BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.75 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr13-il-1000000-n5.txt Download as CSV file: xf-vr13-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-13 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.4759 0.18259 0.18107 0.0269 1.0000 0.0049
-17.000 -0.4710 0.18032 0.17880 0.0257 1.0000 0.0051
-11.000 -0.9899 0.02905 0.02572 -0.0226 0.9988 0.0028
-10.750 -0.9773 0.02591 0.02224 -0.0216 0.9769 0.0029
-10.500 -0.9626 0.02396 0.02006 -0.0200 0.9673 0.0029
-10.250 -0.9460 0.02246 0.01835 -0.0185 0.9602 0.0029
-10.000 -0.9285 0.02099 0.01667 -0.0170 0.9531 0.0029
-9.750 -0.9100 0.01959 0.01506 -0.0156 0.9472 0.0031
-9.500 -0.8892 0.01848 0.01378 -0.0146 0.9414 0.0032
-9.250 -0.8681 0.01756 0.01272 -0.0134 0.9359 0.0033
-9.000 -0.8450 0.01673 0.01177 -0.0126 0.9303 0.0035
-8.750 -0.8219 0.01600 0.01093 -0.0118 0.9242 0.0036
-8.500 -0.7982 0.01535 0.01018 -0.0110 0.9189 0.0038
-8.250 -0.7737 0.01475 0.00949 -0.0104 0.9130 0.0040
-8.000 -0.7494 0.01421 0.00885 -0.0097 0.9073 0.0042
-7.750 -0.7242 0.01371 0.00826 -0.0092 0.9015 0.0044
-7.500 -0.6990 0.01325 0.00772 -0.0086 0.8952 0.0046
-7.250 -0.6740 0.01275 0.00714 -0.0080 0.8894 0.0051
-7.000 -0.6482 0.01231 0.00665 -0.0076 0.8833 0.0056
-6.750 -0.6224 0.01194 0.00621 -0.0071 0.8775 0.0063
-6.500 -0.5961 0.01158 0.00580 -0.0067 0.8717 0.0070
-6.250 -0.5698 0.01125 0.00543 -0.0063 0.8652 0.0079
-6.000 -0.5433 0.01096 0.00510 -0.0060 0.8592 0.0088
-5.750 -0.5164 0.01069 0.00480 -0.0057 0.8526 0.0097
-5.250 -0.4624 0.01024 0.00427 -0.0052 0.8388 0.0118
-4.750 -0.4077 0.00987 0.00386 -0.0048 0.8240 0.0139
-4.500 -0.3801 0.00973 0.00369 -0.0047 0.8174 0.0151
-4.250 -0.3524 0.00957 0.00351 -0.0046 0.8107 0.0162
-4.000 -0.3246 0.00951 0.00345 -0.0045 0.8023 0.0177
-3.750 -0.2967 0.00943 0.00334 -0.0044 0.7909 0.0191
-3.500 -0.2691 0.00930 0.00315 -0.0042 0.7790 0.0199
-3.250 -0.2415 0.00918 0.00297 -0.0040 0.7686 0.0203
-3.000 -0.2145 0.00891 0.00265 -0.0038 0.7579 0.0217
-2.750 -0.1867 0.00877 0.00249 -0.0037 0.7469 0.0230
-2.500 -0.1589 0.00867 0.00234 -0.0036 0.7345 0.0242
-2.250 -0.1310 0.00855 0.00218 -0.0034 0.7209 0.0252
-2.000 -0.1031 0.00845 0.00202 -0.0034 0.7069 0.0258
-1.750 -0.0751 0.00836 0.00188 -0.0033 0.6911 0.0264
-1.500 -0.0474 0.00824 0.00169 -0.0032 0.6735 0.0278
-1.250 -0.0194 0.00817 0.00157 -0.0031 0.6553 0.0294
-1.000 0.0085 0.00814 0.00148 -0.0031 0.6325 0.0314
-0.750 0.0363 0.00820 0.00139 -0.0030 0.5905 0.0331
-0.500 0.0638 0.00830 0.00133 -0.0030 0.5423 0.0378
-0.250 0.0910 0.00848 0.00131 -0.0029 0.4806 0.0467
0.000 0.1175 0.00854 0.00131 -0.0028 0.4258 0.0901
0.250 0.1432 0.00853 0.00132 -0.0026 0.3673 0.1739
0.500 0.1670 0.00823 0.00132 -0.0022 0.3205 0.3375
0.750 0.1848 0.00732 0.00129 -0.0006 0.2911 0.6505
1.000 0.2020 0.00654 0.00138 0.0020 0.2726 0.9178
1.250 0.2587 0.00681 0.00160 -0.0043 0.2523 0.9621
1.500 0.2943 0.00702 0.00174 -0.0059 0.2397 0.9754
1.750 0.3303 0.00722 0.00185 -0.0077 0.2284 0.9821
2.000 0.3687 0.00742 0.00197 -0.0100 0.2174 0.9864
2.250 0.4041 0.00754 0.00204 -0.0117 0.2087 0.9885
2.500 0.4360 0.00768 0.00210 -0.0127 0.1995 0.9901
2.750 0.4674 0.00781 0.00218 -0.0135 0.1905 0.9917
3.000 0.4980 0.00794 0.00226 -0.0142 0.1834 0.9932
3.250 0.5284 0.00807 0.00234 -0.0148 0.1765 0.9944
3.500 0.5601 0.00819 0.00242 -0.0158 0.1703 0.9950
3.750 0.5916 0.00831 0.00250 -0.0167 0.1644 0.9958
4.000 0.6227 0.00846 0.00261 -0.0175 0.1567 0.9966
4.250 0.6538 0.00860 0.00271 -0.0184 0.1499 0.9974
4.500 0.6848 0.00876 0.00282 -0.0192 0.1439 0.9983
4.750 0.7160 0.00888 0.00295 -0.0200 0.1402 0.9991
5.000 0.7470 0.00904 0.00307 -0.0209 0.1353 0.9998
5.250 0.7741 0.00921 0.00321 -0.0209 0.1298 1.0000
5.500 0.7994 0.00935 0.00335 -0.0205 0.1264 1.0000
5.750 0.8245 0.00951 0.00350 -0.0200 0.1224 1.0000
6.000 0.8493 0.00970 0.00366 -0.0195 0.1178 1.0000
6.250 0.8743 0.00985 0.00383 -0.0191 0.1153 1.0000
6.500 0.8993 0.01002 0.00401 -0.0186 0.1124 1.0000
6.750 0.9240 0.01020 0.00419 -0.0181 0.1093 1.0000
7.000 0.9484 0.01043 0.00439 -0.0175 0.1045 1.0000
7.250 0.9730 0.01062 0.00460 -0.0170 0.1015 1.0000
7.500 0.9974 0.01082 0.00481 -0.0165 0.0980 1.0000
7.750 1.0214 0.01106 0.00504 -0.0159 0.0936 1.0000
8.000 1.0454 0.01130 0.00528 -0.0153 0.0898 1.0000
8.250 1.0694 0.01153 0.00552 -0.0147 0.0850 1.0000
8.500 1.0926 0.01185 0.00580 -0.0141 0.0785 1.0000
8.750 1.1159 0.01213 0.00608 -0.0134 0.0722 1.0000
9.000 1.1380 0.01255 0.00644 -0.0126 0.0626 1.0000
9.250 1.1598 0.01298 0.00684 -0.0118 0.0552 1.0000
9.500 1.1821 0.01334 0.00720 -0.0110 0.0518 1.0000
9.750 1.2039 0.01374 0.00761 -0.0101 0.0482 1.0000
10.000 1.2261 0.01409 0.00798 -0.0093 0.0454 1.0000
10.250 1.2477 0.01447 0.00840 -0.0085 0.0420 1.0000
10.500 1.2679 0.01500 0.00891 -0.0074 0.0369 1.0000
10.750 1.2891 0.01540 0.00933 -0.0065 0.0338 1.0000
11.250 1.3283 0.01644 0.01037 -0.0044 0.0266 1.0000
11.500 1.3469 0.01703 0.01096 -0.0032 0.0236 1.0000
11.750 1.3659 0.01753 0.01150 -0.0020 0.0217 1.0000
12.000 1.3844 0.01806 0.01206 -0.0008 0.0200 1.0000
12.250 1.4017 0.01866 0.01269 0.0005 0.0184 1.0000
12.500 1.4187 0.01926 0.01334 0.0019 0.0170 1.0000
12.750 1.4360 0.01981 0.01393 0.0032 0.0164 1.0000
13.000 1.4523 0.02040 0.01460 0.0046 0.0155 1.0000
13.250 1.4670 0.02108 0.01531 0.0061 0.0145 1.0000
13.500 1.4779 0.02181 0.01609 0.0083 0.0135 1.0000
13.750 1.4882 0.02257 0.01691 0.0104 0.0127 1.0000
14.000 1.4993 0.02335 0.01775 0.0122 0.0121 1.0000
14.250 1.5095 0.02426 0.01872 0.0139 0.0112 1.0000
14.500 1.5186 0.02530 0.01982 0.0156 0.0104 1.0000
14.750 1.5265 0.02648 0.02106 0.0171 0.0097 1.0000
15.000 1.5348 0.02768 0.02234 0.0184 0.0092 1.0000
15.250 1.5421 0.02902 0.02377 0.0196 0.0085 1.0000
15.500 1.5470 0.03061 0.02544 0.0208 0.0077 1.0000
15.750 1.5496 0.03250 0.02740 0.0217 0.0070 1.0000
16.000 1.5521 0.03450 0.02949 0.0225 0.0065 1.0000
16.250 1.5528 0.03678 0.03187 0.0229 0.0059 1.0000
16.500 1.5495 0.03959 0.03477 0.0231 0.0052 1.0000
16.750 1.5438 0.04286 0.03815 0.0229 0.0046 1.0000
17.000 1.5355 0.04666 0.04206 0.0222 0.0040 1.0000
17.250 1.5235 0.05126 0.04679 0.0208 0.0036 1.0000
17.500 1.5063 0.05697 0.05266 0.0184 0.0033 1.0000
17.750 1.4848 0.06399 0.05985 0.0150 0.0033 1.0000
18.000 1.4578 0.07242 0.06847 0.0106 0.0034 1.0000
18.250 1.4234 0.08248 0.07875 0.0054 0.0039 1.0000
18.500 1.3763 0.09462 0.09111 -0.0005 0.0047 1.0000
18.750 1.3320 0.10614 0.10283 -0.0060 0.0055 1.0000
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Polar data table (+)
Polar graphs
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