BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 100,000 Max Cl/Cd: 36.33 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43012-il-100000.txt Download as CSV file: xf-v43012-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43012-1.58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3919 0.09407 0.08910 -0.0249 1.0000 0.0793
-9.000 -0.3969 0.09046 0.08555 -0.0270 1.0000 0.0811
-8.750 -0.4112 0.08636 0.08153 -0.0307 1.0000 0.0825
-8.500 -0.4333 0.08335 0.07855 -0.0315 1.0000 0.0832
-8.250 -0.4596 0.08128 0.07642 -0.0307 1.0000 0.0839
-8.000 -0.4845 0.08025 0.07519 -0.0286 1.0000 0.0844
-7.750 -0.4827 0.07533 0.07034 -0.0275 1.0000 0.0855
-7.500 -0.4615 0.07081 0.06605 -0.0264 1.0000 0.0882
-7.250 -0.4620 0.06818 0.06343 -0.0246 1.0000 0.0906
-7.000 -0.4673 0.06583 0.06100 -0.0224 1.0000 0.0937
-6.750 -0.4906 0.06755 0.06210 -0.0176 1.0000 0.0972
-6.500 -0.4826 0.06142 0.05622 -0.0167 1.0000 0.0990
-6.250 -0.4751 0.05804 0.05298 -0.0148 1.0000 0.1013
-6.000 -0.4722 0.05577 0.05068 -0.0123 1.0000 0.1046
-5.500 -0.4742 0.05189 0.04642 -0.0063 1.0000 0.1138
-5.250 -0.4682 0.04932 0.04393 -0.0041 1.0000 0.1173
-5.000 -0.4702 0.04963 0.04372 -0.0003 1.0000 0.1273
-4.750 -0.4624 0.04557 0.03992 0.0011 1.0000 0.1309
-4.500 -0.4604 0.04509 0.03910 0.0040 1.0000 0.1434
-4.250 -0.4224 0.04065 0.03478 -0.0004 0.9905 0.1634
-4.000 -0.3856 0.03754 0.03167 -0.0042 0.9787 0.2013
-3.750 -0.3467 0.03478 0.02884 -0.0076 0.9664 0.2351
-3.500 -0.3044 0.03246 0.02622 -0.0106 0.9533 0.2585
-3.250 -0.2547 0.02983 0.02344 -0.0143 0.9419 0.2706
-3.000 -0.2081 0.02747 0.02077 -0.0168 0.9283 0.2659
-2.750 -0.1524 0.02675 0.01919 -0.0191 0.9148 0.2239
-2.500 -0.0872 0.02612 0.01793 -0.0217 0.9033 0.1556
-2.250 -0.0260 0.02472 0.01618 -0.0249 0.8926 0.1203
-2.000 0.0223 0.02348 0.01470 -0.0265 0.8772 0.1069
-1.500 0.1017 0.02108 0.01207 -0.0278 0.8364 0.1005
-1.250 0.1380 0.02037 0.01122 -0.0278 0.8124 0.0981
-1.000 0.1703 0.01945 0.01028 -0.0274 0.7849 0.0980
-0.750 0.2005 0.01847 0.00932 -0.0267 0.7574 0.0990
-0.500 0.2230 0.01781 0.00867 -0.0248 0.7261 0.1031
-0.250 0.2452 0.01745 0.00816 -0.0228 0.6932 0.1083
0.000 0.2671 0.01715 0.00762 -0.0207 0.6584 0.1129
0.250 0.2889 0.01690 0.00711 -0.0188 0.6216 0.1216
0.500 0.3110 0.01666 0.00663 -0.0169 0.5840 0.1460
0.750 0.4933 0.01578 0.00730 -0.0433 0.4819 1.0000
1.000 0.5119 0.01605 0.00730 -0.0417 0.4564 1.0000
1.250 0.5311 0.01635 0.00733 -0.0401 0.4363 1.0000
1.500 0.5511 0.01669 0.00744 -0.0387 0.4196 1.0000
1.750 0.5715 0.01709 0.00763 -0.0374 0.4052 1.0000
2.000 0.5924 0.01753 0.00786 -0.0362 0.3935 1.0000
2.250 0.6134 0.01793 0.00816 -0.0350 0.3828 1.0000
2.500 0.6344 0.01838 0.00852 -0.0338 0.3736 1.0000
2.750 0.6556 0.01880 0.00882 -0.0326 0.3646 1.0000
3.000 0.6764 0.01926 0.00923 -0.0314 0.3566 1.0000
3.250 0.6974 0.01968 0.00958 -0.0302 0.3488 1.0000
3.500 0.7186 0.02018 0.01000 -0.0290 0.3419 1.0000
3.750 0.7387 0.02059 0.01041 -0.0276 0.3342 1.0000
4.000 0.7609 0.02112 0.01077 -0.0267 0.3278 1.0000
4.250 0.7797 0.02157 0.01134 -0.0251 0.3206 1.0000
4.500 0.8011 0.02205 0.01174 -0.0239 0.3146 1.0000
4.750 0.8219 0.02269 0.01236 -0.0228 0.3091 1.0000
5.000 0.8411 0.02325 0.01302 -0.0213 0.3029 1.0000
5.250 0.8629 0.02383 0.01353 -0.0203 0.2978 1.0000
5.500 0.8833 0.02463 0.01435 -0.0191 0.2931 1.0000
5.750 0.9016 0.02536 0.01524 -0.0175 0.2876 1.0000
6.000 0.9224 0.02602 0.01589 -0.0164 0.2826 1.0000
6.250 0.9442 0.02694 0.01673 -0.0155 0.2781 1.0000
6.500 0.9593 0.02780 0.01784 -0.0135 0.2725 1.0000
6.750 0.9787 0.02857 0.01867 -0.0123 0.2673 1.0000
7.000 1.0017 0.02948 0.01946 -0.0116 0.2631 1.0000
7.250 1.0144 0.03072 0.02098 -0.0095 0.2586 1.0000
7.500 1.0288 0.03190 0.02236 -0.0076 0.2541 1.0000
7.750 1.0475 0.03292 0.02345 -0.0064 0.2502 1.0000
8.000 1.0688 0.03403 0.02452 -0.0056 0.2469 1.0000
8.250 1.0799 0.03577 0.02648 -0.0035 0.2437 1.0000
8.500 1.0843 0.03768 0.02874 -0.0007 0.2405 1.0000
8.750 1.0914 0.03954 0.03086 0.0016 0.2373 1.0000
9.000 1.1039 0.04105 0.03250 0.0033 0.2344 1.0000
9.250 1.1247 0.04214 0.03358 0.0040 0.2317 1.0000
9.500 1.1467 0.04377 0.03515 0.0043 0.2293 1.0000
9.750 1.1318 0.04694 0.03877 0.0085 0.2274 1.0000
10.000 1.1082 0.05093 0.04313 0.0127 0.2260 1.0000
10.250 1.0628 0.05636 0.04889 0.0176 0.2252 1.0000
10.500 0.8774 0.07736 0.07013 0.0171 0.2282 1.0000
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Polar data table (+)
Polar graphs
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