BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.61 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8-il-1000000-n5.txt Download as CSV file: xf-vr8-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5881 0.08553 0.08395 -0.0075 1.0000 0.0032
-9.250 -0.5944 0.07999 0.07844 -0.0109 1.0000 0.0032
-9.000 -0.6051 0.07352 0.07200 -0.0158 1.0000 0.0032
-8.750 -0.6235 0.06666 0.06514 -0.0226 1.0000 0.0031
-8.500 -0.6346 0.06000 0.05839 -0.0264 1.0000 0.0031
-8.250 -0.6415 0.05356 0.05181 -0.0282 1.0000 0.0031
-7.750 -0.7062 0.01993 0.01610 -0.0224 1.0000 0.0032
-7.500 -0.6868 0.01832 0.01426 -0.0212 1.0000 0.0036
-7.250 -0.6653 0.01734 0.01314 -0.0203 1.0000 0.0038
-7.000 -0.6438 0.01620 0.01183 -0.0194 0.9999 0.0040
-6.750 -0.6139 0.01510 0.01056 -0.0202 0.9958 0.0044
-6.500 -0.5848 0.01385 0.00912 -0.0208 0.9910 0.0049
-6.250 -0.5542 0.01265 0.00774 -0.0217 0.9858 0.0053
-6.000 -0.5230 0.01203 0.00703 -0.0227 0.9781 0.0059
-5.750 -0.4891 0.01199 0.00698 -0.0242 0.9639 0.0065
-5.500 -0.4539 0.01172 0.00662 -0.0258 0.9386 0.0075
-5.250 -0.4305 0.01136 0.00591 -0.0247 0.8537 0.0087
-5.000 -0.4097 0.01179 0.00586 -0.0232 0.7252 0.0092
-4.750 -0.3843 0.01173 0.00557 -0.0228 0.6760 0.0102
-4.500 -0.3579 0.01169 0.00527 -0.0224 0.6409 0.0116
-4.250 -0.3327 0.01178 0.00497 -0.0220 0.5563 0.0122
-4.000 -0.3113 0.01212 0.00456 -0.0214 0.3104 0.0127
-3.750 -0.2871 0.01247 0.00434 -0.0211 0.0406 0.0135
-3.500 -0.2605 0.01219 0.00400 -0.0209 0.0353 0.0143
-3.250 -0.2332 0.01211 0.00384 -0.0208 0.0333 0.0152
-3.000 -0.2054 0.01216 0.00377 -0.0208 0.0227 0.0157
-2.750 -0.1797 0.01165 0.00324 -0.0205 0.0218 0.0162
-2.500 -0.1536 0.01123 0.00281 -0.0203 0.0215 0.0164
-2.250 -0.1270 0.01095 0.00251 -0.0202 0.0213 0.0167
-2.000 -0.1001 0.01074 0.00226 -0.0201 0.0212 0.0168
-1.750 -0.0731 0.01053 0.00203 -0.0200 0.0212 0.0173
-1.500 -0.0458 0.01041 0.00189 -0.0199 0.0202 0.0173
-1.250 -0.0184 0.01033 0.00179 -0.0199 0.0194 0.0171
-1.000 0.0089 0.01026 0.00170 -0.0198 0.0186 0.0170
-0.750 0.0363 0.01023 0.00168 -0.0198 0.0178 0.0169
-0.500 0.0637 0.01020 0.00163 -0.0198 0.0171 0.0169
-0.250 0.0912 0.01017 0.00159 -0.0197 0.0167 0.0169
0.000 0.1186 0.01017 0.00157 -0.0197 0.0165 0.0171
0.250 0.1459 0.01019 0.00157 -0.0197 0.0164 0.0173
0.500 0.1733 0.01024 0.00159 -0.0196 0.0163 0.0178
0.750 0.2006 0.01030 0.00164 -0.0196 0.0164 0.0185
1.000 0.2278 0.01040 0.00171 -0.0195 0.0165 0.0193
1.250 0.2550 0.01051 0.00181 -0.0195 0.0166 0.0199
1.500 0.2820 0.01064 0.00194 -0.0194 0.0167 0.0205
1.750 0.3090 0.01079 0.00210 -0.0194 0.0169 0.0215
2.250 0.3619 0.01129 0.00262 -0.0191 0.0173 0.0318
2.500 0.3899 0.01122 0.00257 -0.0192 0.0182 0.0326
2.750 0.4175 0.01124 0.00262 -0.0192 0.0187 0.0337
3.000 0.4445 0.01137 0.00280 -0.0192 0.0193 0.0348
3.250 0.4733 0.01115 0.00264 -0.0193 0.0214 0.0356
3.500 0.5009 0.01117 0.00270 -0.0194 0.0219 0.0374
3.750 0.5281 0.01128 0.00284 -0.0193 0.0223 0.0444
4.000 0.5539 0.01033 0.00317 -0.0199 0.0223 0.5851
4.250 0.5800 0.01022 0.00349 -0.0198 0.0222 0.7150
4.500 0.6038 0.01007 0.00381 -0.0191 0.0223 0.8498
4.750 0.6109 0.01008 0.00412 -0.0141 0.0223 0.9439
5.000 0.6337 0.01047 0.00453 -0.0132 0.0222 0.9730
5.250 0.6550 0.01090 0.00501 -0.0119 0.0218 0.9826
5.500 0.6947 0.01291 0.00685 -0.0158 0.0166 1.0000
5.750 0.7178 0.01333 0.00729 -0.0151 0.0158 1.0000
6.000 0.7398 0.01430 0.00813 -0.0143 0.0150 1.0000
6.250 0.7635 0.01464 0.00855 -0.0138 0.0140 1.0000
6.500 0.7884 0.01463 0.00869 -0.0134 0.0129 1.0000
6.750 0.8122 0.01507 0.00915 -0.0129 0.0122 1.0000
7.000 0.8358 0.01562 0.00967 -0.0124 0.0117 1.0000
7.250 0.8611 0.01557 0.00977 -0.0121 0.0109 1.0000
7.500 0.8863 0.01578 0.01023 -0.0117 0.0077 1.0000
7.750 0.9116 0.01586 0.01031 -0.0115 0.0064 1.0000
8.000 0.9362 0.01608 0.01053 -0.0112 0.0055 1.0000
8.250 0.9597 0.01653 0.01103 -0.0108 0.0047 1.0000
8.500 0.9833 0.01695 0.01149 -0.0104 0.0042 1.0000
8.750 1.0075 0.01721 0.01176 -0.0101 0.0038 1.0000
9.000 1.0303 0.01775 0.01236 -0.0095 0.0034 1.0000
9.250 1.0519 0.01857 0.01330 -0.0089 0.0033 1.0000
9.500 1.0731 0.01947 0.01433 -0.0083 0.0031 1.0000
9.750 1.0940 0.02041 0.01540 -0.0077 0.0029 1.0000
10.000 1.1141 0.02140 0.01654 -0.0070 0.0028 1.0000
10.250 1.1337 0.02246 0.01774 -0.0063 0.0026 1.0000
10.500 1.1526 0.02350 0.01892 -0.0055 0.0024 1.0000
10.750 1.1709 0.02458 0.02013 -0.0048 0.0023 1.0000
11.000 1.1880 0.02570 0.02139 -0.0039 0.0022 1.0000
11.250 1.2029 0.02703 0.02287 -0.0029 0.0021 1.0000
11.500 1.2160 0.02842 0.02443 -0.0017 0.0020 1.0000
11.750 1.2230 0.03032 0.02654 0.0000 0.0018 1.0000
12.000 1.2147 0.03321 0.02975 0.0033 0.0017 1.0000
12.250 1.2151 0.03489 0.03157 0.0055 0.0017 1.0000
12.500 1.2055 0.03761 0.03451 0.0076 0.0017 1.0000
12.750 1.1929 0.04095 0.03807 0.0085 0.0017 1.0000
13.000 1.1768 0.04516 0.04251 0.0082 0.0017 1.0000
13.250 1.1676 0.04904 0.04654 0.0070 0.0017 1.0000
13.500 1.1530 0.05411 0.05178 0.0046 0.0017 1.0000
13.750 1.1293 0.06113 0.05900 0.0008 0.0016 1.0000
14.000 1.1172 0.06686 0.06485 -0.0028 0.0016 1.0000
14.250 1.0661 0.08142 0.07968 -0.0128 0.0017 1.0000
14.500 0.9716 0.11321 0.11180 -0.0316 0.0021 1.0000
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Polar data table (+)
Polar graphs
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