BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.19 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8-il-1000000.txt Download as CSV file: xf-vr8-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4682 0.11061 0.10907 0.0031 1.0000 0.0084
-10.500 -0.4673 0.10606 0.10453 0.0013 1.0000 0.0089
-6.250 -0.5444 0.02960 0.02659 -0.0230 1.0000 0.0093
-6.000 -0.5333 0.02554 0.02217 -0.0205 1.0000 0.0093
-5.750 -0.5214 0.02166 0.01790 -0.0180 1.0000 0.0089
-5.500 -0.4999 0.01766 0.01336 -0.0167 0.9988 0.0092
-5.250 -0.4517 0.01507 0.01029 -0.0213 0.9890 0.0104
-5.000 -0.4122 0.01422 0.00946 -0.0243 0.9742 0.0111
-4.750 -0.3753 0.01330 0.00842 -0.0263 0.9471 0.0119
-4.500 -0.3469 0.01261 0.00746 -0.0261 0.8934 0.0129
-4.250 -0.3234 0.01320 0.00770 -0.0248 0.8226 0.0141
-4.000 -0.3021 0.01157 0.00590 -0.0239 0.7754 0.0167
-3.750 -0.2769 0.01164 0.00573 -0.0234 0.7308 0.0207
-3.500 -0.2525 0.01075 0.00464 -0.0226 0.6946 0.0207
-3.250 -0.2286 0.00992 0.00363 -0.0218 0.6582 0.0214
-3.000 -0.2043 0.00956 0.00302 -0.0212 0.6027 0.0228
-2.750 -0.1805 0.00963 0.00260 -0.0205 0.4782 0.0234
-2.500 -0.1600 0.01072 0.00245 -0.0198 0.0459 0.0231
-2.250 -0.1330 0.01050 0.00214 -0.0196 0.0396 0.0233
-2.000 -0.1058 0.01033 0.00190 -0.0194 0.0362 0.0229
-1.750 -0.0784 0.01019 0.00169 -0.0193 0.0359 0.0225
-1.500 -0.0510 0.01007 0.00151 -0.0192 0.0355 0.0223
-1.250 -0.0234 0.00998 0.00136 -0.0192 0.0352 0.0225
-1.000 0.0042 0.00992 0.00123 -0.0191 0.0351 0.0233
-0.750 0.0318 0.00988 0.00115 -0.0190 0.0350 0.0242
-0.500 0.0593 0.00983 0.00109 -0.0190 0.0350 0.0265
-0.250 0.0870 0.00981 0.00107 -0.0190 0.0339 0.0269
0.000 0.1146 0.00980 0.00104 -0.0190 0.0325 0.0341
0.250 0.1422 0.00981 0.00098 -0.0189 0.0284 0.0366
0.500 0.1693 0.00996 0.00096 -0.0188 0.0276 0.0409
0.750 0.1973 0.00988 0.00102 -0.0189 0.0251 0.0406
1.000 0.2249 0.00990 0.00105 -0.0189 0.0245 0.0416
1.250 0.2525 0.00993 0.00110 -0.0189 0.0243 0.0449
1.500 0.2772 0.00868 0.00110 -0.0192 0.0241 0.5062
1.750 0.3036 0.00832 0.00120 -0.0192 0.0238 0.6484
2.000 0.3267 0.00777 0.00133 -0.0182 0.0234 0.8439
2.250 0.3377 0.00768 0.00153 -0.0138 0.0233 0.9407
2.500 0.3581 0.00785 0.00172 -0.0119 0.0230 0.9783
2.750 0.3969 0.00796 0.00185 -0.0143 0.0229 0.9890
3.000 0.4724 0.00809 0.00197 -0.0249 0.0232 0.9994
3.250 0.5000 0.00825 0.00214 -0.0249 0.0233 1.0000
3.500 0.5239 0.00843 0.00237 -0.0241 0.0237 1.0000
3.750 0.5479 0.00864 0.00260 -0.0234 0.0241 1.0000
4.000 0.5719 0.00885 0.00286 -0.0226 0.0245 1.0000
4.250 0.5957 0.00910 0.00315 -0.0218 0.0251 1.0000
4.500 0.6192 0.00938 0.00349 -0.0209 0.0256 1.0000
4.750 0.6424 0.00971 0.00387 -0.0200 0.0256 1.0000
5.000 0.6651 0.01010 0.00431 -0.0190 0.0252 1.0000
5.250 0.6876 0.01052 0.00478 -0.0180 0.0255 1.0000
5.500 0.7096 0.01101 0.00532 -0.0169 0.0255 1.0000
5.750 0.7308 0.01159 0.00597 -0.0157 0.0251 1.0000
6.000 0.7476 0.01282 0.00728 -0.0138 0.0236 1.0000
6.250 0.7687 0.01354 0.00806 -0.0126 0.0213 1.0000
6.500 0.7828 0.01734 0.01176 -0.0108 0.0183 1.0000
6.750 0.8081 0.01596 0.01042 -0.0105 0.0153 1.0000
7.000 0.8061 0.00693 0.00158 -0.0081 0.0131 1.0000
7.250 0.8303 0.00674 0.00158 -0.0076 0.0118 1.0000
7.500 0.8530 0.00706 0.00196 -0.0072 0.0107 1.0000
7.750 0.8757 0.00748 0.00235 -0.0069 0.0101 1.0000
8.000 0.8975 0.00901 0.00380 -0.0066 0.0096 1.0000
8.250 0.9182 0.00911 0.00433 -0.0054 0.0083 1.0000
8.500 0.9397 0.00985 0.00523 -0.0048 0.0076 1.0000
8.750 0.9606 0.01047 0.00595 -0.0042 0.0072 1.0000
9.000 0.9827 0.01075 0.00628 -0.0039 0.0069 1.0000
9.250 0.9986 0.01229 0.00802 -0.0029 0.0065 1.0000
9.500 1.0141 0.01406 0.01001 -0.0017 0.0062 1.0000
9.750 1.0258 0.01656 0.01281 -0.0002 0.0056 1.0000
10.000 1.0371 0.01865 0.01512 0.0010 0.0052 1.0000
10.250 1.0441 0.02081 0.01750 0.0027 0.0050 1.0000
10.500 1.0502 0.02283 0.01970 0.0042 0.0048 1.0000
10.750 1.0410 0.02589 0.02301 0.0072 0.0047 1.0000
11.000 1.0098 0.03017 0.02760 0.0108 0.0048 1.0000
11.250 0.9875 0.03402 0.03165 0.0116 0.0047 1.0000
11.500 0.9443 0.04164 0.03955 0.0102 0.0048 1.0000
11.750 0.9066 0.05035 0.04847 0.0068 0.0049 1.0000
12.000 0.8762 0.05962 0.05790 0.0021 0.0050 1.0000
12.250 0.8367 0.07163 0.07005 -0.0041 0.0052 1.0000
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Polar data table (+)
Polar graphs
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