BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 50,000 Max Cl/Cd: 31.71 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8b-il-50000-n5.txt Download as CSV file: xf-vr8b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6472 0.12045 0.11420 0.0317 1.0000 0.1179
-9.000 -0.6442 0.11641 0.11021 0.0298 1.0000 0.1215
-8.750 -0.6706 0.11386 0.10782 0.0190 1.0000 0.1272
-8.500 -0.6495 0.10798 0.10193 0.0228 1.0000 0.1294
-8.250 -0.6418 0.10353 0.09750 0.0220 1.0000 0.1315
-8.000 -0.6385 0.09913 0.09314 0.0197 1.0000 0.1336
-7.750 -0.6440 0.09461 0.08868 0.0128 1.0000 0.1400
-7.500 -0.6336 0.07923 0.07286 -0.0048 1.0000 0.0538
-7.250 -0.6235 0.07454 0.06819 -0.0054 1.0000 0.0513
-7.000 -0.6150 0.06919 0.06270 -0.0083 1.0000 0.0489
-6.750 -0.6047 0.06337 0.05660 -0.0116 1.0000 0.0463
-6.250 -0.5716 0.05284 0.04492 -0.0161 1.0000 0.0419
-6.000 -0.5512 0.04871 0.04025 -0.0171 1.0000 0.0423
-5.750 -0.5321 0.04467 0.03610 -0.0181 1.0000 0.0450
-5.500 -0.5087 0.04133 0.03239 -0.0188 1.0000 0.0471
-5.250 -0.4827 0.03776 0.02827 -0.0192 1.0000 0.0471
-5.000 -0.4552 0.03457 0.02455 -0.0195 1.0000 0.0473
-4.750 -0.4270 0.03188 0.02140 -0.0195 1.0000 0.0486
-4.500 -0.3983 0.02981 0.01886 -0.0196 1.0000 0.0529
-4.250 -0.3693 0.02784 0.01649 -0.0193 1.0000 0.0545
-4.000 -0.3418 0.02583 0.01434 -0.0189 1.0000 0.0559
-3.750 -0.3148 0.02428 0.01273 -0.0184 1.0000 0.0580
-3.500 -0.2880 0.02304 0.01136 -0.0180 1.0000 0.0608
-3.250 -0.2607 0.02206 0.01018 -0.0179 1.0000 0.0668
-3.000 -0.2340 0.02099 0.00906 -0.0180 1.0000 0.0737
-2.750 -0.2067 0.02011 0.00802 -0.0182 1.0000 0.0819
-2.500 -0.1794 0.01904 0.00701 -0.0186 1.0000 0.1029
-2.250 -0.1652 0.01600 0.00664 -0.0170 1.0000 0.5971
-2.000 -0.1561 0.01534 0.00689 -0.0099 1.0000 0.8415
-1.750 -0.1005 0.01516 0.00645 -0.0137 1.0000 0.9777
-1.500 -0.0632 0.01499 0.00597 -0.0168 1.0000 1.0000
-1.250 -0.0508 0.01503 0.00583 -0.0154 1.0000 1.0000
-1.000 -0.0183 0.01518 0.00572 -0.0176 0.9884 1.0000
-0.750 0.0259 0.01536 0.00565 -0.0218 0.9712 1.0000
-0.500 0.0674 0.01557 0.00564 -0.0252 0.9516 1.0000
-0.250 0.1016 0.01571 0.00563 -0.0268 0.9210 1.0000
0.000 0.1326 0.01582 0.00558 -0.0272 0.8919 1.0000
0.250 0.1589 0.01593 0.00553 -0.0265 0.8642 1.0000
0.500 0.1837 0.01605 0.00552 -0.0255 0.8404 1.0000
0.750 0.2081 0.01619 0.00553 -0.0245 0.8207 1.0000
1.000 0.2329 0.01635 0.00560 -0.0237 0.8017 1.0000
1.250 0.2573 0.01651 0.00567 -0.0228 0.7827 1.0000
1.500 0.2821 0.01668 0.00579 -0.0219 0.7654 1.0000
1.750 0.3080 0.01688 0.00596 -0.0215 0.7511 1.0000
2.000 0.3337 0.01708 0.00614 -0.0209 0.7359 1.0000
2.250 0.3592 0.01728 0.00634 -0.0203 0.7197 1.0000
2.500 0.3849 0.01749 0.00659 -0.0196 0.7033 1.0000
2.750 0.4112 0.01771 0.00686 -0.0192 0.6882 1.0000
3.000 0.4381 0.01796 0.00721 -0.0191 0.6745 1.0000
3.250 0.4646 0.01820 0.00754 -0.0187 0.6592 1.0000
3.500 0.4907 0.01842 0.00792 -0.0181 0.6420 1.0000
3.750 0.5171 0.01866 0.00830 -0.0177 0.6241 1.0000
4.000 0.5435 0.01889 0.00870 -0.0172 0.6023 1.0000
4.250 0.5677 0.01899 0.00884 -0.0159 0.5623 1.0000
4.500 0.5921 0.01912 0.00901 -0.0148 0.5094 1.0000
4.750 0.6158 0.01942 0.00922 -0.0137 0.4115 1.0000
5.000 0.6337 0.02126 0.00969 -0.0130 0.1951 1.0000
5.250 0.6563 0.02332 0.01117 -0.0136 0.0990 1.0000
5.500 0.6799 0.02492 0.01266 -0.0138 0.0786 1.0000
5.750 0.7037 0.02625 0.01415 -0.0136 0.0690 1.0000
6.000 0.7263 0.02769 0.01569 -0.0134 0.0630 1.0000
6.250 0.7490 0.02906 0.01737 -0.0129 0.0595 1.0000
6.500 0.7714 0.03055 0.01907 -0.0121 0.0571 1.0000
6.750 0.7942 0.03218 0.02085 -0.0112 0.0551 1.0000
7.000 0.8178 0.03414 0.02291 -0.0103 0.0534 1.0000
7.250 0.8432 0.03638 0.02542 -0.0094 0.0515 1.0000
7.500 0.8671 0.03873 0.02818 -0.0088 0.0476 1.0000
7.750 0.8901 0.04172 0.03161 -0.0082 0.0458 1.0000
8.000 0.9095 0.04482 0.03491 -0.0080 0.0429 1.0000
8.250 0.9252 0.04859 0.03930 -0.0076 0.0403 1.0000
8.500 0.9377 0.05285 0.04418 -0.0072 0.0394 1.0000
8.750 0.9453 0.05749 0.04937 -0.0070 0.0391 1.0000
9.000 0.9476 0.06235 0.05471 -0.0070 0.0390 1.0000
9.250 0.9446 0.06731 0.06006 -0.0074 0.0391 1.0000
9.500 0.9363 0.07231 0.06538 -0.0083 0.0392 1.0000
9.750 0.9227 0.07725 0.07053 -0.0096 0.0394 1.0000
10.000 0.9063 0.08257 0.07600 -0.0122 0.0397 1.0000
10.250 0.8904 0.08877 0.08229 -0.0165 0.0401 1.0000
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Polar data table (+)
Polar graphs
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