BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 500,000 Max Cl/Cd: 42.65 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr9-il-500000-n5.txt Download as CSV file: xf-vr9-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6394 0.08983 0.08762 0.0092 1.0000 0.0036
-8.500 -0.6414 0.08521 0.08303 0.0065 1.0000 0.0036
-8.250 -0.6456 0.08039 0.07824 0.0032 1.0000 0.0035
-8.000 -0.6521 0.07583 0.07371 -0.0010 1.0000 0.0034
-7.750 -0.6541 0.06985 0.06769 -0.0064 1.0000 0.0034
-7.500 -0.6526 0.06426 0.06202 -0.0099 1.0000 0.0033
-7.250 -0.6488 0.05858 0.05622 -0.0125 1.0000 0.0032
-7.000 -0.6418 0.05312 0.05059 -0.0141 1.0000 0.0031
-6.750 -0.6323 0.04768 0.04494 -0.0149 1.0000 0.0030
-6.500 -0.6204 0.04219 0.03917 -0.0149 1.0000 0.0029
-6.250 -0.6064 0.03672 0.03337 -0.0144 1.0000 0.0029
-6.000 -0.5904 0.03148 0.02773 -0.0132 1.0000 0.0029
-5.750 -0.5727 0.02626 0.02204 -0.0116 1.0000 0.0030
-5.500 -0.5528 0.02178 0.01707 -0.0099 1.0000 0.0034
-5.250 -0.5309 0.01862 0.01345 -0.0085 1.0000 0.0039
-4.750 -0.4590 0.01464 0.00863 -0.0121 0.8973 0.0056
-4.500 -0.4385 0.01377 0.00723 -0.0102 0.7950 0.0060
-4.250 -0.4170 0.01320 0.00614 -0.0087 0.6963 0.0069
-4.000 -0.3934 0.01262 0.00510 -0.0077 0.6182 0.0090
-3.750 -0.3728 0.01370 0.00460 -0.0070 0.0458 0.0108
-3.500 -0.3461 0.01356 0.00437 -0.0069 0.0378 0.0142
-3.250 -0.3184 0.01362 0.00424 -0.0067 0.0355 0.0155
-3.000 -0.2955 0.01239 0.00304 -0.0062 0.0349 0.0179
-2.750 -0.2698 0.01190 0.00243 -0.0058 0.0331 0.0191
-2.500 -0.2435 0.01154 0.00195 -0.0056 0.0328 0.0203
-2.250 -0.2169 0.01131 0.00160 -0.0054 0.0325 0.0211
-2.000 -0.1900 0.01117 0.00134 -0.0053 0.0322 0.0219
-1.750 -0.1630 0.01107 0.00114 -0.0051 0.0299 0.0224
-1.500 -0.1358 0.01098 0.00092 -0.0050 0.0266 0.0238
-1.250 -0.1089 0.01106 0.00088 -0.0048 0.0265 0.0237
0.500 0.0812 0.01093 0.00047 -0.0043 0.0265 0.0229
1.000 0.1354 0.01095 0.00063 -0.0042 0.0228 0.0229
1.250 0.1626 0.01095 0.00071 -0.0041 0.0223 0.0230
1.500 0.1897 0.01099 0.00082 -0.0040 0.0214 0.0231
1.750 0.2166 0.01111 0.00103 -0.0039 0.0207 0.0233
2.250 0.2702 0.01143 0.00163 -0.0035 0.0192 0.0319
2.500 0.2968 0.01166 0.00194 -0.0033 0.0189 0.0326
2.750 0.3232 0.01191 0.00228 -0.0032 0.0188 0.0348
3.000 0.3496 0.01218 0.00270 -0.0029 0.0188 0.0362
3.250 0.3759 0.01248 0.00309 -0.0027 0.0190 0.0415
3.500 0.4020 0.01283 0.00357 -0.0024 0.0193 0.0456
3.750 0.4263 0.01356 0.00432 -0.0020 0.0177 0.0472
4.500 0.4871 0.01275 0.00584 0.0016 0.0113 0.8828
4.750 0.5366 0.01314 0.00680 -0.0028 0.0074 0.9999
5.000 0.5626 0.01319 0.00685 -0.0027 0.0059 1.0000
5.250 0.5866 0.01411 0.00793 -0.0019 0.0050 1.0000
5.500 0.6098 0.01567 0.00974 -0.0009 0.0043 1.0000
5.750 0.6327 0.01783 0.01225 0.0003 0.0037 1.0000
6.000 0.6541 0.02100 0.01590 0.0017 0.0034 1.0000
6.250 0.6730 0.02537 0.02083 0.0035 0.0033 1.0000
6.500 0.6892 0.03046 0.02644 0.0053 0.0034 1.0000
6.750 0.7025 0.03617 0.03263 0.0070 0.0035 1.0000
7.000 0.7134 0.04197 0.03882 0.0081 0.0037 1.0000
7.250 0.7218 0.04763 0.04478 0.0085 0.0039 1.0000
7.500 0.7273 0.05323 0.05063 0.0084 0.0040 1.0000
7.750 0.7297 0.05871 0.05630 0.0075 0.0041 1.0000
8.000 0.7289 0.06416 0.06189 0.0058 0.0042 1.0000
8.250 0.7244 0.06976 0.06759 0.0030 0.0043 1.0000
8.500 0.7127 0.07565 0.07353 -0.0018 0.0044 1.0000
8.750 0.7037 0.08192 0.07976 -0.0078 0.0044 1.0000
9.000 0.6989 0.08737 0.08518 -0.0115 0.0045 1.0000
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Polar data table (+)
Polar graphs
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