BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 50,000 Max Cl/Cd: 33.25 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7b-il-50000-n5.txt Download as CSV file: xf-vr7b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4902 0.13401 0.12773 0.0110 1.0000 0.1181
-10.500 -0.4853 0.13047 0.12422 0.0089 1.0000 0.1226
-10.250 -0.5030 0.12843 0.12229 0.0020 1.0000 0.1270
-10.000 -0.4853 0.12297 0.11685 0.0026 1.0000 0.1290
-9.750 -0.4707 0.11883 0.11270 0.0026 1.0000 0.1324
-9.500 -0.4648 0.11513 0.10903 0.0005 1.0000 0.1367
-9.250 -0.3611 0.09334 0.08754 -0.0253 1.0000 0.0723
-9.000 -0.3526 0.08929 0.08351 -0.0259 1.0000 0.0706
-8.750 -0.3515 0.08468 0.07894 -0.0280 1.0000 0.0689
-8.500 -0.4688 0.08695 0.08092 -0.0272 1.0000 0.0610
-8.250 -0.4645 0.08254 0.07655 -0.0301 1.0000 0.0599
-8.000 -0.4620 0.07766 0.07165 -0.0341 1.0000 0.0589
-7.750 -0.4604 0.07280 0.06672 -0.0379 1.0000 0.0581
-7.500 -0.4588 0.06820 0.06201 -0.0410 1.0000 0.0574
-7.250 -0.4580 0.06408 0.05775 -0.0428 1.0000 0.0569
-7.000 -0.4608 0.06076 0.05428 -0.0428 1.0000 0.0564
-6.750 -0.4441 0.05591 0.04903 -0.0465 0.9863 0.0556
-6.500 -0.4184 0.05070 0.04324 -0.0508 0.9739 0.0542
-6.250 -0.3904 0.04628 0.03818 -0.0540 0.9627 0.0533
-6.000 -0.3607 0.04274 0.03405 -0.0563 0.9522 0.0530
-5.750 -0.3317 0.04004 0.03094 -0.0578 0.9414 0.0537
-5.500 -0.3047 0.03799 0.02851 -0.0586 0.9297 0.0558
-5.250 -0.2790 0.03610 0.02621 -0.0587 0.9174 0.0577
-5.000 -0.2529 0.03433 0.02403 -0.0585 0.9054 0.0588
-4.750 -0.2258 0.03273 0.02205 -0.0582 0.8947 0.0598
-4.500 -0.1992 0.03137 0.02036 -0.0576 0.8836 0.0610
-4.250 -0.1734 0.03010 0.01898 -0.0571 0.8730 0.0639
-4.000 -0.1474 0.02909 0.01788 -0.0564 0.8639 0.0681
-3.750 -0.1215 0.02820 0.01679 -0.0555 0.8540 0.0717
-3.500 -0.0966 0.02727 0.01578 -0.0547 0.8448 0.0755
-3.250 -0.0717 0.02651 0.01491 -0.0540 0.8363 0.0830
-3.000 -0.0471 0.02575 0.01412 -0.0535 0.8269 0.0920
-2.750 -0.0226 0.02498 0.01332 -0.0528 0.8192 0.1078
-2.500 0.0016 0.02388 0.01260 -0.0527 0.8098 0.1623
-2.250 0.0101 0.02157 0.01260 -0.0485 0.8030 0.6335
-2.000 0.0219 0.02156 0.01322 -0.0411 0.7940 0.8497
-1.750 0.1173 0.02147 0.01264 -0.0495 0.7889 0.9863
-1.500 0.1561 0.02133 0.01218 -0.0524 0.7790 1.0000
-1.250 0.1732 0.02123 0.01183 -0.0509 0.7707 1.0000
-1.000 0.1925 0.02133 0.01170 -0.0503 0.7599 1.0000
-0.750 0.2117 0.02139 0.01155 -0.0493 0.7513 1.0000
-0.500 0.2316 0.02151 0.01147 -0.0483 0.7424 1.0000
-0.250 0.2524 0.02169 0.01146 -0.0475 0.7335 1.0000
0.000 0.2743 0.02181 0.01139 -0.0466 0.7259 1.0000
0.250 0.2975 0.02208 0.01151 -0.0462 0.7170 1.0000
0.500 0.3211 0.02221 0.01147 -0.0454 0.7098 1.0000
0.750 0.3455 0.02254 0.01167 -0.0453 0.7008 1.0000
1.000 0.3702 0.02270 0.01169 -0.0446 0.6939 1.0000
1.250 0.3953 0.02308 0.01198 -0.0446 0.6847 1.0000
1.500 0.4206 0.02325 0.01204 -0.0440 0.6778 1.0000
1.750 0.4460 0.02369 0.01243 -0.0441 0.6685 1.0000
2.000 0.4717 0.02388 0.01253 -0.0436 0.6615 1.0000
2.250 0.4972 0.02437 0.01300 -0.0437 0.6521 1.0000
2.500 0.5232 0.02459 0.01315 -0.0432 0.6451 1.0000
2.750 0.5485 0.02513 0.01370 -0.0434 0.6355 1.0000
3.000 0.5748 0.02535 0.01389 -0.0429 0.6287 1.0000
3.250 0.5998 0.02597 0.01455 -0.0432 0.6188 1.0000
3.500 0.6263 0.02617 0.01473 -0.0427 0.6121 1.0000
3.750 0.6508 0.02688 0.01552 -0.0430 0.6021 1.0000
4.000 0.6776 0.02704 0.01568 -0.0424 0.5956 1.0000
4.250 0.7015 0.02783 0.01656 -0.0428 0.5852 1.0000
4.500 0.7288 0.02792 0.01665 -0.0421 0.5791 1.0000
4.750 0.7518 0.02878 0.01767 -0.0424 0.5681 1.0000
5.000 0.7776 0.02914 0.01808 -0.0421 0.5605 1.0000
5.250 0.8019 0.02968 0.01873 -0.0419 0.5510 1.0000
5.500 0.8256 0.03026 0.01945 -0.0417 0.5409 1.0000
5.750 0.8532 0.03014 0.01938 -0.0408 0.5328 1.0000
6.000 0.8755 0.03076 0.02014 -0.0406 0.5204 1.0000
6.250 0.8991 0.03119 0.02069 -0.0401 0.5095 1.0000
6.500 0.9270 0.03108 0.02069 -0.0393 0.5014 1.0000
6.750 0.9481 0.03185 0.02165 -0.0391 0.4892 1.0000
7.000 0.9708 0.03231 0.02226 -0.0385 0.4772 1.0000
7.250 0.9958 0.03241 0.02251 -0.0377 0.4657 1.0000
7.500 1.0223 0.03227 0.02247 -0.0368 0.4542 1.0000
7.750 1.0431 0.03283 0.02323 -0.0362 0.4401 1.0000
8.000 1.0647 0.03312 0.02369 -0.0353 0.4248 1.0000
8.250 1.0858 0.03317 0.02386 -0.0341 0.4063 1.0000
8.500 1.1023 0.03357 0.02438 -0.0329 0.3843 1.0000
8.750 1.1210 0.03371 0.02454 -0.0315 0.3623 1.0000
9.000 1.1328 0.03473 0.02573 -0.0304 0.3398 1.0000
9.250 1.1454 0.03563 0.02672 -0.0292 0.3180 1.0000
9.500 1.1548 0.03682 0.02800 -0.0280 0.2955 1.0000
9.750 1.1605 0.03820 0.02937 -0.0265 0.2724 1.0000
10.000 1.1616 0.04002 0.03117 -0.0251 0.2491 1.0000
10.250 1.1620 0.04208 0.03314 -0.0239 0.2269 1.0000
10.500 1.1609 0.04457 0.03559 -0.0231 0.2059 1.0000
10.750 1.1588 0.04727 0.03818 -0.0224 0.1875 1.0000
11.000 1.1569 0.05012 0.04096 -0.0219 0.1715 1.0000
11.250 1.1552 0.05310 0.04391 -0.0215 0.1569 1.0000
11.500 1.1539 0.05612 0.04694 -0.0213 0.1441 1.0000
11.750 1.1533 0.05912 0.04994 -0.0211 0.1335 1.0000
12.000 1.1527 0.06207 0.05279 -0.0209 0.1244 1.0000
12.250 1.1528 0.06522 0.05609 -0.0209 0.1152 1.0000
12.500 1.1534 0.06826 0.05919 -0.0208 0.1078 1.0000
12.750 1.1536 0.07139 0.06239 -0.0209 0.1008 1.0000
13.000 1.1550 0.07448 0.06557 -0.0208 0.0951 1.0000
13.250 1.1556 0.07773 0.06896 -0.0210 0.0897 1.0000
13.500 1.1596 0.08036 0.07154 -0.0207 0.0850 1.0000
13.750 1.1575 0.08443 0.07593 -0.0213 0.0812 1.0000
14.000 1.1564 0.08821 0.07989 -0.0219 0.0776 1.0000
14.250 1.1640 0.09038 0.08198 -0.0214 0.0738 1.0000
14.500 1.1555 0.09567 0.08756 -0.0230 0.0716 1.0000
14.750 1.1429 0.10184 0.09405 -0.0254 0.0699 1.0000
15.000 1.1281 0.10867 0.10114 -0.0284 0.0686 1.0000
15.250 1.1089 0.11672 0.10945 -0.0323 0.0679 1.0000
15.500 1.0808 0.12744 0.12040 -0.0383 0.0677 1.0000
15.750 1.0347 0.14417 0.13729 -0.0483 0.0686 1.0000
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Polar data table (+)
Polar graphs
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