BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 500,000 Max Cl/Cd: 84.79 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8b-il-500000.txt Download as CSV file: xf-vr8b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6782 0.08676 0.08486 0.0197 1.0000 0.0123
-8.000 -0.6766 0.07940 0.07742 0.0109 1.0000 0.0123
-7.750 -0.6834 0.07092 0.06886 0.0055 1.0000 0.0125
-7.500 -0.6808 0.06496 0.06279 0.0021 1.0000 0.0126
-7.250 -0.6726 0.06020 0.05792 -0.0002 1.0000 0.0128
-7.000 -0.6610 0.05565 0.05324 -0.0024 1.0000 0.0130
-6.750 -0.6465 0.05127 0.04870 -0.0042 1.0000 0.0132
-6.500 -0.6292 0.04713 0.04438 -0.0058 1.0000 0.0136
-6.250 -0.6096 0.04301 0.04003 -0.0071 1.0000 0.0141
-6.000 -0.5875 0.03889 0.03565 -0.0082 1.0000 0.0151
-5.750 -0.5574 0.03607 0.03240 -0.0080 1.0000 0.0174
-5.500 -0.5320 0.03260 0.02850 -0.0084 1.0000 0.0176
-4.500 -0.4254 0.01976 0.01449 -0.0118 1.0000 0.0269
-4.250 -0.3969 0.01934 0.01405 -0.0130 1.0000 0.0359
-4.000 -0.3632 0.01637 0.01066 -0.0129 0.9913 0.0300
-3.750 -0.3338 0.01388 0.00779 -0.0119 0.9752 0.0250
-3.500 -0.3151 0.01283 0.00670 -0.0097 0.9589 0.0268
-3.250 -0.2916 0.01191 0.00571 -0.0084 0.9416 0.0270
-3.000 -0.2692 0.01122 0.00495 -0.0069 0.9207 0.0274
-2.750 -0.2498 0.01082 0.00446 -0.0046 0.8932 0.0287
-2.500 -0.2275 0.01040 0.00388 -0.0030 0.8577 0.0294
-2.250 -0.2023 0.01008 0.00335 -0.0021 0.8170 0.0298
-2.000 -0.1752 0.00994 0.00289 -0.0017 0.7561 0.0304
-1.750 -0.1459 0.00984 0.00252 -0.0020 0.7088 0.0310
-1.500 -0.1161 0.00972 0.00226 -0.0024 0.6827 0.0320
-1.250 -0.0862 0.00962 0.00203 -0.0028 0.6600 0.0339
-1.000 -0.0563 0.00955 0.00185 -0.0033 0.6355 0.0374
-0.750 -0.0262 0.00963 0.00165 -0.0038 0.5842 0.0427
-0.500 0.0041 0.00971 0.00150 -0.0045 0.5268 0.0521
-0.250 0.0369 0.00850 0.00127 -0.0071 0.4472 0.4496
0.000 0.0717 0.00981 0.00150 -0.0103 0.0399 0.5545
0.250 0.1014 0.00960 0.00151 -0.0109 0.0375 0.6326
0.500 0.1308 0.00953 0.00151 -0.0113 0.0368 0.6713
0.750 0.1600 0.00942 0.00154 -0.0117 0.0373 0.7208
1.000 0.1865 0.00915 0.00162 -0.0112 0.0393 0.8150
1.250 0.2042 0.00895 0.00170 -0.0084 0.0420 0.9053
1.500 0.2223 0.00887 0.00169 -0.0057 0.0464 0.9651
1.750 0.2524 0.00880 0.00163 -0.0062 0.0499 1.0000
2.000 0.2823 0.00890 0.00172 -0.0067 0.0507 1.0000
2.250 0.3122 0.00901 0.00184 -0.0073 0.0505 1.0000
2.500 0.3421 0.00914 0.00197 -0.0078 0.0492 1.0000
2.750 0.3719 0.00929 0.00212 -0.0084 0.0464 1.0000
3.000 0.4018 0.00944 0.00229 -0.0089 0.0446 1.0000
3.250 0.4315 0.00961 0.00250 -0.0095 0.0404 1.0000
3.500 0.4613 0.00983 0.00274 -0.0100 0.0358 1.0000
3.750 0.4911 0.01007 0.00299 -0.0106 0.0333 1.0000
4.000 0.5208 0.01031 0.00327 -0.0111 0.0325 1.0000
4.250 0.5504 0.01059 0.00360 -0.0116 0.0318 1.0000
4.500 0.5799 0.01089 0.00395 -0.0121 0.0309 1.0000
4.750 0.6093 0.01127 0.00437 -0.0126 0.0306 1.0000
5.000 0.6387 0.01172 0.00488 -0.0132 0.0303 1.0000
5.250 0.6678 0.01225 0.00550 -0.0137 0.0301 1.0000
5.500 0.6966 0.01280 0.00609 -0.0142 0.0291 1.0000
5.750 0.7250 0.01345 0.00678 -0.0146 0.0279 1.0000
6.000 0.7521 0.01467 0.00805 -0.0150 0.0266 1.0000
6.250 0.7791 0.01578 0.00925 -0.0151 0.0259 1.0000
6.500 0.8052 0.01742 0.01100 -0.0149 0.0256 1.0000
7.000 0.8292 0.00978 0.00400 -0.0115 0.0242 1.0000
7.250 0.8504 0.01196 0.00643 -0.0115 0.0202 1.0000
7.500 0.8732 0.01360 0.00830 -0.0113 0.0183 1.0000
7.750 0.8940 0.01611 0.01081 -0.0113 0.0171 1.0000
8.000 0.9424 0.03644 0.03133 -0.0144 0.0162 1.0000
8.250 0.9588 0.03967 0.03503 -0.0139 0.0162 1.0000
8.500 0.9845 0.03720 0.03295 -0.0135 0.0130 1.0000
8.750 1.0007 0.03901 0.03473 -0.0141 0.0110 1.0000
9.000 1.0080 0.04333 0.03961 -0.0134 0.0108 1.0000
9.250 1.0092 0.04833 0.04499 -0.0129 0.0109 1.0000
9.500 1.0052 0.05331 0.05027 -0.0127 0.0110 1.0000
9.750 0.9982 0.05815 0.05527 -0.0127 0.0112 1.0000
12.500 0.6861 0.13313 0.13116 -0.0400 0.0160 1.0000
12.750 0.6783 0.13871 0.13672 -0.0422 0.0158 1.0000
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Polar data table (+)
Polar graphs
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