 1.3602 0.05379 0.04903 0.0112 0.0271 1.0000
15.750 1.3493 0.05766 0.05312 0.0111 0.0269 1.0000
16.000 1.3353 0.06215 0.05783 0.0104 0.0268 1.0000
16.250 1.3175 0.06745 0.06335 0.0089 0.0267 1.0000
16.500 1.2955 0.07379 0.06992 0.0065 0.0266 1.0000
16.750 1.2683 0.08170 0.07808 0.0025 0.0265 1.0000
17.000 1.2320 0.09217 0.08881 -0.0037 0.0266 1.0000
17.250 1.1720 0.10929 0.10626 -0.0151 0.0268 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RUTAN WING AIRFOIL (amsoil2-il)