BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 200,000 Max Cl/Cd: 44.12 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8b-il-200000-n5.txt Download as CSV file: xf-vr8b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6662 0.09433 0.09127 0.0244 1.0000 0.0140
-8.250 -0.6660 0.08827 0.08524 0.0189 1.0000 0.0141
-8.000 -0.6654 0.08176 0.07873 0.0112 1.0000 0.0140
-7.500 -0.6556 0.07374 0.07067 0.0050 1.0000 0.0157
-7.250 -0.6476 0.06759 0.06439 -0.0003 1.0000 0.0167
-7.000 -0.6373 0.05805 0.05449 -0.0057 1.0000 0.0139
-6.750 -0.6249 0.05375 0.05004 -0.0076 1.0000 0.0134
-6.500 -0.6090 0.04842 0.04443 -0.0095 1.0000 0.0129
-6.250 -0.5901 0.04296 0.03861 -0.0110 1.0000 0.0125
-6.000 -0.5684 0.03766 0.03286 -0.0119 1.0000 0.0124
-5.750 -0.5443 0.03269 0.02737 -0.0125 1.0000 0.0125
-5.500 -0.5179 0.02819 0.02224 -0.0127 1.0000 0.0131
-5.250 -0.4902 0.02500 0.01845 -0.0130 1.0000 0.0148
-5.000 -0.4619 0.02315 0.01619 -0.0135 1.0000 0.0173
-4.750 -0.4322 0.02090 0.01332 -0.0136 1.0000 0.0182
-4.500 -0.4041 0.01878 0.01116 -0.0141 1.0000 0.0194
-4.250 -0.3749 0.01748 0.00966 -0.0145 1.0000 0.0217
-3.750 -0.3144 0.01506 0.00712 -0.0159 0.9748 0.0245
-3.500 -0.2870 0.01442 0.00643 -0.0159 0.9580 0.0259
-3.250 -0.2613 0.01381 0.00581 -0.0155 0.9373 0.0272
-3.000 -0.2374 0.01329 0.00524 -0.0145 0.9136 0.0275
-2.750 -0.2191 0.01297 0.00479 -0.0119 0.8719 0.0279
-2.500 -0.2014 0.01276 0.00432 -0.0091 0.8224 0.0285
-2.250 -0.1793 0.01259 0.00388 -0.0074 0.7744 0.0293
-2.000 -0.1535 0.01246 0.00348 -0.0067 0.7352 0.0306
-1.750 -0.1263 0.01238 0.00313 -0.0065 0.6962 0.0326
-1.500 -0.0984 0.01234 0.00277 -0.0064 0.6392 0.0369
-1.250 -0.0695 0.01240 0.00241 -0.0067 0.5647 0.0484
-1.000 -0.0399 0.01066 0.00210 -0.0088 0.5184 0.4715
-0.750 -0.0111 0.01036 0.00201 -0.0091 0.4973 0.5690
-0.500 0.0176 0.01021 0.00194 -0.0093 0.4875 0.6185
-0.250 0.0456 0.00997 0.00190 -0.0093 0.4940 0.6719
0.000 0.0724 0.00975 0.00189 -0.0089 0.4964 0.7280
0.250 0.0983 0.00959 0.00190 -0.0082 0.4984 0.7742
0.500 0.1229 0.00947 0.00191 -0.0072 0.4958 0.8194
0.750 0.1456 0.00938 0.00191 -0.0056 0.4896 0.8706
1.000 0.1695 0.00931 0.00187 -0.0043 0.4758 0.9269
1.250 0.2001 0.00928 0.00181 -0.0049 0.4621 0.9840
1.500 0.2313 0.00936 0.00180 -0.0058 0.4385 1.0000
1.750 0.2608 0.00954 0.00184 -0.0064 0.4092 1.0000
2.000 0.2904 0.01047 0.00201 -0.0077 0.2475 1.0000
2.250 0.3202 0.01173 0.00242 -0.0093 0.0521 1.0000
2.500 0.3495 0.01193 0.00258 -0.0099 0.0489 1.0000
2.750 0.3787 0.01214 0.00276 -0.0104 0.0446 1.0000
3.000 0.4079 0.01234 0.00295 -0.0109 0.0402 1.0000
3.250 0.4370 0.01257 0.00318 -0.0114 0.0353 1.0000
3.500 0.4661 0.01280 0.00344 -0.0119 0.0334 1.0000
3.750 0.4952 0.01302 0.00375 -0.0123 0.0322 1.0000
4.000 0.5242 0.01327 0.00406 -0.0128 0.0308 1.0000
4.250 0.5531 0.01355 0.00443 -0.0132 0.0289 1.0000
4.500 0.5819 0.01390 0.00484 -0.0136 0.0278 1.0000
4.750 0.6105 0.01429 0.00533 -0.0141 0.0274 1.0000
5.000 0.6390 0.01473 0.00584 -0.0145 0.0271 1.0000
5.250 0.6673 0.01521 0.00641 -0.0149 0.0270 1.0000
5.500 0.6953 0.01576 0.00708 -0.0153 0.0269 1.0000
5.750 0.7229 0.01641 0.00784 -0.0157 0.0269 1.0000
6.000 0.7501 0.01719 0.00876 -0.0160 0.0269 1.0000
6.250 0.7766 0.01799 0.00964 -0.0163 0.0262 1.0000
6.500 0.8023 0.01891 0.01054 -0.0166 0.0247 1.0000
6.750 0.8264 0.02027 0.01191 -0.0167 0.0231 1.0000
7.000 0.8491 0.02216 0.01369 -0.0165 0.0220 1.0000
7.250 0.8722 0.02444 0.01602 -0.0162 0.0197 1.0000
7.500 0.8958 0.02675 0.01857 -0.0160 0.0170 1.0000
7.750 0.9190 0.02891 0.02124 -0.0156 0.0151 1.0000
8.000 0.9414 0.03131 0.02390 -0.0154 0.0137 1.0000
8.250 0.9613 0.03359 0.02687 -0.0149 0.0120 1.0000
8.500 0.9815 0.03523 0.02875 -0.0149 0.0106 1.0000
8.750 0.9966 0.03847 0.03258 -0.0142 0.0097 1.0000
9.000 1.0061 0.04275 0.03748 -0.0135 0.0091 1.0000
9.250 1.0104 0.04727 0.04250 -0.0129 0.0088 1.0000
9.500 1.0088 0.05202 0.04768 -0.0125 0.0086 1.0000
9.750 1.0007 0.05688 0.05289 -0.0124 0.0085 1.0000
10.000 0.9844 0.06153 0.05779 -0.0128 0.0085 1.0000
10.250 0.9657 0.06723 0.06371 -0.0159 0.0085 1.0000
10.500 0.9458 0.07449 0.07115 -0.0214 0.0087 1.0000
10.750 0.9250 0.08355 0.08036 -0.0288 0.0089 1.0000
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Polar data table (+)
Polar graphs
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