BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.43 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13009-il-1000000-n5.txt Download as CSV file: xf-v13009-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V(1.95)3009-1.25 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
------ -------- --------- --------- -------- -------- --------
-14.000 -1.1397 0.04809 0.04569 -0.0317 1.0000 0.0107
-13.750 -1.1664 0.04181 0.03916 -0.0348 1.0000 0.0107
-13.500 -1.1801 0.03831 0.03546 -0.0339 1.0000 0.0107
-13.250 -1.1846 0.03569 0.03265 -0.0322 1.0000 0.0107
-13.000 -1.1801 0.03341 0.03018 -0.0310 1.0000 0.0108
-12.750 -1.1711 0.03146 0.02805 -0.0298 1.0000 0.0109
-12.500 -1.1586 0.02982 0.02624 -0.0288 1.0000 0.0109
-12.250 -1.1432 0.02847 0.02475 -0.0279 1.0000 0.0110
-12.000 -1.1259 0.02728 0.02343 -0.0271 1.0000 0.0110
-11.750 -1.1143 0.02516 0.02107 -0.0258 1.0000 0.0112
-11.500 -1.0986 0.02354 0.01928 -0.0248 1.0000 0.0114
-11.250 -1.0800 0.02231 0.01793 -0.0239 1.0000 0.0115
-11.000 -1.0598 0.02129 0.01679 -0.0231 1.0000 0.0116
-10.750 -1.0386 0.02039 0.01579 -0.0224 1.0000 0.0117
-10.500 -1.0166 0.01958 0.01489 -0.0217 1.0000 0.0119
-10.250 -0.9942 0.01883 0.01405 -0.0210 1.0000 0.0120
-10.000 -0.9713 0.01812 0.01326 -0.0204 1.0000 0.0121
-9.750 -0.9483 0.01744 0.01250 -0.0197 1.0000 0.0123
-9.500 -0.9249 0.01680 0.01178 -0.0191 1.0000 0.0124
-9.250 -0.9014 0.01618 0.01109 -0.0184 1.0000 0.0125
-9.000 -0.8777 0.01559 0.01043 -0.0177 1.0000 0.0127
-8.750 -0.8539 0.01504 0.00981 -0.0171 1.0000 0.0129
-8.500 -0.8300 0.01450 0.00921 -0.0163 1.0000 0.0131
-8.250 -0.8062 0.01400 0.00865 -0.0156 1.0000 0.0132
-8.000 -0.7823 0.01353 0.00812 -0.0149 1.0000 0.0134
-7.750 -0.7585 0.01308 0.00763 -0.0141 1.0000 0.0136
-7.500 -0.7347 0.01267 0.00717 -0.0132 1.0000 0.0138
-7.250 -0.7109 0.01230 0.00674 -0.0124 1.0000 0.0139
-7.000 -0.6869 0.01197 0.00638 -0.0116 1.0000 0.0141
-6.750 -0.6634 0.01156 0.00594 -0.0107 1.0000 0.0144
-6.500 -0.6330 0.01107 0.00542 -0.0113 0.9979 0.0148
-6.250 -0.6009 0.01068 0.00501 -0.0123 0.9953 0.0152
-6.000 -0.5692 0.01034 0.00466 -0.0131 0.9922 0.0156
-5.750 -0.5377 0.01003 0.00434 -0.0139 0.9879 0.0160
-5.500 -0.5053 0.00975 0.00403 -0.0148 0.9836 0.0165
-5.250 -0.4744 0.00948 0.00375 -0.0154 0.9766 0.0170
-5.000 -0.4428 0.00923 0.00348 -0.0162 0.9686 0.0175
-4.750 -0.4109 0.00900 0.00323 -0.0169 0.9558 0.0179
-4.500 -0.3810 0.00874 0.00295 -0.0172 0.9343 0.0192
-4.250 -0.3543 0.00858 0.00273 -0.0166 0.9047 0.0205
-4.000 -0.3289 0.00850 0.00253 -0.0158 0.8702 0.0219
-3.750 -0.3036 0.00842 0.00234 -0.0151 0.8329 0.0248
-3.500 -0.2779 0.00838 0.00217 -0.0144 0.7945 0.0287
-3.250 -0.2515 0.00833 0.00203 -0.0140 0.7609 0.0335
-3.000 -0.2245 0.00825 0.00190 -0.0137 0.7379 0.0386
-2.750 -0.1972 0.00820 0.00179 -0.0134 0.7157 0.0423
-2.500 -0.1701 0.00815 0.00169 -0.0131 0.6882 0.0472
-2.250 -0.1429 0.00815 0.00159 -0.0128 0.6580 0.0506
-2.000 -0.1157 0.00814 0.00149 -0.0126 0.6284 0.0547
-1.750 -0.0884 0.00814 0.00142 -0.0124 0.5967 0.0598
-1.500 -0.0611 0.00814 0.00134 -0.0122 0.5690 0.0663
-1.250 -0.0337 0.00814 0.00128 -0.0120 0.5411 0.0741
-1.000 -0.0063 0.00812 0.00122 -0.0118 0.5153 0.0846
-0.750 0.0210 0.00811 0.00117 -0.0116 0.4876 0.1018
-0.500 0.0480 0.00805 0.00113 -0.0114 0.4603 0.1360
-0.250 0.0748 0.00797 0.00110 -0.0112 0.4287 0.1836
0.000 0.1001 0.00763 0.00104 -0.0109 0.3952 0.3159
0.250 0.1237 0.00703 0.00099 -0.0104 0.3680 0.5222
0.500 0.1494 0.00682 0.00100 -0.0100 0.3465 0.6131
0.750 0.1754 0.00671 0.00104 -0.0095 0.3254 0.6829
1.000 0.2013 0.00666 0.00108 -0.0091 0.3042 0.7403
1.250 0.2273 0.00663 0.00114 -0.0085 0.2834 0.7881
1.500 0.2534 0.00666 0.00120 -0.0080 0.2644 0.8235
1.750 0.2778 0.00663 0.00128 -0.0070 0.2448 0.8792
2.000 0.3029 0.00671 0.00141 -0.0060 0.2175 0.9370
2.250 0.3329 0.00690 0.00150 -0.0064 0.1926 0.9556
2.500 0.3639 0.00707 0.00159 -0.0070 0.1791 0.9653
2.750 0.3948 0.00721 0.00168 -0.0076 0.1702 0.9737
3.000 0.4274 0.00735 0.00177 -0.0086 0.1638 0.9793
3.250 0.4585 0.00749 0.00187 -0.0092 0.1585 0.9849
3.500 0.4915 0.00760 0.00197 -0.0103 0.1551 0.9885
3.750 0.5238 0.00772 0.00207 -0.0112 0.1511 0.9922
4.000 0.5569 0.00786 0.00218 -0.0123 0.1462 0.9952
4.250 0.5915 0.00801 0.00231 -0.0138 0.1414 0.9981
4.500 0.6239 0.00812 0.00241 -0.0148 0.1374 1.0000
4.750 0.6490 0.00829 0.00252 -0.0142 0.1294 1.0000
5.000 0.6744 0.00843 0.00265 -0.0136 0.1231 1.0000
5.250 0.6995 0.00862 0.00278 -0.0131 0.1143 1.0000
5.500 0.7247 0.00881 0.00293 -0.0125 0.1047 1.0000
5.750 0.7496 0.00904 0.00310 -0.0119 0.0942 1.0000
6.000 0.7745 0.00928 0.00331 -0.0113 0.0859 1.0000
6.250 0.7995 0.00955 0.00353 -0.0108 0.0787 1.0000
6.500 0.8248 0.00976 0.00373 -0.0103 0.0739 1.0000
6.750 0.8502 0.01000 0.00396 -0.0098 0.0693 1.0000
7.000 0.8755 0.01027 0.00421 -0.0093 0.0647 1.0000
7.250 0.9011 0.01049 0.00443 -0.0089 0.0616 1.0000
7.500 0.9265 0.01077 0.00470 -0.0085 0.0574 1.0000
7.750 0.9519 0.01105 0.00498 -0.0081 0.0539 1.0000
8.000 0.9775 0.01131 0.00524 -0.0077 0.0509 1.0000
8.250 1.0026 0.01164 0.00556 -0.0073 0.0470 1.0000
8.500 1.0279 0.01194 0.00587 -0.0069 0.0440 1.0000
8.750 1.0530 0.01226 0.00618 -0.0065 0.0409 1.0000
9.000 1.0778 0.01264 0.00655 -0.0061 0.0375 1.0000
9.250 1.1029 0.01295 0.00689 -0.0057 0.0360 1.0000
9.500 1.1280 0.01327 0.00724 -0.0053 0.0347 1.0000
9.750 1.1526 0.01364 0.00762 -0.0049 0.0329 1.0000
10.000 1.1768 0.01406 0.00805 -0.0045 0.0308 1.0000
10.250 1.2012 0.01444 0.00846 -0.0040 0.0294 1.0000
10.500 1.2257 0.01480 0.00886 -0.0036 0.0283 1.0000
10.750 1.2498 0.01519 0.00928 -0.0032 0.0271 1.0000
11.000 1.2734 0.01564 0.00975 -0.0027 0.0258 1.0000
11.250 1.2965 0.01613 0.01026 -0.0022 0.0244 1.0000
11.500 1.3198 0.01657 0.01076 -0.0017 0.0235 1.0000
11.750 1.3431 0.01700 0.01123 -0.0012 0.0224 1.0000
12.000 1.3656 0.01750 0.01176 -0.0006 0.0208 1.0000
12.250 1.3871 0.01809 0.01236 0.0000 0.0190 1.0000
12.500 1.4089 0.01862 0.01294 0.0006 0.0174 1.0000
12.750 1.4290 0.01931 0.01364 0.0014 0.0150 1.0000
13.000 1.4482 0.02006 0.01442 0.0023 0.0124 1.0000
13.250 1.4661 0.02090 0.01529 0.0032 0.0105 1.0000
13.500 1.4830 0.02179 0.01623 0.0043 0.0091 1.0000
13.750 1.4996 0.02265 0.01715 0.0054 0.0084 1.0000
14.000 1.5144 0.02360 0.01818 0.0067 0.0078 1.0000
14.250 1.5274 0.02463 0.01928 0.0081 0.0072 1.0000
14.500 1.5380 0.02561 0.02035 0.0099 0.0070 1.0000
14.750 1.5466 0.02666 0.02149 0.0118 0.0068 1.0000
15.000 1.5531 0.02789 0.02282 0.0135 0.0066 1.0000
15.250 1.5579 0.02936 0.02438 0.0150 0.0064 1.0000
15.500 1.5609 0.03112 0.02625 0.0162 0.0062 1.0000
15.750 1.5620 0.03325 0.02849 0.0168 0.0060 1.0000
16.000 1.5609 0.03586 0.03122 0.0168 0.0059 1.0000
16.250 1.5573 0.03905 0.03453 0.0161 0.0057 1.0000
16.500 1.5505 0.04299 0.03860 0.0146 0.0056 1.0000
16.750 1.5395 0.04788 0.04365 0.0122 0.0055 1.0000
17.000 1.5232 0.05399 0.04992 0.0088 0.0055 1.0000
17.250 1.5002 0.06149 0.05760 0.0044 0.0055 1.0000
17.500 1.4686 0.07064 0.06694 -0.0007 0.0055 1.0000
17.750 1.4276 0.08152 0.07802 -0.0065 0.0056 1.0000
18.000 1.3769 0.09411 0.09082 -0.0130 0.0058 1.0000
18.250 1.3231 0.10750 0.10441 -0.0198 0.0060 1.0000
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Polar data table (+)
Polar graphs
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