AVISTAR (avistar-il) Xfoil prediction polar at RE=100,000 Ncrit=5
Details | Polar file |
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Airfoil: AVISTAR (avistar-il) Reynolds number: 100,000 Max Cl/Cd: 46.74 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-avistar-il-100000-n5.txt Download as CSV file: xf-avistar-il-100000-n5.csv |
XFOIL Version 6.96 Calculated polar for: AVISTAR 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.4503 0.11262 0.10713 -0.0425 1.0000 0.0824 -10.750 -0.4509 0.10775 0.10232 -0.0444 1.0000 0.0828 -10.250 -0.4955 0.08040 0.07476 -0.0594 1.0000 0.0478 -10.000 -0.5050 0.07574 0.07010 -0.0618 1.0000 0.0475 -9.750 -0.5203 0.07134 0.06567 -0.0636 1.0000 0.0472 -9.500 -0.5412 0.06774 0.06203 -0.0632 1.0000 0.0469 -9.250 -0.5676 0.06538 0.05965 -0.0595 1.0000 0.0467 -9.000 -0.5936 0.06362 0.05788 -0.0545 1.0000 0.0464 -8.750 -0.6199 0.06206 0.05626 -0.0489 1.0000 0.0462 -8.500 -0.6161 0.05747 0.05135 -0.0506 0.9908 0.0458 -8.250 -0.6081 0.05326 0.04678 -0.0518 0.9826 0.0456 -8.000 -0.5971 0.04957 0.04270 -0.0523 0.9744 0.0454 -7.750 -0.5831 0.04628 0.03902 -0.0525 0.9668 0.0453 -7.500 -0.5646 0.04330 0.03563 -0.0530 0.9605 0.0457 -7.250 -0.5462 0.04080 0.03268 -0.0529 0.9534 0.0466 -7.000 -0.5251 0.03847 0.02982 -0.0528 0.9463 0.0473 -6.750 -0.5012 0.03640 0.02730 -0.0528 0.9389 0.0477 -6.500 -0.4754 0.03456 0.02509 -0.0529 0.9308 0.0479 -6.250 -0.4451 0.03261 0.02296 -0.0539 0.9247 0.0484 -6.000 -0.4200 0.03116 0.02139 -0.0537 0.9159 0.0489 -5.750 -0.3895 0.02981 0.01995 -0.0545 0.9104 0.0500 -5.500 -0.3641 0.02875 0.01875 -0.0543 0.9029 0.0514 -5.250 -0.3368 0.02768 0.01751 -0.0542 0.8959 0.0526 -5.000 -0.3055 0.02655 0.01621 -0.0547 0.8908 0.0534 -4.750 -0.2809 0.02570 0.01523 -0.0541 0.8825 0.0541 -4.500 -0.2524 0.02485 0.01424 -0.0540 0.8758 0.0548 -4.250 -0.2237 0.02380 0.01326 -0.0542 0.8700 0.0562 -4.000 -0.2003 0.02311 0.01262 -0.0535 0.8613 0.0579 -3.750 -0.1732 0.02241 0.01191 -0.0532 0.8549 0.0598 -3.500 -0.1499 0.02185 0.01133 -0.0523 0.8469 0.0612 -3.250 -0.1261 0.02131 0.01075 -0.0513 0.8390 0.0624 -3.000 -0.1023 0.02070 0.01013 -0.0504 0.8324 0.0638 -2.750 -0.0821 0.02024 0.00969 -0.0490 0.8228 0.0661 -2.500 -0.0572 0.01978 0.00917 -0.0482 0.8159 0.0694 -2.000 -0.0111 0.01904 0.00833 -0.0461 0.7987 0.0755 -1.750 0.0124 0.01874 0.00798 -0.0451 0.7900 0.0802 -1.500 0.0364 0.01835 0.00763 -0.0442 0.7813 0.0897 -1.250 0.0551 0.01725 0.00724 -0.0427 0.7729 0.2255 -1.000 0.0685 0.01588 0.00717 -0.0401 0.7634 0.5239 -0.750 0.0915 0.01538 0.00725 -0.0382 0.7554 0.6840 -0.500 0.1202 0.01521 0.00730 -0.0377 0.7457 0.7631 -0.250 0.1624 0.01510 0.00734 -0.0395 0.7385 0.8303 0.000 0.2049 0.01519 0.00746 -0.0418 0.7280 0.8818 0.250 0.2583 0.01529 0.00751 -0.0461 0.7197 0.9246 0.500 0.3091 0.01541 0.00755 -0.0506 0.7088 0.9414 0.750 0.3504 0.01545 0.00749 -0.0533 0.6995 0.9515 1.000 0.3906 0.01551 0.00747 -0.0558 0.6894 0.9617 1.250 0.4301 0.01558 0.00747 -0.0583 0.6792 0.9724 1.500 0.4683 0.01563 0.00743 -0.0605 0.6698 0.9848 1.750 0.5076 0.01575 0.00751 -0.0633 0.6595 0.9967 2.000 0.5375 0.01573 0.00738 -0.0639 0.6501 1.0000 2.250 0.5577 0.01577 0.00738 -0.0627 0.6375 1.0000 2.500 0.5785 0.01580 0.00733 -0.0614 0.6249 1.0000 2.750 0.6001 0.01583 0.00726 -0.0602 0.6131 1.0000 3.000 0.6215 0.01594 0.00733 -0.0591 0.6013 1.0000 3.250 0.6438 0.01607 0.00742 -0.0581 0.5919 1.0000 3.500 0.6665 0.01622 0.00753 -0.0572 0.5830 1.0000 3.750 0.6891 0.01639 0.00770 -0.0563 0.5740 1.0000 4.000 0.7120 0.01657 0.00785 -0.0553 0.5649 1.0000 4.250 0.7337 0.01675 0.00801 -0.0541 0.5518 1.0000 4.500 0.7545 0.01691 0.00811 -0.0527 0.5342 1.0000 4.750 0.7745 0.01710 0.00820 -0.0511 0.5134 1.0000 5.000 0.7943 0.01732 0.00835 -0.0495 0.4936 1.0000 5.250 0.8138 0.01757 0.00853 -0.0479 0.4731 1.0000 5.500 0.8324 0.01786 0.00879 -0.0462 0.4507 1.0000 5.750 0.8497 0.01818 0.00906 -0.0443 0.4221 1.0000 6.000 0.8662 0.01856 0.00936 -0.0422 0.3867 1.0000 6.250 0.8788 0.01915 0.00969 -0.0396 0.3319 1.0000 6.500 0.8842 0.02024 0.01027 -0.0361 0.2694 1.0000 6.750 0.8899 0.02145 0.01110 -0.0327 0.2094 1.0000 7.000 0.8770 0.02386 0.01255 -0.0272 0.0752 1.0000 7.250 0.8820 0.02511 0.01364 -0.0238 0.0602 1.0000 7.500 0.8905 0.02607 0.01460 -0.0210 0.0556 1.0000 7.750 0.8984 0.02695 0.01553 -0.0180 0.0529 1.0000 8.000 0.9061 0.02787 0.01652 -0.0152 0.0508 1.0000 8.250 0.9125 0.02894 0.01765 -0.0124 0.0489 1.0000 8.500 0.9178 0.03016 0.01893 -0.0098 0.0473 1.0000 8.750 0.9253 0.03132 0.02020 -0.0076 0.0458 1.0000 9.000 0.9315 0.03264 0.02160 -0.0055 0.0444 1.0000 9.250 0.9365 0.03411 0.02316 -0.0036 0.0433 1.0000 9.500 0.9402 0.03575 0.02487 -0.0017 0.0425 1.0000 9.750 0.9428 0.03756 0.02674 0.0000 0.0419 1.0000 10.000 0.9444 0.03952 0.02875 0.0017 0.0414 1.0000 10.250 0.9499 0.04125 0.03056 0.0030 0.0409 1.0000 10.500 0.9560 0.04297 0.03235 0.0042 0.0404 1.0000 10.750 0.9632 0.04465 0.03409 0.0054 0.0399 1.0000 11.000 0.9718 0.04624 0.03573 0.0065 0.0394 1.0000 11.250 0.9822 0.04772 0.03724 0.0076 0.0387 1.0000 11.500 0.9943 0.04910 0.03863 0.0087 0.0379 1.0000 11.750 1.0082 0.05038 0.03989 0.0097 0.0370 1.0000 12.000 1.0262 0.05144 0.04087 0.0107 0.0362 1.0000 12.250 1.0483 0.05239 0.04178 0.0116 0.0355 1.0000 12.500 1.0668 0.05362 0.04310 0.0125 0.0351 1.0000 12.750 1.0855 0.05494 0.04452 0.0133 0.0348 1.0000 13.000 1.1037 0.05640 0.04610 0.0140 0.0344 1.0000 13.250 1.1205 0.05802 0.04785 0.0147 0.0341 1.0000 13.500 1.1359 0.05980 0.04977 0.0154 0.0338 1.0000 13.750 1.1489 0.06179 0.05191 0.0161 0.0336 1.0000 14.000 1.1587 0.06399 0.05429 0.0168 0.0333 1.0000 14.250 1.1651 0.06639 0.05687 0.0174 0.0330 1.0000 14.500 1.1688 0.06897 0.05963 0.0180 0.0327 1.0000 14.750 1.1706 0.07171 0.06253 0.0184 0.0323 1.0000 15.000 1.1713 0.07456 0.06554 0.0187 0.0320 1.0000 15.250 1.1717 0.07750 0.06863 0.0188 0.0317 1.0000 15.500 1.1720 0.08056 0.07182 0.0188 0.0314 1.0000 15.750 1.1711 0.08380 0.07520 0.0187 0.0312 1.0000 16.000 1.1680 0.08732 0.07887 0.0185 0.0310 1.0000 16.250 1.1578 0.09148 0.08323 0.0177 0.0310 1.0000 16.500 1.1430 0.09620 0.08819 0.0165 0.0310 1.0000 16.750 1.1237 0.10164 0.09389 0.0145 0.0310 1.0000 17.000 1.0990 0.10821 0.10074 0.0114 0.0312 1.0000 17.250 1.0700 0.11608 0.10892 0.0071 0.0314 1.0000 17.500 1.0347 0.12593 0.11911 0.0011 0.0316 1.0000 17.750 0.9911 0.13903 0.13253 -0.0075 0.0321 1.0000 |
Polar data table (+)
Polar graphs
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