BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 1,000,000 Max Cl/Cd: 52.83 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr9-il-1000000.txt Download as CSV file: xf-vr9-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-9 AIRFOIL
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 -0.6405 0.08431 0.08275 0.0050 1.0000 0.0055
-8.250 -0.6441 0.07984 0.07830 0.0018 1.0000 0.0056
-8.000 -0.6541 0.07471 0.07320 -0.0031 1.0000 0.0056
-7.750 -0.6552 0.06895 0.06738 -0.0079 1.0000 0.0056
-7.500 -0.6534 0.06354 0.06189 -0.0111 1.0000 0.0056
-7.250 -0.6486 0.05841 0.05666 -0.0133 1.0000 0.0057
-7.000 -0.6406 0.05354 0.05166 -0.0146 1.0000 0.0060
-6.750 -0.6302 0.04878 0.04674 -0.0154 1.0000 0.0062
-6.500 -0.6162 0.04399 0.04175 -0.0154 1.0000 0.0069
-5.500 -0.5494 0.02470 0.02115 -0.0107 1.0000 0.0075
-5.250 -0.5306 0.02096 0.01702 -0.0093 1.0000 0.0073
-5.000 -0.5079 0.01890 0.01463 -0.0081 1.0000 0.0076
-4.750 -0.4830 0.01834 0.01381 -0.0072 1.0000 0.0080
-4.500 -0.4623 0.01454 0.00964 -0.0056 1.0000 0.0077
-4.250 -0.4387 0.01278 0.00764 -0.0044 1.0000 0.0078
-4.000 -0.4170 0.01091 0.00567 -0.0032 1.0000 0.0089
-3.750 -0.3926 0.01054 0.00531 -0.0027 1.0000 0.0102
-3.500 -0.3683 0.01003 0.00476 -0.0019 1.0000 0.0117
-3.250 -0.3434 0.00977 0.00446 -0.0012 1.0000 0.0131
-3.000 -0.2878 0.00879 0.00291 -0.0075 0.8016 0.0184
-2.750 -0.2665 0.00880 0.00235 -0.0061 0.6583 0.0203
-2.500 -0.2443 0.00930 0.00198 -0.0054 0.4059 0.0214
-2.250 -0.2210 0.00986 0.00152 -0.0049 0.0476 0.0242
-2.000 -0.1939 0.00972 0.00129 -0.0047 0.0433 0.0247
-1.750 -0.1667 0.00962 0.00110 -0.0046 0.0419 0.0248
-1.500 -0.1394 0.00954 0.00095 -0.0045 0.0417 0.0253
-1.250 -0.1121 0.00948 0.00084 -0.0044 0.0416 0.0249
-1.000 -0.0848 0.00943 0.00076 -0.0043 0.0416 0.0245
-0.750 -0.0574 0.00940 0.00070 -0.0042 0.0408 0.0242
-0.500 -0.0300 0.00938 0.00065 -0.0041 0.0390 0.0239
-0.250 -0.0026 0.00936 0.00062 -0.0041 0.0363 0.0237
0.000 0.0246 0.00940 0.00055 -0.0040 0.0297 0.0235
0.500 0.0794 0.00941 0.00057 -0.0038 0.0271 0.0237
0.750 0.1068 0.00943 0.00061 -0.0038 0.0270 0.0246
1.000 0.1341 0.00943 0.00069 -0.0037 0.0271 0.0349
1.250 0.1615 0.00946 0.00075 -0.0036 0.0267 0.0392
1.500 0.1888 0.00950 0.00082 -0.0035 0.0261 0.0404
1.750 0.2161 0.00955 0.00091 -0.0034 0.0258 0.0420
2.000 0.2434 0.00963 0.00106 -0.0033 0.0253 0.0507
2.250 0.2645 0.00824 0.00120 -0.0028 0.0245 0.5968
2.500 0.2879 0.00795 0.00150 -0.0019 0.0232 0.7424
2.750 0.3305 0.00770 0.00208 -0.0048 0.0229 0.9894
3.000 0.3683 0.00814 0.00259 -0.0071 0.0225 1.0000
3.250 0.3925 0.00861 0.00315 -0.0063 0.0222 1.0000
3.500 0.4161 0.00915 0.00371 -0.0056 0.0193 1.0000
3.750 0.4373 0.01031 0.00489 -0.0045 0.0147 1.0000
4.000 0.4628 0.01052 0.00513 -0.0040 0.0129 1.0000
4.250 0.4874 0.01103 0.00566 -0.0034 0.0108 1.0000
4.500 0.5110 0.01180 0.00640 -0.0029 0.0096 1.0000
4.750 0.5342 0.01325 0.00796 -0.0019 0.0086 1.0000
5.000 0.5600 0.01374 0.00863 -0.0013 0.0076 1.0000
5.250 0.5844 0.01509 0.01017 -0.0004 0.0070 1.0000
5.500 0.6089 0.01606 0.01129 0.0003 0.0063 1.0000
5.750 0.6332 0.01664 0.01198 0.0006 0.0055 1.0000
6.000 0.6281 0.01189 0.00832 0.0040 0.0051 1.0000
6.250 0.6494 0.01352 0.01014 0.0047 0.0053 1.0000
8.500 0.6230 0.06869 0.06725 -0.0036 0.0080 1.0000
8.750 0.6139 0.07469 0.07323 -0.0068 0.0082 1.0000
9.000 0.6074 0.08080 0.07933 -0.0098 0.0080 1.0000
9.250 0.6028 0.08658 0.08510 -0.0123 0.0079 1.0000
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Polar data table (+)
Polar graphs
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