RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 500,000 Max Cl/Cd: 68.14 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil1-il-500000-n5.txt Download as CSV file: xf-amsoil1-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0672 0.05495 0.05161 -0.0521 1.0000 0.0200
-14.500 -1.1026 0.04571 0.04206 -0.0593 1.0000 0.0200
-14.250 -1.1188 0.04098 0.03709 -0.0612 1.0000 0.0201
-14.000 -1.1276 0.03767 0.03355 -0.0613 1.0000 0.0203
-13.750 -1.1316 0.03516 0.03083 -0.0602 1.0000 0.0205
-13.500 -1.1310 0.03321 0.02868 -0.0586 1.0000 0.0207
-13.250 -1.1217 0.03176 0.02714 -0.0575 1.0000 0.0209
-13.000 -1.1078 0.03059 0.02590 -0.0568 1.0000 0.0212
-12.750 -1.0916 0.02956 0.02480 -0.0561 1.0000 0.0214
-12.500 -1.0741 0.02857 0.02373 -0.0555 1.0000 0.0217
-12.250 -1.0560 0.02756 0.02261 -0.0550 1.0000 0.0220
-12.000 -1.0373 0.02652 0.02147 -0.0545 1.0000 0.0223
-11.750 -1.0176 0.02549 0.02031 -0.0540 0.9978 0.0227
-11.500 -0.9924 0.02442 0.01907 -0.0547 0.9767 0.0231
-11.250 -0.9682 0.02341 0.01789 -0.0549 0.9624 0.0235
-11.000 -0.9459 0.02255 0.01685 -0.0545 0.9497 0.0239
-10.750 -0.9251 0.02175 0.01594 -0.0538 0.9386 0.0243
-10.500 -0.9035 0.02115 0.01528 -0.0530 0.9285 0.0247
-10.250 -0.8806 0.02062 0.01468 -0.0524 0.9198 0.0251
-10.000 -0.8577 0.02010 0.01407 -0.0518 0.9120 0.0256
-9.750 -0.8340 0.01952 0.01339 -0.0513 0.9049 0.0260
-9.500 -0.8103 0.01893 0.01269 -0.0508 0.8977 0.0265
-9.250 -0.7861 0.01836 0.01200 -0.0503 0.8914 0.0271
-9.000 -0.7611 0.01783 0.01134 -0.0500 0.8851 0.0276
-8.750 -0.7365 0.01727 0.01069 -0.0496 0.8792 0.0281
-8.500 -0.7113 0.01678 0.01017 -0.0493 0.8737 0.0287
-8.250 -0.6853 0.01636 0.00970 -0.0492 0.8678 0.0292
-8.000 -0.6594 0.01594 0.00921 -0.0489 0.8622 0.0298
-7.750 -0.6335 0.01553 0.00872 -0.0487 0.8574 0.0305
-7.500 -0.6068 0.01511 0.00824 -0.0486 0.8523 0.0311
-7.250 -0.5800 0.01474 0.00778 -0.0484 0.8468 0.0318
-7.000 -0.5539 0.01431 0.00731 -0.0482 0.8418 0.0326
-6.750 -0.5270 0.01395 0.00693 -0.0481 0.8373 0.0334
-6.500 -0.4996 0.01362 0.00657 -0.0481 0.8323 0.0342
-6.250 -0.4724 0.01330 0.00621 -0.0480 0.8273 0.0350
-6.000 -0.4453 0.01301 0.00585 -0.0479 0.8227 0.0359
-5.750 -0.4176 0.01271 0.00551 -0.0478 0.8181 0.0368
-5.500 -0.3901 0.01238 0.00519 -0.0479 0.8134 0.0380
-5.250 -0.3623 0.01213 0.00492 -0.0478 0.8086 0.0393
-5.000 -0.3346 0.01190 0.00464 -0.0478 0.8043 0.0405
-4.750 -0.3064 0.01166 0.00438 -0.0478 0.7997 0.0417
-4.500 -0.2785 0.01139 0.00412 -0.0479 0.7949 0.0434
-4.250 -0.2503 0.01119 0.00391 -0.0479 0.7902 0.0454
-3.750 -0.1937 0.01080 0.00351 -0.0480 0.7816 0.0500
-3.500 -0.1652 0.01063 0.00333 -0.0482 0.7768 0.0529
-3.250 -0.1368 0.01045 0.00316 -0.0482 0.7723 0.0561
-3.000 -0.1084 0.01032 0.00301 -0.0483 0.7683 0.0602
-2.750 -0.0796 0.01015 0.00288 -0.0485 0.7642 0.0648
-2.500 -0.0507 0.01002 0.00276 -0.0486 0.7598 0.0695
-2.250 -0.0221 0.00988 0.00265 -0.0487 0.7553 0.0753
-2.000 0.0066 0.00976 0.00254 -0.0488 0.7511 0.0817
-1.750 0.0355 0.00965 0.00245 -0.0490 0.7470 0.0891
-1.500 0.0645 0.00952 0.00237 -0.0492 0.7425 0.0978
-1.250 0.0934 0.00940 0.00230 -0.0494 0.7379 0.1085
-1.000 0.1221 0.00929 0.00223 -0.0495 0.7334 0.1227
-0.750 0.1511 0.00916 0.00218 -0.0498 0.7287 0.1430
-0.500 0.1800 0.00898 0.00213 -0.0500 0.7236 0.1745
-0.250 0.2086 0.00875 0.00208 -0.0502 0.7189 0.2290
0.000 0.2342 0.00748 0.00195 -0.0507 0.7149 0.5768
0.250 0.2617 0.00716 0.00203 -0.0505 0.7104 0.6868
0.500 0.2898 0.00706 0.00209 -0.0504 0.7053 0.7348
0.750 0.3176 0.00703 0.00210 -0.0501 0.6952 0.7669
1.000 0.3452 0.00702 0.00210 -0.0498 0.6788 0.7902
1.250 0.3728 0.00703 0.00212 -0.0495 0.6639 0.8120
1.500 0.4003 0.00705 0.00216 -0.0492 0.6490 0.8312
1.750 0.4276 0.00710 0.00220 -0.0488 0.6325 0.8476
2.000 0.4539 0.00718 0.00224 -0.0483 0.6106 0.8659
2.250 0.4795 0.00728 0.00230 -0.0475 0.5817 0.8837
2.500 0.5057 0.00748 0.00236 -0.0471 0.5459 0.8945
2.750 0.5308 0.00779 0.00247 -0.0465 0.4938 0.9022
3.000 0.5533 0.00847 0.00273 -0.0457 0.3964 0.9110
3.250 0.5727 0.00945 0.00315 -0.0446 0.2720 0.9206
3.500 0.5948 0.01010 0.00347 -0.0437 0.2007 0.9309
3.750 0.6189 0.01049 0.00371 -0.0431 0.1649 0.9424
4.000 0.6443 0.01082 0.00392 -0.0427 0.1404 0.9542
4.250 0.6722 0.01111 0.00412 -0.0428 0.1224 0.9662
4.500 0.7023 0.01140 0.00434 -0.0435 0.1089 0.9794
4.750 0.7336 0.01169 0.00456 -0.0445 0.0976 0.9991
5.000 0.7598 0.01200 0.00480 -0.0444 0.0888 1.0000
5.250 0.7863 0.01227 0.00504 -0.0443 0.0822 1.0000
5.500 0.8124 0.01258 0.00530 -0.0441 0.0765 1.0000
5.750 0.8383 0.01288 0.00557 -0.0439 0.0710 1.0000
6.000 0.8640 0.01319 0.00586 -0.0437 0.0664 1.0000
6.250 0.8895 0.01353 0.00615 -0.0435 0.0621 1.0000
6.500 0.9148 0.01386 0.00647 -0.0432 0.0588 1.0000
6.750 0.9398 0.01420 0.00680 -0.0428 0.0555 1.0000
7.000 0.9643 0.01457 0.00715 -0.0424 0.0527 1.0000
7.250 0.9889 0.01492 0.00750 -0.0420 0.0501 1.0000
7.500 1.0128 0.01532 0.00788 -0.0416 0.0478 1.0000
7.750 1.0364 0.01573 0.00829 -0.0410 0.0461 1.0000
8.000 1.0600 0.01612 0.00870 -0.0405 0.0445 1.0000
8.250 1.0829 0.01654 0.00913 -0.0399 0.0428 1.0000
8.500 1.1048 0.01703 0.00961 -0.0391 0.0413 1.0000
8.750 1.1269 0.01748 0.01008 -0.0384 0.0402 1.0000
9.000 1.1486 0.01794 0.01058 -0.0376 0.0391 1.0000
9.250 1.1696 0.01843 0.01109 -0.0367 0.0380 1.0000
9.500 1.1896 0.01896 0.01163 -0.0357 0.0370 1.0000
9.750 1.2077 0.01957 0.01224 -0.0344 0.0360 1.0000
10.000 1.2248 0.02012 0.01284 -0.0329 0.0353 1.0000
10.250 1.2420 0.02069 0.01346 -0.0315 0.0345 1.0000
10.500 1.2589 0.02132 0.01413 -0.0302 0.0338 1.0000
10.750 1.2755 0.02198 0.01484 -0.0289 0.0331 1.0000
11.000 1.2917 0.02270 0.01558 -0.0276 0.0323 1.0000
11.250 1.3067 0.02351 0.01642 -0.0263 0.0316 1.0000
11.500 1.3207 0.02442 0.01736 -0.0249 0.0310 1.0000
11.750 1.3364 0.02522 0.01824 -0.0238 0.0305 1.0000
12.000 1.3512 0.02609 0.01918 -0.0226 0.0299 1.0000
12.250 1.3656 0.02701 0.02017 -0.0215 0.0293 1.0000
12.500 1.3797 0.02797 0.02118 -0.0204 0.0288 1.0000
12.750 1.3933 0.02897 0.02224 -0.0193 0.0282 1.0000
13.000 1.4058 0.03006 0.02338 -0.0183 0.0277 1.0000
13.250 1.4165 0.03133 0.02468 -0.0171 0.0272 1.0000
13.500 1.4266 0.03267 0.02608 -0.0160 0.0268 1.0000
13.750 1.4379 0.03393 0.02745 -0.0150 0.0264 1.0000
14.000 1.4483 0.03528 0.02890 -0.0140 0.0260 1.0000
14.250 1.4579 0.03672 0.03042 -0.0131 0.0256 1.0000
14.500 1.4668 0.03825 0.03204 -0.0122 0.0252 1.0000
14.750 1.4749 0.03987 0.03374 -0.0114 0.0248 1.0000
15.000 1.4825 0.04156 0.03551 -0.0106 0.0244 1.0000
15.250 1.4892 0.04336 0.03739 -0.0100 0.0241 1.0000
15.500 1.4944 0.04535 0.03945 -0.0093 0.0238 1.0000
15.750 1.4974 0.04759 0.04176 -0.0088 0.0234 1.0000
16.000 1.4985 0.05009 0.04433 -0.0083 0.0231 1.0000
16.250 1.5019 0.05244 0.04682 -0.0081 0.0229 1.0000
16.500 1.5041 0.05499 0.04950 -0.0079 0.0226 1.0000
16.750 1.5049 0.05778 0.05241 -0.0079 0.0223 1.0000
17.000 1.5046 0.06082 0.05557 -0.0081 0.0220 1.0000
17.250 1.5033 0.06408 0.05896 -0.0085 0.0218 1.0000
17.500 1.5006 0.06761 0.06261 -0.0092 0.0215 1.0000
17.750 1.4968 0.07140 0.06652 -0.0101 0.0213 1.0000
18.000 1.4916 0.07553 0.07077 -0.0112 0.0211 1.0000
18.250 1.4848 0.08003 0.07540 -0.0127 0.0209 1.0000
18.500 1.4762 0.08494 0.08043 -0.0145 0.0207 1.0000
18.750 1.4655 0.09032 0.08594 -0.0167 0.0206 1.0000
19.000 1.4529 0.09621 0.09196 -0.0193 0.0205 1.0000
19.250 1.4379 0.10270 0.09859 -0.0224 0.0203 1.0000
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