BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.11 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8b-il-1000000.txt Download as CSV file: xf-vr8b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6945 0.09324 0.09189 0.0331 1.0000 0.0083
-8.250 -0.6943 0.08723 0.08590 0.0279 1.0000 0.0083
-8.000 -0.6935 0.07922 0.07789 0.0168 1.0000 0.0083
-7.750 -0.6883 0.07184 0.07041 0.0099 1.0000 0.0083
-7.500 -0.6969 0.06103 0.05942 0.0032 1.0000 0.0085
-7.250 -0.6883 0.05618 0.05445 0.0006 1.0000 0.0087
-7.000 -0.6743 0.05220 0.05034 -0.0014 1.0000 0.0088
-6.750 -0.6577 0.04798 0.04597 -0.0031 1.0000 0.0090
-6.500 -0.6389 0.04385 0.04166 -0.0046 1.0000 0.0092
-6.250 -0.6179 0.03978 0.03738 -0.0058 1.0000 0.0096
-6.000 -0.5950 0.03560 0.03295 -0.0067 1.0000 0.0100
-5.750 -0.5731 0.01976 0.01555 -0.0056 0.9885 0.0086
-5.500 -0.5504 0.01879 0.01448 -0.0050 0.9773 0.0089
-5.250 -0.5295 0.01830 0.01391 -0.0037 0.9678 0.0093
-5.000 -0.5083 0.01715 0.01259 -0.0022 0.9592 0.0096
-4.750 -0.4827 0.01614 0.01143 -0.0017 0.9504 0.0102
-4.500 -0.4563 0.01511 0.01022 -0.0012 0.9403 0.0111
-4.250 -0.4303 0.01478 0.00971 -0.0003 0.9244 0.0120
-4.000 -0.4098 0.01295 0.00771 0.0013 0.8985 0.0135
-3.750 -0.3865 0.01244 0.00703 0.0023 0.8498 0.0146
-3.500 -0.3590 0.01198 0.00631 0.0025 0.7931 0.0161
-3.250 -0.3296 0.01158 0.00565 0.0022 0.7508 0.0184
-3.000 -0.3003 0.01059 0.00459 0.0016 0.7284 0.0212
-2.750 -0.2703 0.01010 0.00397 0.0010 0.7063 0.0224
-2.500 -0.2398 0.00964 0.00334 0.0004 0.6761 0.0225
-2.250 -0.2090 0.00938 0.00285 -0.0003 0.6286 0.0232
-2.000 -0.1784 0.00913 0.00242 -0.0010 0.5944 0.0235
-1.750 -0.1480 0.00898 0.00210 -0.0016 0.5640 0.0238
-1.500 -0.1174 0.00895 0.00185 -0.0023 0.5174 0.0239
-1.250 -0.0862 0.00915 0.00166 -0.0033 0.4191 0.0239
-1.000 -0.0508 0.01035 0.00170 -0.0061 0.0395 0.0241
-0.750 -0.0209 0.01037 0.00153 -0.0066 0.0261 0.0242
-0.500 0.0084 0.01029 0.00150 -0.0070 0.0221 0.0241
-0.250 0.0380 0.01027 0.00146 -0.0074 0.0216 0.0241
0.000 0.0675 0.01026 0.00142 -0.0078 0.0214 0.0242
0.250 0.0971 0.01026 0.00141 -0.0082 0.0214 0.0249
0.500 0.1266 0.01026 0.00139 -0.0087 0.0216 0.0307
0.750 0.1562 0.01027 0.00138 -0.0091 0.0218 0.0408
1.000 0.1857 0.01030 0.00138 -0.0095 0.0220 0.0423
1.250 0.2152 0.01032 0.00141 -0.0100 0.0222 0.0490
1.500 0.2490 0.00890 0.00145 -0.0125 0.0225 0.5649
1.750 0.2794 0.00858 0.00157 -0.0134 0.0227 0.6939
2.000 0.3074 0.00819 0.00174 -0.0134 0.0230 0.8484
2.250 0.3208 0.00801 0.00186 -0.0096 0.0232 0.9606
2.500 0.3440 0.00792 0.00180 -0.0083 0.0235 1.0000
2.750 0.3741 0.00807 0.00195 -0.0089 0.0239 1.0000
4.250 0.5537 0.00906 0.00310 -0.0122 0.0262 1.0000
4.500 0.5835 0.00932 0.00339 -0.0128 0.0264 1.0000
4.750 0.6133 0.00964 0.00375 -0.0133 0.0265 1.0000
5.000 0.6430 0.01003 0.00421 -0.0139 0.0265 1.0000
5.250 0.6724 0.01052 0.00476 -0.0145 0.0257 1.0000
5.500 0.7017 0.01114 0.00544 -0.0151 0.0249 1.0000
5.750 0.7305 0.01188 0.00625 -0.0157 0.0243 1.0000
6.000 0.7585 0.01288 0.00728 -0.0162 0.0227 1.0000
6.250 0.7850 0.01426 0.00875 -0.0166 0.0187 1.0000
6.500 0.8094 0.01631 0.01072 -0.0169 0.0155 1.0000
6.750 0.8377 0.01644 0.01089 -0.0173 0.0134 1.0000
7.000 0.8635 0.01769 0.01192 -0.0175 0.0123 1.0000
7.250 0.8898 0.01882 0.01322 -0.0178 0.0110 1.0000
7.500 0.9179 0.01900 0.01363 -0.0180 0.0098 1.0000
7.750 0.9446 0.01959 0.01433 -0.0182 0.0090 1.0000
8.000 0.9715 0.01982 0.01454 -0.0186 0.0084 1.0000
8.250 0.9984 0.01987 0.01459 -0.0190 0.0081 1.0000
8.500 1.0234 0.02103 0.01594 -0.0190 0.0074 1.0000
8.750 1.0462 0.02317 0.01847 -0.0187 0.0064 1.0000
9.000 1.0704 0.02417 0.01962 -0.0187 0.0060 1.0000
9.250 1.0944 0.02497 0.02054 -0.0188 0.0057 1.0000
9.500 1.1017 0.03078 0.02704 -0.0177 0.0052 1.0000
9.750 1.1169 0.03343 0.02998 -0.0172 0.0051 1.0000
10.000 1.1248 0.03727 0.03420 -0.0165 0.0049 1.0000
10.250 1.1214 0.04254 0.03989 -0.0155 0.0047 1.0000
10.500 1.1046 0.04878 0.04653 -0.0147 0.0045 1.0000
10.750 1.0799 0.05404 0.05202 -0.0146 0.0045 1.0000
11.000 1.0557 0.06064 0.05882 -0.0182 0.0046 1.0000
11.250 1.0333 0.06850 0.06685 -0.0244 0.0046 1.0000
11.500 1.0111 0.07773 0.07622 -0.0321 0.0047 1.0000
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Polar data table (+)
Polar graphs
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