BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 50,000 Max Cl/Cd: 29.49 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr5-il-50000-n5.txt Download as CSV file: xf-vr5-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3980 0.11251 0.10620 -0.0198 1.0000 0.1138
-9.500 -0.3995 0.10937 0.10314 -0.0235 1.0000 0.1189
-9.250 -0.4156 0.10676 0.10067 -0.0313 1.0000 0.1211
-9.000 -0.3891 0.10160 0.09550 -0.0276 1.0000 0.1255
-8.750 -0.3821 0.09817 0.09211 -0.0292 1.0000 0.1307
-8.500 -0.4016 0.09536 0.08949 -0.0370 1.0000 0.1363
-8.250 -0.3967 0.09128 0.08549 -0.0376 1.0000 0.1388
-8.000 -0.3879 0.08815 0.08240 -0.0365 1.0000 0.1420
-7.500 -0.3909 0.07104 0.06462 -0.0593 0.9683 0.0622
-7.250 -0.3691 0.06644 0.05998 -0.0621 0.9584 0.0605
-7.000 -0.3508 0.06190 0.05522 -0.0656 0.9468 0.0589
-6.750 -0.3343 0.05769 0.05071 -0.0683 0.9344 0.0576
-6.500 -0.3173 0.05382 0.04650 -0.0702 0.9228 0.0568
-6.250 -0.2985 0.05042 0.04270 -0.0716 0.9122 0.0576
-6.000 -0.2781 0.04729 0.03911 -0.0725 0.9024 0.0589
-5.750 -0.2591 0.04450 0.03585 -0.0725 0.8916 0.0597
-5.500 -0.2373 0.04180 0.03266 -0.0725 0.8825 0.0600
-5.250 -0.2138 0.03946 0.02973 -0.0723 0.8737 0.0615
-5.000 -0.1917 0.03736 0.02730 -0.0720 0.8646 0.0641
-4.750 -0.1662 0.03554 0.02525 -0.0719 0.8573 0.0664
-4.500 -0.1423 0.03404 0.02345 -0.0714 0.8482 0.0691
-4.250 -0.1147 0.03263 0.02161 -0.0710 0.8418 0.0734
-4.000 -0.0892 0.03140 0.02001 -0.0703 0.8330 0.0756
-3.750 -0.0620 0.03009 0.01867 -0.0699 0.8270 0.0796
-3.500 -0.0372 0.02932 0.01779 -0.0692 0.8186 0.0853
-3.250 -0.0096 0.02849 0.01671 -0.0684 0.8126 0.0893
-3.000 0.0145 0.02778 0.01598 -0.0677 0.8052 0.0943
-2.750 0.0395 0.02726 0.01533 -0.0671 0.7987 0.1033
-2.500 0.0627 0.02671 0.01473 -0.0665 0.7922 0.1116
-2.250 0.0862 0.02624 0.01416 -0.0659 0.7852 0.1239
-2.000 0.1111 0.02552 0.01350 -0.0655 0.7805 0.1541
-1.750 0.1178 0.02328 0.01362 -0.0626 0.7729 0.6114
-1.500 0.1286 0.02325 0.01401 -0.0559 0.7679 0.8225
-1.250 0.2599 0.02289 0.01317 -0.0705 0.7675 1.0000
-1.000 0.2767 0.02313 0.01323 -0.0697 0.7603 1.0000
-0.750 0.2939 0.02332 0.01324 -0.0687 0.7540 1.0000
-0.500 0.3111 0.02353 0.01328 -0.0675 0.7483 1.0000
-0.250 0.3262 0.02389 0.01352 -0.0663 0.7410 1.0000
0.000 0.3453 0.02405 0.01351 -0.0651 0.7362 1.0000
0.250 0.3600 0.02457 0.01391 -0.0640 0.7290 1.0000
0.500 0.3797 0.02488 0.01408 -0.0631 0.7233 1.0000
0.750 0.4023 0.02511 0.01417 -0.0624 0.7189 1.0000
1.000 0.4198 0.02577 0.01475 -0.0618 0.7111 1.0000
1.250 0.4440 0.02605 0.01492 -0.0614 0.7064 1.0000
1.500 0.4656 0.02658 0.01538 -0.0610 0.7004 1.0000
1.750 0.4873 0.02713 0.01588 -0.0607 0.6938 1.0000
2.000 0.5137 0.02739 0.01606 -0.0605 0.6897 1.0000
2.250 0.5331 0.02821 0.01686 -0.0602 0.6823 1.0000
2.500 0.5571 0.02868 0.01731 -0.0600 0.6767 1.0000
2.750 0.5849 0.02890 0.01751 -0.0598 0.6730 1.0000
3.000 0.6015 0.03001 0.01865 -0.0596 0.6642 1.0000
3.250 0.6277 0.03037 0.01902 -0.0594 0.6594 1.0000
3.500 0.6479 0.03122 0.01992 -0.0592 0.6523 1.0000
3.750 0.6714 0.03174 0.02048 -0.0589 0.6454 1.0000
4.000 0.6953 0.03213 0.02091 -0.0584 0.6379 1.0000
4.250 0.7196 0.03239 0.02122 -0.0577 0.6292 1.0000
4.500 0.7406 0.03292 0.02184 -0.0570 0.6194 1.0000
4.750 0.7689 0.03287 0.02185 -0.0565 0.6128 1.0000
5.000 0.7865 0.03379 0.02288 -0.0559 0.6026 1.0000
5.250 0.8160 0.03369 0.02291 -0.0554 0.5970 1.0000
5.500 0.8319 0.03477 0.02411 -0.0548 0.5862 1.0000
5.750 0.8633 0.03450 0.02396 -0.0543 0.5813 1.0000
6.000 0.8776 0.03570 0.02532 -0.0536 0.5697 1.0000
6.250 0.8980 0.03637 0.02617 -0.0530 0.5605 1.0000
6.500 0.9243 0.03649 0.02645 -0.0523 0.5529 1.0000
6.750 0.9396 0.03755 0.02770 -0.0515 0.5414 1.0000
7.000 0.9732 0.03698 0.02734 -0.0509 0.5357 1.0000
7.250 0.9874 0.03795 0.02851 -0.0498 0.5223 1.0000
7.500 1.0047 0.03846 0.02922 -0.0485 0.5087 1.0000
7.750 1.0256 0.03834 0.02929 -0.0471 0.4939 1.0000
8.000 1.0514 0.03727 0.02843 -0.0452 0.4763 1.0000
8.250 1.0627 0.03745 0.02877 -0.0431 0.4538 1.0000
8.500 1.0822 0.03670 0.02815 -0.0410 0.4303 1.0000
8.750 1.0875 0.03767 0.02927 -0.0391 0.4057 1.0000
9.000 1.1018 0.03783 0.02953 -0.0373 0.3770 1.0000
9.250 1.1145 0.03809 0.02971 -0.0352 0.3406 1.0000
9.500 1.1191 0.03936 0.03081 -0.0333 0.2989 1.0000
9.750 1.1190 0.04127 0.03243 -0.0315 0.2578 1.0000
10.000 1.1141 0.04400 0.03493 -0.0302 0.2194 1.0000
10.250 1.1078 0.04713 0.03787 -0.0293 0.1823 1.0000
10.500 1.1007 0.05044 0.04091 -0.0285 0.1553 1.0000
10.750 1.0945 0.05377 0.04401 -0.0278 0.1373 1.0000
11.000 1.0904 0.05697 0.04705 -0.0271 0.1234 1.0000
11.250 1.0887 0.05996 0.04996 -0.0263 0.1119 1.0000
11.500 1.0904 0.06270 0.05274 -0.0256 0.1009 1.0000
11.750 1.0933 0.06533 0.05542 -0.0249 0.0920 1.0000
12.000 1.0961 0.06793 0.05795 -0.0242 0.0852 1.0000
12.250 1.1012 0.07046 0.06065 -0.0236 0.0780 1.0000
12.500 1.1072 0.07275 0.06289 -0.0228 0.0728 1.0000
12.750 1.1156 0.07509 0.06553 -0.0220 0.0675 1.0000
13.000 1.1253 0.07715 0.06763 -0.0211 0.0635 1.0000
13.250 1.1373 0.07926 0.06988 -0.0200 0.0599 1.0000
13.500 1.1421 0.08239 0.07333 -0.0198 0.0569 1.0000
13.750 1.1459 0.08557 0.07673 -0.0196 0.0545 1.0000
14.000 1.1505 0.08873 0.08007 -0.0195 0.0528 1.0000
14.250 1.1573 0.09173 0.08317 -0.0191 0.0513 1.0000
14.500 1.1562 0.09595 0.08762 -0.0196 0.0504 1.0000
14.750 1.1431 0.10171 0.09370 -0.0215 0.0500 1.0000
15.000 1.1272 0.10815 0.10043 -0.0242 0.0498 1.0000
15.250 1.1089 0.11536 0.10787 -0.0277 0.0497 1.0000
15.500 1.0886 0.12346 0.11619 -0.0320 0.0498 1.0000
15.750 1.0668 0.13260 0.12552 -0.0374 0.0499 1.0000
16.000 1.0444 0.14284 0.13590 -0.0437 0.0502 1.0000
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Polar data table (+)
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