BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 100,000 Max Cl/Cd: 55.41 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr5-il-100000-n5.txt Download as CSV file: xf-vr5-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4190 0.11459 0.11009 -0.0157 1.0000 0.0489
-10.000 -0.4198 0.11052 0.10607 -0.0214 1.0000 0.0498
-9.750 -0.4182 0.10616 0.10177 -0.0265 1.0000 0.0500
-9.500 -0.4158 0.10154 0.09720 -0.0319 1.0000 0.0502
-9.250 -0.4131 0.09637 0.09205 -0.0390 0.9684 0.0503
-9.000 -0.3929 0.09351 0.08919 -0.0314 0.9579 0.0527
-8.750 -0.3844 0.09027 0.08593 -0.0328 0.9385 0.0547
-8.500 -0.3820 0.08654 0.08219 -0.0352 0.9211 0.0559
-8.250 -0.3823 0.08239 0.07803 -0.0385 0.9055 0.0564
-8.000 -0.3848 0.07765 0.07326 -0.0435 0.8913 0.0561
-7.750 -0.3899 0.06918 0.06457 -0.0513 0.8791 0.0423
-7.500 -0.3857 0.06398 0.05918 -0.0535 0.8694 0.0357
-7.000 -0.3739 0.05100 0.04523 -0.0585 0.8502 0.0311
-6.750 -0.3612 0.04729 0.04121 -0.0585 0.8422 0.0310
-6.250 -0.3286 0.04165 0.03511 -0.0586 0.8257 0.0328
-6.000 -0.3084 0.03949 0.03273 -0.0588 0.8167 0.0343
-5.750 -0.2884 0.03662 0.02944 -0.0584 0.8101 0.0350
-5.500 -0.2657 0.03369 0.02607 -0.0582 0.8019 0.0354
-5.250 -0.2432 0.03116 0.02306 -0.0575 0.7959 0.0361
-5.000 -0.2179 0.02894 0.02037 -0.0572 0.7877 0.0376
-4.750 -0.1925 0.02721 0.01808 -0.0564 0.7815 0.0401
-4.500 -0.1672 0.02558 0.01633 -0.0564 0.7738 0.0421
-4.250 -0.1416 0.02442 0.01498 -0.0560 0.7675 0.0447
-4.000 -0.1147 0.02338 0.01368 -0.0557 0.7609 0.0482
-3.750 -0.0877 0.02234 0.01239 -0.0552 0.7547 0.0506
-3.500 -0.0625 0.02127 0.01133 -0.0548 0.7495 0.0543
-3.250 -0.0358 0.02046 0.01046 -0.0545 0.7425 0.0569
-3.000 -0.0100 0.01975 0.00964 -0.0539 0.7371 0.0600
-2.750 0.0158 0.01912 0.00896 -0.0536 0.7311 0.0640
-2.500 0.0415 0.01858 0.00841 -0.0532 0.7252 0.0677
-2.250 0.0674 0.01814 0.00785 -0.0527 0.7207 0.0722
-2.000 0.0941 0.01778 0.00745 -0.0527 0.7147 0.0798
-1.750 0.1210 0.01745 0.00709 -0.0526 0.7091 0.0926
-1.500 0.1473 0.01698 0.00668 -0.0523 0.7048 0.1269
-1.250 0.1626 0.01496 0.00672 -0.0506 0.6994 0.6548
-1.000 0.1821 0.01487 0.00690 -0.0479 0.6943 0.7662
-0.750 0.2010 0.01485 0.00696 -0.0447 0.6901 0.8357
-0.500 0.2206 0.01491 0.00710 -0.0413 0.6854 0.9070
-0.250 0.2584 0.01495 0.00705 -0.0424 0.6801 0.9514
0.000 0.2970 0.01495 0.00689 -0.0446 0.6757 0.9648
0.250 0.3340 0.01496 0.00675 -0.0467 0.6716 0.9749
0.500 0.3720 0.01506 0.00678 -0.0494 0.6657 0.9859
0.750 0.4104 0.01511 0.00671 -0.0519 0.6610 0.9977
1.000 0.4354 0.01517 0.00666 -0.0517 0.6572 1.0000
1.250 0.4584 0.01539 0.00685 -0.0515 0.6514 1.0000
1.500 0.4827 0.01556 0.00696 -0.0513 0.6466 1.0000
1.750 0.5081 0.01569 0.00700 -0.0511 0.6428 1.0000
2.000 0.5339 0.01593 0.00721 -0.0512 0.6380 1.0000
2.250 0.5601 0.01618 0.00745 -0.0513 0.6329 1.0000
2.500 0.5869 0.01635 0.00758 -0.0513 0.6288 1.0000
2.750 0.6138 0.01653 0.00773 -0.0513 0.6247 1.0000
3.000 0.6401 0.01682 0.00806 -0.0515 0.6182 1.0000
3.250 0.6672 0.01689 0.00810 -0.0513 0.6126 1.0000
3.500 0.6935 0.01709 0.00833 -0.0514 0.6050 1.0000
3.750 0.7205 0.01717 0.00840 -0.0512 0.5983 1.0000
4.000 0.7471 0.01736 0.00865 -0.0512 0.5912 1.0000
4.250 0.7739 0.01751 0.00884 -0.0512 0.5845 1.0000
4.500 0.8010 0.01767 0.00902 -0.0511 0.5792 1.0000
4.750 0.8271 0.01798 0.00946 -0.0512 0.5723 1.0000
5.000 0.8545 0.01813 0.00964 -0.0511 0.5672 1.0000
5.250 0.8804 0.01845 0.01008 -0.0512 0.5601 1.0000
5.500 0.9071 0.01863 0.01033 -0.0511 0.5535 1.0000
5.750 0.9332 0.01888 0.01071 -0.0510 0.5460 1.0000
6.000 0.9596 0.01902 0.01093 -0.0508 0.5374 1.0000
6.250 0.9847 0.01924 0.01130 -0.0505 0.5265 1.0000
6.500 1.0100 0.01934 0.01152 -0.0501 0.5139 1.0000
6.750 1.0344 0.01943 0.01172 -0.0496 0.4976 1.0000
7.000 1.0581 0.01951 0.01189 -0.0490 0.4773 1.0000
7.250 1.0809 0.01969 0.01220 -0.0484 0.4543 1.0000
7.500 1.1027 0.01991 0.01246 -0.0477 0.4252 1.0000
7.750 1.1226 0.02026 0.01269 -0.0466 0.3875 1.0000
8.000 1.1394 0.02096 0.01322 -0.0454 0.3445 1.0000
8.250 1.1519 0.02203 0.01408 -0.0440 0.2972 1.0000
8.500 1.1607 0.02343 0.01524 -0.0424 0.2562 1.0000
8.750 1.1671 0.02499 0.01663 -0.0407 0.2135 1.0000
9.000 1.1668 0.02689 0.01827 -0.0386 0.1606 1.0000
9.250 1.1627 0.02927 0.02033 -0.0367 0.1282 1.0000
9.500 1.1634 0.03144 0.02239 -0.0352 0.1054 1.0000
9.750 1.1655 0.03358 0.02446 -0.0340 0.0881 1.0000
10.000 1.1680 0.03574 0.02658 -0.0330 0.0762 1.0000
10.250 1.1712 0.03791 0.02877 -0.0320 0.0675 1.0000
10.500 1.1714 0.04040 0.03122 -0.0312 0.0615 1.0000
10.750 1.1762 0.04251 0.03348 -0.0305 0.0558 1.0000
11.000 1.1772 0.04502 0.03603 -0.0298 0.0516 1.0000
11.250 1.1799 0.04739 0.03850 -0.0291 0.0482 1.0000
11.500 1.1831 0.04973 0.04095 -0.0284 0.0452 1.0000
11.750 1.1854 0.05219 0.04349 -0.0279 0.0428 1.0000
12.000 1.1863 0.05476 0.04607 -0.0271 0.0410 1.0000
12.250 1.1925 0.05685 0.04832 -0.0263 0.0391 1.0000
12.500 1.1984 0.05899 0.05059 -0.0256 0.0372 1.0000
12.750 1.2035 0.06125 0.05293 -0.0250 0.0355 1.0000
13.000 1.2077 0.06361 0.05533 -0.0246 0.0341 1.0000
13.250 1.2135 0.06584 0.05757 -0.0238 0.0327 1.0000
13.500 1.2211 0.06805 0.06001 -0.0231 0.0317 1.0000
13.750 1.2282 0.07038 0.06254 -0.0224 0.0308 1.0000
14.000 1.2338 0.07297 0.06531 -0.0218 0.0299 1.0000
14.250 1.2377 0.07581 0.06835 -0.0215 0.0292 1.0000
14.500 1.2392 0.07897 0.07169 -0.0214 0.0286 1.0000
14.750 1.2386 0.08238 0.07527 -0.0217 0.0280 1.0000
15.000 1.2370 0.08593 0.07897 -0.0223 0.0273 1.0000
15.250 1.2349 0.08960 0.08275 -0.0230 0.0268 1.0000
15.500 1.2332 0.09328 0.08653 -0.0236 0.0262 1.0000
15.750 1.2239 0.09830 0.09177 -0.0251 0.0258 1.0000
16.000 1.2108 0.10414 0.09789 -0.0274 0.0256 1.0000
16.250 1.1962 0.11051 0.10453 -0.0303 0.0254 1.0000
16.500 1.1798 0.11750 0.11177 -0.0338 0.0253 1.0000
16.750 1.1619 0.12519 0.11971 -0.0380 0.0253 1.0000
17.000 1.1424 0.13379 0.12852 -0.0432 0.0254 1.0000
17.250 1.1207 0.14353 0.13846 -0.0493 0.0255 1.0000
17.500 1.0967 0.15475 0.14986 -0.0567 0.0256 1.0000
17.750 1.0701 0.16796 0.16319 -0.0653 0.0259 1.0000
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Polar data table (+)
Polar graphs
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