BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 100,000 Max Cl/Cd: 44.26 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8-il-100000.txt Download as CSV file: xf-vr8-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5498 0.09196 0.08722 -0.0074 1.0000 0.0965
-8.250 -0.5634 0.08795 0.08332 -0.0133 1.0000 0.0990
-8.000 -0.5868 0.08388 0.07920 -0.0217 1.0000 0.1002
-7.750 -0.5668 0.07890 0.07434 -0.0176 1.0000 0.1038
-7.500 -0.5613 0.07551 0.07096 -0.0181 1.0000 0.1102
-7.250 -0.5825 0.07229 0.06734 -0.0259 1.0000 0.1145
-7.000 -0.5582 0.06749 0.06289 -0.0216 1.0000 0.1241
-6.750 -0.5569 0.06324 0.05857 -0.0234 1.0000 0.1327
-6.500 -0.5535 0.05965 0.05482 -0.0247 1.0000 0.1452
-6.000 -0.5342 0.05310 0.04814 -0.0240 1.0000 0.1742
-5.750 -0.5214 0.05011 0.04520 -0.0225 1.0000 0.1915
-5.500 -0.5119 0.04739 0.04244 -0.0214 1.0000 0.2180
-5.250 -0.5006 0.04491 0.04001 -0.0194 1.0000 0.2471
-4.750 -0.4342 0.03195 0.02431 -0.0215 1.0000 0.0847
-4.500 -0.4132 0.02865 0.02076 -0.0202 1.0000 0.0806
-4.250 -0.3880 0.02679 0.01811 -0.0180 1.0000 0.0728
-4.000 -0.3648 0.02411 0.01526 -0.0169 1.0000 0.0703
-3.750 -0.3412 0.02210 0.01300 -0.0156 1.0000 0.0691
-3.500 -0.3177 0.02091 0.01156 -0.0143 1.0000 0.0715
-3.250 -0.2946 0.01962 0.01015 -0.0130 1.0000 0.0726
-3.000 -0.2727 0.01814 0.00871 -0.0117 1.0000 0.0734
-2.750 -0.2531 0.01699 0.00767 -0.0102 1.0000 0.0753
-2.500 -0.2352 0.01622 0.00696 -0.0085 1.0000 0.0784
-2.250 -0.2183 0.01568 0.00637 -0.0068 1.0000 0.0829
-2.000 -0.2023 0.01521 0.00589 -0.0053 1.0000 0.0906
-1.750 -0.1862 0.01480 0.00557 -0.0040 1.0000 0.1133
-1.500 -0.0591 0.01165 0.00542 -0.0175 1.0000 1.0000
-1.250 -0.0836 0.01194 0.00567 -0.0107 1.0000 1.0000
-1.000 -0.0353 0.01218 0.00566 -0.0161 0.9879 1.0000
-0.750 0.0207 0.01231 0.00560 -0.0225 0.9737 1.0000
-0.500 0.0755 0.01238 0.00550 -0.0284 0.9599 1.0000
-0.250 0.1512 0.01186 0.00487 -0.0368 0.9342 1.0000
0.000 0.2000 0.01150 0.00438 -0.0398 0.8998 1.0000
0.250 0.2316 0.01145 0.00422 -0.0403 0.8744 1.0000
0.500 0.2590 0.01149 0.00416 -0.0400 0.8544 1.0000
0.750 0.2843 0.01158 0.00417 -0.0393 0.8359 1.0000
1.000 0.3084 0.01171 0.00425 -0.0385 0.8183 1.0000
1.250 0.3323 0.01185 0.00435 -0.0376 0.8028 1.0000
1.500 0.3560 0.01202 0.00448 -0.0367 0.7883 1.0000
1.750 0.3781 0.01215 0.00455 -0.0352 0.7695 1.0000
2.000 0.4000 0.01229 0.00461 -0.0335 0.7498 1.0000
2.250 0.4227 0.01246 0.00480 -0.0323 0.7330 1.0000
2.500 0.4449 0.01260 0.00493 -0.0308 0.7139 1.0000
2.750 0.4672 0.01273 0.00502 -0.0293 0.6942 1.0000
3.000 0.4892 0.01285 0.00516 -0.0277 0.6718 1.0000
3.250 0.5115 0.01297 0.00527 -0.0262 0.6497 1.0000
3.500 0.5337 0.01309 0.00547 -0.0247 0.6247 1.0000
3.750 0.5555 0.01320 0.00560 -0.0230 0.5950 1.0000
4.000 0.5773 0.01331 0.00578 -0.0214 0.5600 1.0000
4.250 0.5958 0.01346 0.00576 -0.0190 0.4802 1.0000
4.500 0.6054 0.01492 0.00600 -0.0158 0.2393 1.0000
4.750 0.6170 0.01711 0.00725 -0.0137 0.0945 1.0000
5.000 0.6364 0.01818 0.00828 -0.0123 0.0812 1.0000
5.250 0.6566 0.01910 0.00931 -0.0108 0.0754 1.0000
5.500 0.6756 0.02023 0.01044 -0.0093 0.0718 1.0000
5.750 0.6950 0.02168 0.01184 -0.0078 0.0697 1.0000
6.000 0.7183 0.02306 0.01327 -0.0067 0.0686 1.0000
6.250 0.7436 0.02472 0.01506 -0.0058 0.0678 1.0000
6.500 0.7684 0.02629 0.01682 -0.0049 0.0647 1.0000
6.750 0.7938 0.02842 0.01918 -0.0040 0.0634 1.0000
7.000 0.8174 0.03063 0.02158 -0.0031 0.0609 1.0000
7.250 0.8387 0.03363 0.02475 -0.0024 0.0583 1.0000
7.500 0.8590 0.03656 0.02833 -0.0005 0.0602 1.0000
7.750 0.8719 0.04130 0.03391 0.0018 0.0650 1.0000
9.750 0.7867 0.09825 0.09366 -0.0099 0.1666 1.0000
10.000 0.7412 0.10455 0.09976 -0.0195 0.1576 1.0000
10.250 0.7606 0.10813 0.10339 -0.0172 0.1534 1.0000
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Polar data table (+)
Polar graphs
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