BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.92 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr12-il-1000000-n5.txt Download as CSV file: xf-vr12-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 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
------ -------- --------- --------- -------- -------- --------
-13.250 -1.1230 0.03843 0.03557 -0.0333 1.0000 0.0038
-13.000 -1.1357 0.03335 0.03012 -0.0308 1.0000 0.0038
-12.750 -1.1311 0.03042 0.02694 -0.0290 1.0000 0.0039
-12.000 -1.0941 0.02486 0.02079 -0.0242 0.9639 0.0041
-11.750 -1.0794 0.02360 0.01937 -0.0224 0.9570 0.0042
-11.500 -1.0620 0.02244 0.01806 -0.0209 0.9507 0.0043
-11.250 -1.0443 0.02144 0.01692 -0.0194 0.9449 0.0044
-11.000 -1.0239 0.02049 0.01585 -0.0183 0.9395 0.0045
-10.750 -1.0033 0.01964 0.01488 -0.0172 0.9339 0.0046
-10.500 -0.9822 0.01886 0.01399 -0.0161 0.9290 0.0048
-10.250 -0.9597 0.01812 0.01315 -0.0153 0.9235 0.0050
-10.000 -0.9373 0.01745 0.01237 -0.0143 0.9176 0.0052
-9.750 -0.9142 0.01683 0.01165 -0.0135 0.9122 0.0054
-9.500 -0.8905 0.01623 0.01096 -0.0128 0.9063 0.0057
-9.250 -0.8672 0.01561 0.01026 -0.0119 0.9009 0.0062
-9.000 -0.8427 0.01507 0.00966 -0.0113 0.8956 0.0067
-8.750 -0.8180 0.01459 0.00910 -0.0107 0.8899 0.0073
-8.500 -0.7933 0.01415 0.00858 -0.0100 0.8844 0.0078
-8.250 -0.7676 0.01373 0.00812 -0.0096 0.8786 0.0085
-8.000 -0.7420 0.01336 0.00770 -0.0091 0.8724 0.0092
-7.750 -0.7162 0.01301 0.00728 -0.0086 0.8669 0.0098
-7.500 -0.6899 0.01266 0.00689 -0.0083 0.8610 0.0104
-7.250 -0.6635 0.01239 0.00658 -0.0079 0.8552 0.0111
-7.000 -0.6368 0.01212 0.00628 -0.0076 0.8496 0.0118
-6.750 -0.6100 0.01185 0.00596 -0.0073 0.8430 0.0125
-6.500 -0.5834 0.01159 0.00564 -0.0070 0.8370 0.0130
-6.250 -0.5561 0.01138 0.00542 -0.0068 0.8309 0.0138
-6.000 -0.5288 0.01120 0.00522 -0.0066 0.8243 0.0144
-5.750 -0.5014 0.01101 0.00499 -0.0064 0.8177 0.0152
-5.500 -0.4742 0.01080 0.00473 -0.0061 0.8106 0.0158
-5.250 -0.4469 0.01059 0.00447 -0.0059 0.8047 0.0163
-5.000 -0.4194 0.01040 0.00427 -0.0058 0.7991 0.0170
-4.750 -0.3918 0.01024 0.00409 -0.0056 0.7934 0.0177
-4.500 -0.3639 0.01011 0.00394 -0.0055 0.7879 0.0187
-4.250 -0.3359 0.01001 0.00380 -0.0054 0.7795 0.0197
-4.000 -0.3080 0.00992 0.00366 -0.0053 0.7700 0.0203
-3.750 -0.2811 0.00966 0.00337 -0.0050 0.7607 0.0216
-3.500 -0.2533 0.00949 0.00318 -0.0049 0.7526 0.0223
-3.250 -0.2257 0.00934 0.00298 -0.0047 0.7437 0.0230
-3.000 -0.1978 0.00917 0.00279 -0.0046 0.7333 0.0237
-2.750 -0.1700 0.00903 0.00260 -0.0045 0.7225 0.0243
-2.500 -0.1420 0.00892 0.00244 -0.0044 0.7108 0.0249
-2.250 -0.1143 0.00876 0.00224 -0.0042 0.6972 0.0260
-2.000 -0.0864 0.00864 0.00208 -0.0041 0.6824 0.0270
-1.750 -0.0584 0.00856 0.00194 -0.0041 0.6654 0.0279
-1.500 -0.0303 0.00850 0.00183 -0.0040 0.6461 0.0291
-1.250 -0.0023 0.00846 0.00173 -0.0040 0.6245 0.0301
-0.750 0.0530 0.00859 0.00156 -0.0039 0.5397 0.0337
-0.500 0.0802 0.00878 0.00154 -0.0039 0.4793 0.0371
-0.250 0.1074 0.00892 0.00154 -0.0038 0.4340 0.0445
0.000 0.1338 0.00906 0.00155 -0.0037 0.3729 0.0741
0.250 0.1596 0.00900 0.00155 -0.0034 0.3315 0.1505
0.500 0.1838 0.00871 0.00155 -0.0030 0.3025 0.2897
0.750 0.2042 0.00804 0.00153 -0.0018 0.2786 0.5287
1.000 0.2163 0.00707 0.00152 0.0015 0.2631 0.8225
1.250 0.2677 0.00706 0.00180 -0.0034 0.2462 0.9514
1.500 0.3069 0.00728 0.00195 -0.0058 0.2346 0.9641
1.750 0.3399 0.00749 0.00209 -0.0068 0.2259 0.9748
2.000 0.3793 0.00771 0.00223 -0.0093 0.2163 0.9796
2.250 0.4102 0.00788 0.00234 -0.0099 0.2090 0.9844
2.500 0.4433 0.00801 0.00241 -0.0112 0.2011 0.9853
2.750 0.4758 0.00813 0.00248 -0.0123 0.1937 0.9862
3.000 0.5080 0.00827 0.00256 -0.0133 0.1859 0.9873
3.250 0.5401 0.00839 0.00264 -0.0143 0.1801 0.9885
3.500 0.5712 0.00854 0.00273 -0.0151 0.1737 0.9898
3.750 0.6018 0.00866 0.00282 -0.0158 0.1688 0.9911
4.000 0.6318 0.00882 0.00293 -0.0164 0.1621 0.9924
4.250 0.6612 0.00898 0.00304 -0.0168 0.1560 0.9936
4.500 0.6917 0.00912 0.00316 -0.0175 0.1509 0.9944
4.750 0.7231 0.00927 0.00327 -0.0185 0.1459 0.9951
5.000 0.7545 0.00941 0.00339 -0.0194 0.1421 0.9958
5.250 0.7858 0.00955 0.00353 -0.0203 0.1385 0.9966
5.500 0.8166 0.00972 0.00366 -0.0211 0.1344 0.9974
5.750 0.8467 0.00990 0.00382 -0.0218 0.1302 0.9982
6.000 0.8769 0.01005 0.00397 -0.0225 0.1278 0.9989
6.250 0.9070 0.01022 0.00414 -0.0232 0.1241 0.9995
6.500 0.9360 0.01042 0.00431 -0.0237 0.1201 1.0000
6.750 0.9601 0.01062 0.00450 -0.0231 0.1164 1.0000
7.000 0.9844 0.01078 0.00468 -0.0225 0.1149 1.0000
7.250 1.0085 0.01095 0.00486 -0.0219 0.1130 1.0000
7.500 1.0324 0.01115 0.00507 -0.0213 0.1108 1.0000
7.750 1.0560 0.01136 0.00528 -0.0206 0.1081 1.0000
8.000 1.0795 0.01160 0.00551 -0.0199 0.1053 1.0000
8.250 1.1029 0.01182 0.00575 -0.0193 0.1032 1.0000
8.500 1.1264 0.01201 0.00597 -0.0186 0.1011 1.0000
8.750 1.1496 0.01224 0.00621 -0.0179 0.0985 1.0000
9.000 1.1722 0.01252 0.00648 -0.0171 0.0949 1.0000
9.250 1.1944 0.01281 0.00677 -0.0163 0.0909 1.0000
9.500 1.2171 0.01303 0.00703 -0.0155 0.0886 1.0000
9.750 1.2391 0.01332 0.00732 -0.0146 0.0844 1.0000
10.000 1.2602 0.01367 0.00764 -0.0136 0.0795 1.0000
10.250 1.2817 0.01397 0.00796 -0.0127 0.0753 1.0000
10.500 1.3013 0.01442 0.00836 -0.0115 0.0672 1.0000
11.000 1.3388 0.01538 0.00928 -0.0089 0.0548 1.0000
11.250 1.3564 0.01592 0.00980 -0.0075 0.0501 1.0000
11.500 1.3750 0.01636 0.01026 -0.0062 0.0471 1.0000
11.750 1.3917 0.01690 0.01081 -0.0047 0.0436 1.0000
12.000 1.4082 0.01743 0.01135 -0.0031 0.0406 1.0000
12.250 1.4260 0.01783 0.01180 -0.0017 0.0393 1.0000
12.500 1.4422 0.01830 0.01231 -0.0001 0.0369 1.0000
13.000 1.4642 0.01955 0.01358 0.0047 0.0304 1.0000
13.250 1.4725 0.02029 0.01432 0.0073 0.0274 1.0000
13.500 1.4835 0.02099 0.01506 0.0094 0.0255 1.0000
13.750 1.4946 0.02177 0.01588 0.0112 0.0238 1.0000
14.000 1.5049 0.02266 0.01680 0.0130 0.0223 1.0000
14.250 1.5160 0.02354 0.01774 0.0145 0.0211 1.0000
14.500 1.5273 0.02444 0.01872 0.0159 0.0202 1.0000
14.750 1.5371 0.02549 0.01982 0.0173 0.0191 1.0000
15.000 1.5451 0.02672 0.02110 0.0187 0.0179 1.0000
15.250 1.5524 0.02805 0.02249 0.0199 0.0168 1.0000
15.500 1.5603 0.02938 0.02389 0.0210 0.0159 1.0000
15.750 1.5662 0.03093 0.02551 0.0220 0.0150 1.0000
16.000 1.5705 0.03269 0.02734 0.0229 0.0141 1.0000
16.250 1.5733 0.03465 0.02938 0.0236 0.0134 1.0000
16.500 1.5763 0.03667 0.03148 0.0242 0.0129 1.0000
16.750 1.5777 0.03892 0.03382 0.0245 0.0123 1.0000
17.000 1.5766 0.04154 0.03654 0.0247 0.0117 1.0000
17.250 1.5718 0.04467 0.03976 0.0245 0.0110 1.0000
17.500 1.5644 0.04831 0.04351 0.0240 0.0105 1.0000
17.750 1.5555 0.05239 0.04770 0.0230 0.0101 1.0000
18.000 1.5443 0.05707 0.05251 0.0214 0.0097 1.0000
18.250 1.5282 0.06281 0.05839 0.0190 0.0094 1.0000
18.500 1.5060 0.06982 0.06557 0.0158 0.0094 1.0000
18.750 1.4752 0.07858 0.07452 0.0117 0.0095 1.0000
19.000 1.4326 0.08954 0.08570 0.0065 0.0099 1.0000
19.250 1.3832 0.10169 0.09807 0.0008 0.0105 1.0000
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Polar data table (+)
Polar graphs
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