BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 500,000 Max Cl/Cd: 53.21 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8-il-500000-n5.txt Download as CSV file: xf-vr8-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5707 0.08580 0.08358 -0.0076 1.0000 0.0053
-9.000 -0.5739 0.08098 0.07879 -0.0106 1.0000 0.0053
-8.750 -0.5783 0.07607 0.07392 -0.0141 1.0000 0.0052
-8.500 -0.5895 0.07014 0.06802 -0.0202 1.0000 0.0052
-8.250 -0.5987 0.06444 0.06226 -0.0240 1.0000 0.0051
-8.000 -0.6030 0.05883 0.05655 -0.0265 1.0000 0.0051
-7.750 -0.6034 0.05354 0.05112 -0.0279 1.0000 0.0050
-7.500 -0.6032 0.04744 0.04479 -0.0283 1.0000 0.0051
-7.250 -0.5997 0.04147 0.03854 -0.0278 1.0000 0.0051
-7.000 -0.5951 0.03496 0.03163 -0.0263 1.0000 0.0051
-6.750 -0.5917 0.02692 0.02293 -0.0235 1.0000 0.0054
-6.500 -0.5770 0.02374 0.01937 -0.0218 1.0000 0.0057
-6.250 -0.5570 0.02244 0.01788 -0.0208 1.0000 0.0061
-6.000 -0.5373 0.02064 0.01582 -0.0195 1.0000 0.0065
-5.750 -0.5173 0.01852 0.01336 -0.0181 0.9999 0.0071
-5.500 -0.4860 0.01642 0.01082 -0.0189 0.9944 0.0087
-5.250 -0.4537 0.01597 0.01032 -0.0202 0.9882 0.0094
-5.000 -0.4203 0.01495 0.00910 -0.0215 0.9812 0.0106
-4.500 -0.3490 0.01339 0.00722 -0.0250 0.9405 0.0136
-4.250 -0.3177 0.01341 0.00665 -0.0251 0.8137 0.0154
-4.000 -0.2971 0.01310 0.00585 -0.0235 0.7185 0.0162
-3.750 -0.2762 0.01256 0.00500 -0.0224 0.6248 0.0171
-3.500 -0.2522 0.01222 0.00440 -0.0218 0.5653 0.0186
-3.250 -0.2277 0.01206 0.00391 -0.0212 0.4941 0.0192
-3.000 -0.2076 0.01313 0.00368 -0.0205 0.0413 0.0195
-2.750 -0.1813 0.01281 0.00329 -0.0203 0.0380 0.0199
-2.500 -0.1550 0.01245 0.00287 -0.0201 0.0366 0.0201
-2.250 -0.1288 0.01208 0.00246 -0.0199 0.0357 0.0210
-2.000 -0.1019 0.01190 0.00220 -0.0198 0.0353 0.0212
-1.750 -0.0748 0.01178 0.00204 -0.0197 0.0341 0.0210
-1.500 -0.0476 0.01168 0.00189 -0.0196 0.0332 0.0210
-1.250 -0.0204 0.01160 0.00177 -0.0196 0.0324 0.0209
-1.000 0.0069 0.01153 0.00164 -0.0195 0.0316 0.0209
-0.750 0.0342 0.01150 0.00157 -0.0194 0.0226 0.0209
-0.500 0.0615 0.01147 0.00152 -0.0194 0.0219 0.0211
-0.250 0.0887 0.01147 0.00150 -0.0193 0.0213 0.0213
0.000 0.1160 0.01148 0.00150 -0.0192 0.0207 0.0218
0.250 0.1432 0.01150 0.00152 -0.0192 0.0204 0.0226
0.750 0.1976 0.01158 0.00160 -0.0191 0.0202 0.0336
1.000 0.2248 0.01166 0.00169 -0.0190 0.0202 0.0348
1.250 0.2519 0.01175 0.00179 -0.0189 0.0202 0.0368
1.500 0.2789 0.01187 0.00191 -0.0189 0.0202 0.0376
1.750 0.3059 0.01199 0.00205 -0.0188 0.0203 0.0377
2.000 0.3329 0.01209 0.00218 -0.0187 0.0204 0.0381
2.250 0.3599 0.01220 0.00230 -0.0187 0.0206 0.0390
2.500 0.3869 0.01230 0.00243 -0.0186 0.0208 0.0405
2.750 0.4139 0.01240 0.00257 -0.0185 0.0209 0.0434
3.000 0.4409 0.01251 0.00276 -0.0185 0.0211 0.0465
3.250 0.4640 0.01098 0.00298 -0.0186 0.0213 0.6906
3.500 0.4774 0.01048 0.00322 -0.0151 0.0215 0.8951
3.750 0.4997 0.01063 0.00348 -0.0135 0.0217 0.9783
4.000 0.5319 0.01085 0.00373 -0.0147 0.0219 0.9869
4.500 0.6045 0.01142 0.00433 -0.0189 0.0223 1.0000
4.750 0.6275 0.01180 0.00475 -0.0181 0.0221 1.0000
5.000 0.6502 0.01223 0.00520 -0.0172 0.0220 1.0000
5.250 0.6731 0.01265 0.00568 -0.0164 0.0219 1.0000
5.500 0.6960 0.01312 0.00618 -0.0157 0.0219 1.0000
5.750 0.7184 0.01367 0.00677 -0.0148 0.0218 1.0000
6.000 0.7373 0.01476 0.00779 -0.0136 0.0209 1.0000
6.250 0.7568 0.01602 0.00902 -0.0125 0.0186 1.0000
6.500 0.7784 0.01740 0.01030 -0.0118 0.0171 1.0000
6.750 0.8022 0.01777 0.01087 -0.0113 0.0158 1.0000
7.000 0.8273 0.01980 0.01254 -0.0113 0.0145 1.0000
7.250 0.8484 0.01898 0.01229 -0.0102 0.0126 1.0000
7.500 0.8714 0.01971 0.01301 -0.0098 0.0117 1.0000
7.750 0.8951 0.01977 0.01350 -0.0091 0.0094 1.0000
8.000 0.9175 0.02056 0.01445 -0.0084 0.0082 1.0000
8.250 0.9397 0.02137 0.01540 -0.0078 0.0071 1.0000
8.500 0.9624 0.02182 0.01593 -0.0073 0.0065 1.0000
8.750 0.9855 0.02199 0.01614 -0.0070 0.0060 1.0000
9.000 1.0055 0.02314 0.01746 -0.0062 0.0054 1.0000
9.250 1.0242 0.02456 0.01909 -0.0052 0.0050 1.0000
9.500 1.0423 0.02587 0.02061 -0.0043 0.0046 1.0000
9.750 1.0598 0.02715 0.02207 -0.0034 0.0043 1.0000
10.000 1.0756 0.02859 0.02372 -0.0023 0.0041 1.0000
10.250 1.0901 0.03003 0.02535 -0.0012 0.0039 1.0000
10.500 1.1020 0.03164 0.02717 0.0001 0.0037 1.0000
10.750 1.1035 0.03460 0.03048 0.0021 0.0035 1.0000
11.000 1.0924 0.03844 0.03471 0.0051 0.0034 1.0000
11.250 1.0775 0.04180 0.03837 0.0080 0.0033 1.0000
11.500 1.0606 0.04552 0.04235 0.0094 0.0034 1.0000
11.750 1.0389 0.05043 0.04752 0.0088 0.0033 1.0000
12.000 1.0189 0.05593 0.05323 0.0065 0.0033 1.0000
12.250 0.9987 0.06225 0.05973 0.0027 0.0034 1.0000
12.500 0.9771 0.06975 0.06740 -0.0024 0.0034 1.0000
12.750 0.9571 0.07820 0.07598 -0.0084 0.0034 1.0000
13.000 0.9302 0.09044 0.08837 -0.0170 0.0034 1.0000
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Polar data table (+)
Polar graphs
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