BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.91 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr9-il-1000000-n5.txt Download as CSV file: xf-vr9-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6222 0.08726 0.08567 0.0067 1.0000 0.0042
-8.250 -0.6334 0.08158 0.08003 0.0034 1.0000 0.0037
-8.000 -0.6405 0.07695 0.07542 -0.0003 1.0000 0.0037
-7.750 -0.6426 0.07159 0.07004 -0.0057 1.0000 0.0038
-7.500 -0.6434 0.06587 0.06427 -0.0096 1.0000 0.0036
-7.250 -0.6407 0.06037 0.05866 -0.0124 1.0000 0.0035
-7.000 -0.6340 0.05527 0.05344 -0.0141 1.0000 0.0034
-6.750 -0.6254 0.05008 0.04810 -0.0152 1.0000 0.0032
-6.500 -0.6145 0.04482 0.04263 -0.0156 1.0000 0.0030
-6.250 -0.6008 0.03992 0.03750 -0.0154 1.0000 0.0028
-6.000 -0.5858 0.03471 0.03200 -0.0146 1.0000 0.0026
-5.750 -0.5693 0.02940 0.02632 -0.0132 1.0000 0.0023
-5.500 -0.5519 0.02338 0.01981 -0.0111 1.0000 0.0021
-5.250 -0.5359 0.01532 0.01085 -0.0075 1.0000 0.0018
-5.000 -0.5098 0.01259 0.00774 -0.0069 0.9927 0.0017
-4.750 -0.4714 0.01128 0.00571 -0.0090 0.8063 0.0017
-4.500 -0.4495 0.01066 0.00455 -0.0077 0.7123 0.0018
-4.250 -0.4310 0.01172 0.00383 -0.0066 0.0502 0.0020
-4.000 -0.4049 0.01129 0.00331 -0.0062 0.0406 0.0028
-3.750 -0.3785 0.01101 0.00297 -0.0060 0.0376 0.0038
-3.500 -0.3516 0.01088 0.00281 -0.0059 0.0228 0.0065
-2.500 -0.2428 0.01070 0.00241 -0.0056 0.0222 0.0167
-2.000 -0.1907 0.00985 0.00136 -0.0051 0.0229 0.0203
-1.750 -0.1637 0.00971 0.00118 -0.0050 0.0229 0.0207
-1.250 -0.1093 0.00956 0.00094 -0.0049 0.0223 0.0212
-1.000 -0.0821 0.00949 0.00082 -0.0048 0.0224 0.0217
-0.750 -0.0548 0.00944 0.00073 -0.0047 0.0225 0.0222
-0.500 -0.0275 0.00942 0.00068 -0.0046 0.0227 0.0220
-0.250 -0.0001 0.00941 0.00065 -0.0046 0.0228 0.0218
0.000 0.0272 0.00941 0.00063 -0.0045 0.0229 0.0216
0.250 0.0545 0.00941 0.00064 -0.0045 0.0228 0.0214
0.500 0.0818 0.00944 0.00070 -0.0044 0.0222 0.0212
0.750 0.1090 0.00949 0.00078 -0.0043 0.0216 0.0209
1.000 0.1363 0.00953 0.00085 -0.0043 0.0212 0.0206
1.250 0.1635 0.00960 0.00093 -0.0042 0.0208 0.0204
1.500 0.1906 0.00970 0.00106 -0.0041 0.0202 0.0201
1.750 0.2175 0.00984 0.00125 -0.0040 0.0192 0.0198
2.000 0.2441 0.01009 0.00155 -0.0038 0.0172 0.0196
2.250 0.2712 0.01016 0.00166 -0.0038 0.0163 0.0195
2.500 0.2979 0.01038 0.00198 -0.0036 0.0151 0.0196
2.750 0.3245 0.01063 0.00228 -0.0034 0.0145 0.0198
3.000 0.3509 0.01094 0.00259 -0.0032 0.0143 0.0219
3.250 0.3771 0.01122 0.00299 -0.0029 0.0142 0.0363
3.500 0.4032 0.01156 0.00341 -0.0027 0.0143 0.0402
3.750 0.4295 0.01180 0.00369 -0.0025 0.0126 0.0441
4.000 0.4508 0.01017 0.00359 -0.0022 0.0107 0.6816
4.250 0.4741 0.00976 0.00369 -0.0012 0.0093 0.8126
4.500 0.5025 0.00925 0.00356 -0.0011 0.0032 0.9590
4.750 0.5457 0.00976 0.00422 -0.0047 0.0024 1.0000
5.000 0.5701 0.01038 0.00496 -0.0040 0.0023 1.0000
5.250 0.5941 0.01114 0.00586 -0.0033 0.0023 1.0000
5.500 0.6177 0.01213 0.00700 -0.0025 0.0023 1.0000
5.750 0.6408 0.01345 0.00851 -0.0015 0.0024 1.0000
6.000 0.6625 0.01584 0.01121 -0.0002 0.0025 1.0000
6.250 0.6772 0.02312 0.01935 0.0030 0.0028 1.0000
6.500 0.6918 0.02921 0.02599 0.0053 0.0030 1.0000
6.750 0.7046 0.03519 0.03240 0.0070 0.0033 1.0000
7.000 0.7155 0.04085 0.03840 0.0082 0.0035 1.0000
7.250 0.7252 0.04602 0.04383 0.0088 0.0035 1.0000
7.500 0.7325 0.05121 0.04922 0.0088 0.0034 1.0000
7.750 0.7382 0.05596 0.05413 0.0083 0.0031 1.0000
8.000 0.7393 0.06116 0.05947 0.0071 0.0031 1.0000
8.250 0.7365 0.06653 0.06495 0.0051 0.0029 1.0000
8.500 0.7234 0.07304 0.07154 0.0015 0.0033 1.0000
8.750 0.7110 0.07909 0.07759 -0.0053 0.0032 1.0000
9.000 0.7006 0.08576 0.08422 -0.0101 0.0039 1.0000
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Polar data table (+)
Polar graphs
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