AVISTAR (avistar-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AVISTAR (avistar-il) Reynolds number: 50,000 Max Cl/Cd: 31.06 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-avistar-il-50000-n5.txt Download as CSV file: xf-avistar-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3093 0.12783 0.12065 -0.0384 1.0000 0.1680
-11.250 -0.2989 0.12366 0.11652 -0.0384 1.0000 0.1689
-10.750 -0.4420 0.11046 0.10263 -0.0434 1.0000 0.0824
-10.500 -0.4340 0.10711 0.09930 -0.0435 1.0000 0.0817
-10.250 -0.4313 0.10320 0.09541 -0.0446 1.0000 0.0809
-10.000 -0.4321 0.09884 0.09111 -0.0463 1.0000 0.0799
-9.750 -0.4366 0.09391 0.08623 -0.0486 1.0000 0.0786
-9.250 -0.5374 0.07733 0.06954 -0.0583 1.0000 0.0719
-9.000 -0.5524 0.07462 0.06685 -0.0559 1.0000 0.0716
-8.750 -0.5690 0.07205 0.06427 -0.0529 1.0000 0.0714
-8.500 -0.5857 0.06968 0.06187 -0.0495 1.0000 0.0711
-8.250 -0.6023 0.06740 0.05951 -0.0456 1.0000 0.0708
-8.000 -0.6164 0.06513 0.05713 -0.0418 1.0000 0.0705
-7.750 -0.6280 0.06279 0.05466 -0.0381 1.0000 0.0701
-7.500 -0.6369 0.06038 0.05207 -0.0346 1.0000 0.0698
-7.250 -0.6428 0.05797 0.04943 -0.0313 1.0000 0.0694
-7.000 -0.6457 0.05556 0.04678 -0.0282 1.0000 0.0691
-6.750 -0.6419 0.05300 0.04391 -0.0261 0.9987 0.0689
-6.500 -0.6195 0.04986 0.04029 -0.0273 0.9916 0.0690
-6.250 -0.5947 0.04712 0.03704 -0.0286 0.9844 0.0700
-6.000 -0.5693 0.04474 0.03414 -0.0294 0.9764 0.0711
-5.750 -0.5397 0.04259 0.03149 -0.0306 0.9691 0.0718
-5.500 -0.5086 0.04062 0.02915 -0.0318 0.9615 0.0722
-5.250 -0.4759 0.03871 0.02703 -0.0333 0.9543 0.0728
-5.000 -0.4422 0.03708 0.02528 -0.0349 0.9469 0.0742
-4.750 -0.4069 0.03571 0.02380 -0.0367 0.9401 0.0765
-4.500 -0.3738 0.03453 0.02246 -0.0379 0.9321 0.0788
-4.250 -0.3319 0.03333 0.02106 -0.0405 0.9268 0.0806
-4.000 -0.3018 0.03245 0.02005 -0.0408 0.9178 0.0819
-3.750 -0.2628 0.03138 0.01901 -0.0429 0.9117 0.0846
-3.500 -0.2298 0.03058 0.01819 -0.0440 0.9042 0.0885
-3.250 -0.1983 0.02991 0.01742 -0.0447 0.8959 0.0922
-3.000 -0.1602 0.02909 0.01652 -0.0467 0.8902 0.0958
-2.750 -0.1388 0.02859 0.01599 -0.0457 0.8789 0.1003
-2.500 -0.1029 0.02788 0.01523 -0.0473 0.8725 0.1090
-2.250 -0.0810 0.02744 0.01480 -0.0465 0.8614 0.1189
-2.000 -0.0488 0.02654 0.01413 -0.0474 0.8544 0.1480
-1.750 -0.0420 0.02465 0.01407 -0.0443 0.8434 0.4682
-1.500 -0.0166 0.02399 0.01438 -0.0417 0.8364 0.7019
-1.250 0.0277 0.02406 0.01470 -0.0427 0.8291 0.8170
-1.000 0.0913 0.02439 0.01496 -0.0476 0.8225 0.8950
-0.750 0.2056 0.02479 0.01508 -0.0622 0.8204 0.9566
-0.500 0.2587 0.02465 0.01473 -0.0672 0.8131 0.9724
-0.250 0.3032 0.02466 0.01461 -0.0712 0.8023 0.9892
0.000 0.3476 0.02446 0.01426 -0.0749 0.7945 1.0000
0.250 0.3611 0.02454 0.01426 -0.0730 0.7816 1.0000
0.500 0.3767 0.02461 0.01424 -0.0714 0.7705 1.0000
0.750 0.3958 0.02460 0.01413 -0.0701 0.7607 1.0000
1.000 0.4093 0.02483 0.01429 -0.0681 0.7490 1.0000
1.250 0.4317 0.02480 0.01416 -0.0671 0.7410 1.0000
1.500 0.4443 0.02517 0.01448 -0.0650 0.7292 1.0000
1.750 0.4690 0.02514 0.01437 -0.0642 0.7222 1.0000
2.000 0.4816 0.02562 0.01481 -0.0621 0.7105 1.0000
2.250 0.5078 0.02559 0.01471 -0.0615 0.7039 1.0000
2.500 0.5204 0.02615 0.01527 -0.0594 0.6925 1.0000
2.750 0.5478 0.02610 0.01516 -0.0589 0.6861 1.0000
3.000 0.5614 0.02661 0.01567 -0.0568 0.6740 1.0000
3.250 0.5848 0.02665 0.01568 -0.0556 0.6645 1.0000
3.500 0.6067 0.02673 0.01574 -0.0543 0.6536 1.0000
3.750 0.6253 0.02699 0.01601 -0.0526 0.6421 1.0000
4.000 0.6537 0.02683 0.01583 -0.0520 0.6337 1.0000
4.250 0.6691 0.02735 0.01640 -0.0500 0.6220 1.0000
4.500 0.6971 0.02728 0.01632 -0.0494 0.6141 1.0000
4.750 0.7133 0.02781 0.01692 -0.0476 0.6028 1.0000
5.000 0.7369 0.02801 0.01717 -0.0466 0.5936 1.0000
5.250 0.7583 0.02832 0.01754 -0.0453 0.5835 1.0000
5.500 0.7781 0.02873 0.01803 -0.0439 0.5731 1.0000
5.750 0.8076 0.02850 0.01783 -0.0433 0.5623 1.0000
6.000 0.8295 0.02828 0.01761 -0.0413 0.5441 1.0000
6.250 0.8434 0.02831 0.01763 -0.0383 0.5212 1.0000
6.500 0.8586 0.02832 0.01764 -0.0356 0.4982 1.0000
6.750 0.8742 0.02843 0.01773 -0.0330 0.4765 1.0000
7.000 0.8888 0.02862 0.01791 -0.0304 0.4548 1.0000
7.250 0.8974 0.02914 0.01848 -0.0273 0.4313 1.0000
7.500 0.9056 0.02967 0.01907 -0.0242 0.4060 1.0000
7.750 0.9114 0.03034 0.01976 -0.0210 0.3771 1.0000
8.000 0.9153 0.03105 0.02037 -0.0174 0.3410 1.0000
8.250 0.9176 0.03194 0.02099 -0.0137 0.3017 1.0000
8.500 0.9173 0.03327 0.02204 -0.0103 0.2615 1.0000
8.750 0.9150 0.03506 0.02357 -0.0073 0.2143 1.0000
9.250 0.8882 0.04123 0.02865 -0.0019 0.0948 1.0000
9.500 0.8849 0.04391 0.03121 -0.0003 0.0850 1.0000
9.750 0.8833 0.04654 0.03381 0.0010 0.0796 1.0000
10.000 0.8836 0.04908 0.03641 0.0020 0.0756 1.0000
10.250 0.8826 0.05183 0.03921 0.0028 0.0728 1.0000
10.500 0.8821 0.05461 0.04202 0.0035 0.0708 1.0000
10.750 0.8840 0.05719 0.04472 0.0041 0.0691 1.0000
11.000 0.8858 0.05981 0.04746 0.0046 0.0676 1.0000
11.250 0.8879 0.06241 0.05015 0.0051 0.0663 1.0000
11.500 0.8904 0.06497 0.05277 0.0055 0.0649 1.0000
11.750 0.8935 0.06745 0.05527 0.0061 0.0636 1.0000
12.000 0.8990 0.06963 0.05747 0.0068 0.0622 1.0000
12.250 0.9077 0.07153 0.05951 0.0075 0.0607 1.0000
12.500 0.9174 0.07331 0.06139 0.0082 0.0592 1.0000
12.750 0.9291 0.07485 0.06300 0.0092 0.0578 1.0000
13.000 0.9445 0.07599 0.06419 0.0104 0.0567 1.0000
13.250 0.9656 0.07657 0.06481 0.0121 0.0557 1.0000
13.500 0.9992 0.07621 0.06442 0.0143 0.0547 1.0000
13.750 1.0192 0.07755 0.06597 0.0154 0.0542 1.0000
14.000 1.0333 0.07956 0.06822 0.0160 0.0535 1.0000
14.250 1.0420 0.08213 0.07103 0.0163 0.0528 1.0000
14.500 1.0465 0.08513 0.07427 0.0164 0.0522 1.0000
14.750 1.0473 0.08853 0.07790 0.0161 0.0516 1.0000
15.000 1.0453 0.09231 0.08190 0.0155 0.0511 1.0000
15.250 1.0400 0.09653 0.08636 0.0146 0.0508 1.0000
15.500 1.0313 0.10132 0.09139 0.0131 0.0506 1.0000
15.750 1.0185 0.10686 0.09717 0.0110 0.0506 1.0000
16.000 1.0012 0.11339 0.10396 0.0080 0.0507 1.0000
16.250 0.9789 0.12125 0.11207 0.0038 0.0510 1.0000
16.500 0.9513 0.13085 0.12192 -0.0018 0.0515 1.0000
16.750 0.9207 0.14242 0.13371 -0.0089 0.0522 1.0000
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Polar data table (+)
Polar graphs
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