AVISTAR (avistar-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AVISTAR (avistar-il) Reynolds number: 200,000 Max Cl/Cd: 63.93 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-avistar-il-200000.txt Download as CSV file: xf-avistar-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4926 0.08007 0.07626 -0.0614 1.0000 0.0716
-9.500 -0.5332 0.07615 0.07228 -0.0616 1.0000 0.0717
-9.250 -0.5686 0.07508 0.07125 -0.0554 1.0000 0.0717
-9.000 -0.5993 0.07446 0.07065 -0.0488 1.0000 0.0716
-8.750 -0.6434 0.07167 0.06732 -0.0475 0.9933 0.0721
-8.500 -0.5994 0.06568 0.06180 -0.0501 0.9941 0.0737
-8.250 -0.5728 0.06283 0.05898 -0.0525 0.9896 0.0754
-8.000 -0.5542 0.05889 0.05487 -0.0561 0.9841 0.0788
-7.750 -0.5569 0.05349 0.04893 -0.0581 0.9741 0.0843
-7.500 -0.5229 0.05069 0.04620 -0.0612 0.9711 0.0870
-7.250 -0.5176 0.04779 0.04274 -0.0611 0.9620 0.0957
-7.000 -0.4831 0.04485 0.03997 -0.0640 0.9598 0.0987
-6.750 -0.4714 0.04286 0.03759 -0.0634 0.9517 0.1091
-6.500 -0.4404 0.04076 0.03562 -0.0651 0.9476 0.1145
-6.250 -0.4161 0.03861 0.03334 -0.0662 0.9435 0.1266
-6.000 -0.4022 0.03718 0.03176 -0.0649 0.9347 0.1398
-5.750 -0.3797 0.03566 0.03016 -0.0650 0.9292 0.1552
-5.500 -0.3561 0.02834 0.02067 -0.0588 0.9216 0.0728
-5.250 -0.3278 0.02649 0.01877 -0.0588 0.9154 0.0707
-5.000 -0.2981 0.02451 0.01664 -0.0589 0.9106 0.0685
-4.750 -0.2722 0.02310 0.01500 -0.0581 0.9037 0.0662
-4.500 -0.2458 0.02204 0.01371 -0.0573 0.8964 0.0651
-4.250 -0.2165 0.02103 0.01259 -0.0571 0.8911 0.0650
-4.000 -0.1921 0.02026 0.01182 -0.0564 0.8828 0.0661
-3.750 -0.1657 0.01951 0.01105 -0.0558 0.8760 0.0673
-3.500 -0.1389 0.01880 0.01030 -0.0553 0.8699 0.0680
-3.250 -0.1150 0.01820 0.00970 -0.0543 0.8610 0.0687
-3.000 -0.0894 0.01759 0.00905 -0.0534 0.8545 0.0697
-2.750 -0.0664 0.01713 0.00860 -0.0522 0.8454 0.0709
-2.500 -0.0429 0.01659 0.00803 -0.0510 0.8375 0.0728
-2.250 -0.0217 0.01599 0.00748 -0.0496 0.8293 0.0752
-2.000 0.0007 0.01556 0.00706 -0.0483 0.8204 0.0775
-1.750 0.0248 0.01521 0.00665 -0.0472 0.8130 0.0804
-1.500 0.0476 0.01490 0.00630 -0.0460 0.8028 0.0841
-1.250 0.0726 0.01453 0.00588 -0.0450 0.7955 0.0921
-1.000 0.0946 0.01413 0.00562 -0.0437 0.7841 0.1143
-0.750 0.0985 0.01219 0.00530 -0.0392 0.7763 0.5138
-0.500 0.1093 0.01152 0.00545 -0.0349 0.7648 0.7165
-0.250 0.1381 0.01120 0.00546 -0.0339 0.7569 0.8197
0.000 0.1774 0.01116 0.00553 -0.0355 0.7457 0.8834
0.250 0.2257 0.01120 0.00552 -0.0391 0.7364 0.9222
0.500 0.2882 0.01136 0.00561 -0.0458 0.7252 0.9415
0.750 0.3427 0.01164 0.00580 -0.0507 0.7138 0.9559
1.000 0.3942 0.01188 0.00590 -0.0551 0.7038 0.9703
1.250 0.4402 0.01201 0.00596 -0.0588 0.6900 0.9806
1.500 0.4827 0.01205 0.00592 -0.0620 0.6764 0.9896
1.750 0.5270 0.01206 0.00582 -0.0656 0.6639 0.9971
2.000 0.5595 0.01201 0.00567 -0.0670 0.6521 1.0000
2.250 0.5808 0.01197 0.00560 -0.0662 0.6408 1.0000
2.500 0.6034 0.01198 0.00550 -0.0654 0.6322 1.0000
2.750 0.6255 0.01201 0.00554 -0.0647 0.6219 1.0000
3.000 0.6481 0.01207 0.00551 -0.0638 0.6118 1.0000
3.250 0.6701 0.01212 0.00547 -0.0627 0.5991 1.0000
3.500 0.6916 0.01217 0.00549 -0.0615 0.5844 1.0000
3.750 0.7134 0.01226 0.00553 -0.0604 0.5700 1.0000
4.000 0.7354 0.01238 0.00557 -0.0593 0.5556 1.0000
4.250 0.7576 0.01252 0.00563 -0.0581 0.5414 1.0000
4.500 0.7795 0.01267 0.00572 -0.0570 0.5257 1.0000
4.750 0.8011 0.01283 0.00585 -0.0557 0.5092 1.0000
5.000 0.8216 0.01300 0.00597 -0.0543 0.4876 1.0000
5.250 0.8416 0.01319 0.00613 -0.0528 0.4625 1.0000
5.500 0.8598 0.01345 0.00628 -0.0509 0.4262 1.0000
5.750 0.8722 0.01402 0.00650 -0.0481 0.3496 1.0000
6.000 0.8740 0.01545 0.00721 -0.0438 0.2464 1.0000
6.250 0.8677 0.01755 0.00839 -0.0387 0.0974 1.0000
6.500 0.8730 0.01888 0.00943 -0.0351 0.0632 1.0000
6.750 0.8878 0.01954 0.01013 -0.0329 0.0585 1.0000
7.000 0.9003 0.02032 0.01093 -0.0304 0.0555 1.0000
7.250 0.9129 0.02105 0.01173 -0.0279 0.0537 1.0000
7.500 0.9240 0.02179 0.01254 -0.0252 0.0523 1.0000
7.750 0.9303 0.02258 0.01339 -0.0217 0.0511 1.0000
8.000 0.9347 0.02349 0.01434 -0.0181 0.0500 1.0000
8.250 0.9375 0.02461 0.01548 -0.0147 0.0490 1.0000
8.500 0.9381 0.02602 0.01689 -0.0114 0.0481 1.0000
8.750 0.9440 0.02730 0.01818 -0.0089 0.0472 1.0000
9.000 0.9536 0.02842 0.01934 -0.0069 0.0465 1.0000
9.250 0.9636 0.02961 0.02056 -0.0050 0.0460 1.0000
9.500 0.9749 0.03081 0.02177 -0.0033 0.0455 1.0000
9.750 0.9881 0.03197 0.02294 -0.0018 0.0450 1.0000
10.000 1.0037 0.03308 0.02405 -0.0005 0.0446 1.0000
10.250 1.0224 0.03413 0.02508 0.0006 0.0442 1.0000
10.500 1.0444 0.03513 0.02607 0.0014 0.0439 1.0000
10.750 1.0694 0.03614 0.02709 0.0019 0.0436 1.0000
11.000 1.0971 0.03720 0.02815 0.0021 0.0432 1.0000
11.250 1.1289 0.03841 0.02933 0.0017 0.0426 1.0000
11.500 1.1708 0.03998 0.03087 0.0001 0.0420 1.0000
11.750 1.2025 0.04152 0.03250 -0.0005 0.0422 1.0000
12.000 1.2205 0.04304 0.03424 0.0006 0.0427 1.0000
12.250 1.2333 0.04488 0.03639 0.0024 0.0436 1.0000
12.500 1.2600 0.04740 0.03916 0.0024 0.0451 1.0000
12.750 1.3461 0.05268 0.04441 -0.0063 0.0481 1.0000
13.000 1.2832 0.04851 0.04114 0.0027 0.0550 1.0000
13.250 1.2459 0.04950 0.04241 0.0106 0.0544 1.0000
13.500 1.2088 0.04930 0.04256 0.0178 0.0564 1.0000
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Polar data table (+)
Polar graphs
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