BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 50,000 Max Cl/Cd: 32.49 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8b-il-50000.txt Download as CSV file: xf-vr8b-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6870 0.14621 0.13987 0.0441 1.0000 0.1671
-10.250 -0.6654 0.13976 0.13340 0.0460 1.0000 0.1758
-10.000 -0.6802 0.13831 0.13204 0.0416 1.0000 0.1814
-9.750 -0.6596 0.13231 0.12602 0.0435 1.0000 0.1921
-9.500 -0.6573 0.12834 0.12205 0.0422 1.0000 0.2001
-9.250 -0.6662 0.12608 0.11986 0.0393 1.0000 0.2098
-9.000 -0.6568 0.12169 0.11550 0.0397 1.0000 0.2233
-8.750 -0.6514 0.11778 0.11163 0.0396 1.0000 0.2374
-8.500 -0.6490 0.11418 0.10807 0.0391 1.0000 0.2521
-8.250 -0.6498 0.11087 0.10483 0.0383 1.0000 0.2672
-8.000 -0.6351 0.10615 0.10012 0.0398 1.0000 0.2853
-7.750 -0.6252 0.10245 0.09644 0.0407 1.0000 0.3062
-7.500 -0.6391 0.10033 0.09444 0.0391 1.0000 0.3250
-7.250 -0.6203 0.09606 0.09017 0.0417 1.0000 0.3525
-7.000 -0.6093 0.09247 0.08660 0.0436 1.0000 0.3808
-6.750 -0.6082 0.08973 0.08393 0.0451 1.0000 0.4109
-6.500 -0.5786 0.08525 0.07937 0.0487 1.0000 0.4500
-6.250 -0.5652 0.08219 0.07633 0.0519 1.0000 0.4948
-6.000 -0.5434 0.07825 0.07239 0.0543 1.0000 0.5348
-5.250 -0.5147 0.04475 0.03672 -0.0181 1.0000 0.1498
-5.000 -0.4842 0.04034 0.03161 -0.0195 1.0000 0.1356
-4.750 -0.4516 0.03697 0.02722 -0.0203 1.0000 0.1245
-4.500 -0.4225 0.03331 0.02330 -0.0206 1.0000 0.1198
-4.250 -0.3912 0.03043 0.01991 -0.0206 1.0000 0.1156
-4.000 -0.3603 0.02806 0.01713 -0.0204 1.0000 0.1149
-3.750 -0.3306 0.02618 0.01502 -0.0203 1.0000 0.1211
-3.500 -0.3005 0.02452 0.01308 -0.0197 1.0000 0.1246
-3.250 -0.2726 0.02273 0.01136 -0.0188 1.0000 0.1296
-3.000 -0.2445 0.02144 0.00996 -0.0181 1.0000 0.1383
-2.750 -0.2179 0.02006 0.00866 -0.0178 1.0000 0.1547
-2.500 -0.1922 0.01770 0.00719 -0.0181 1.0000 0.2513
-2.250 -0.1192 0.01566 0.00719 -0.0167 1.0000 1.0000
-2.000 -0.0994 0.01534 0.00659 -0.0168 1.0000 1.0000
-1.750 -0.0807 0.01512 0.00615 -0.0166 1.0000 1.0000
-1.500 -0.0640 0.01501 0.00584 -0.0159 1.0000 1.0000
-1.250 -0.0506 0.01500 0.00567 -0.0147 1.0000 1.0000
-1.000 -0.0398 0.01512 0.00563 -0.0131 1.0000 1.0000
-0.750 -0.0272 0.01535 0.00566 -0.0118 1.0000 1.0000
-0.500 -0.0122 0.01565 0.00579 -0.0112 1.0000 1.0000
-0.250 0.0050 0.01601 0.00600 -0.0110 1.0000 1.0000
0.000 0.0237 0.01643 0.00628 -0.0112 1.0000 1.0000
0.250 0.0432 0.01689 0.00663 -0.0115 1.0000 1.0000
0.500 0.0634 0.01739 0.00702 -0.0120 1.0000 1.0000
0.750 0.0840 0.01793 0.00749 -0.0126 1.0000 1.0000
1.000 0.1048 0.01852 0.00801 -0.0133 1.0000 1.0000
1.250 0.1532 0.01924 0.00872 -0.0191 0.9885 1.0000
1.500 0.2079 0.02003 0.00954 -0.0259 0.9740 1.0000
1.750 0.2859 0.02058 0.01022 -0.0358 0.9413 1.0000
2.000 0.3472 0.02094 0.01077 -0.0422 0.9192 1.0000
2.250 0.3839 0.02144 0.01139 -0.0443 0.9019 1.0000
2.500 0.4253 0.02161 0.01171 -0.0459 0.8779 1.0000
2.750 0.4567 0.02177 0.01202 -0.0454 0.8535 1.0000
3.000 0.4868 0.02197 0.01243 -0.0446 0.8342 1.0000
3.250 0.5112 0.02222 0.01284 -0.0429 0.8117 1.0000
3.500 0.5354 0.02223 0.01301 -0.0401 0.7900 1.0000
3.750 0.5567 0.02236 0.01331 -0.0373 0.7647 1.0000
4.000 0.5766 0.02227 0.01339 -0.0335 0.7369 1.0000
4.250 0.5937 0.02184 0.01312 -0.0281 0.7040 1.0000
4.500 0.6113 0.02144 0.01285 -0.0233 0.6642 1.0000
4.750 0.6244 0.02037 0.01168 -0.0164 0.5942 1.0000
5.000 0.6421 0.01976 0.01099 -0.0118 0.4750 1.0000
5.250 0.6523 0.02354 0.01235 -0.0097 0.1644 1.0000
5.500 0.6748 0.02565 0.01430 -0.0090 0.1377 1.0000
5.750 0.6992 0.02741 0.01606 -0.0078 0.1262 1.0000
6.000 0.7251 0.02939 0.01790 -0.0065 0.1193 1.0000
6.250 0.7541 0.03146 0.02024 -0.0055 0.1151 1.0000
6.500 0.7822 0.03386 0.02285 -0.0048 0.1104 1.0000
6.750 0.8084 0.03680 0.02592 -0.0045 0.1050 1.0000
7.000 0.8349 0.04017 0.02989 -0.0041 0.1044 1.0000
7.250 0.8593 0.04418 0.03440 -0.0038 0.1050 1.0000
7.500 0.8802 0.04842 0.03923 -0.0037 0.1048 1.0000
7.750 0.8963 0.05295 0.04441 -0.0038 0.1043 1.0000
8.000 0.9128 0.05828 0.05002 -0.0039 0.1058 1.0000
8.250 0.9076 0.06506 0.05798 -0.0060 0.1148 1.0000
8.500 0.9084 0.07162 0.06494 -0.0079 0.1227 1.0000
8.750 0.9073 0.07932 0.07288 -0.0104 0.1347 1.0000
9.000 0.8596 0.08880 0.08259 -0.0206 0.1420 1.0000
9.250 0.7798 0.11809 0.11158 -0.0590 0.3184 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il)