BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 500,000 Max Cl/Cd: 71.68 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13009-il-500000-n5.txt Download as CSV file: xf-v13009-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.9358 0.04625 0.04331 -0.0287 1.0000 0.0139
-11.000 -0.9632 0.03857 0.03506 -0.0285 1.0000 0.0140
-10.750 -0.9641 0.03452 0.03060 -0.0274 1.0000 0.0141
-10.500 -0.9559 0.03168 0.02742 -0.0263 1.0000 0.0142
-10.250 -0.9466 0.02882 0.02422 -0.0251 1.0000 0.0143
-10.000 -0.9329 0.02660 0.02173 -0.0240 1.0000 0.0145
-9.750 -0.9153 0.02501 0.01996 -0.0231 1.0000 0.0147
-9.500 -0.8958 0.02373 0.01853 -0.0223 1.0000 0.0149
-9.250 -0.8752 0.02261 0.01727 -0.0215 1.0000 0.0151
-9.000 -0.8539 0.02158 0.01611 -0.0207 1.0000 0.0152
-8.750 -0.8321 0.02062 0.01502 -0.0199 1.0000 0.0155
-8.500 -0.8099 0.01970 0.01398 -0.0191 1.0000 0.0157
-8.250 -0.7874 0.01883 0.01300 -0.0184 1.0000 0.0159
-8.000 -0.7646 0.01802 0.01206 -0.0176 1.0000 0.0162
-7.750 -0.7415 0.01729 0.01124 -0.0168 1.0000 0.0166
-7.500 -0.7183 0.01662 0.01046 -0.0160 1.0000 0.0170
-7.250 -0.6950 0.01599 0.00974 -0.0151 1.0000 0.0173
-7.000 -0.6718 0.01537 0.00904 -0.0142 1.0000 0.0176
-6.750 -0.6486 0.01481 0.00840 -0.0133 1.0000 0.0178
-6.500 -0.6262 0.01412 0.00765 -0.0123 1.0000 0.0182
-6.250 -0.6035 0.01354 0.00705 -0.0113 1.0000 0.0186
-6.000 -0.5803 0.01308 0.00657 -0.0104 1.0000 0.0191
-5.750 -0.5569 0.01268 0.00614 -0.0095 1.0000 0.0196
-5.500 -0.5336 0.01230 0.00573 -0.0085 1.0000 0.0202
-5.250 -0.5032 0.01190 0.00531 -0.0091 0.9976 0.0209
-5.000 -0.4692 0.01152 0.00490 -0.0105 0.9941 0.0217
-4.750 -0.4365 0.01114 0.00449 -0.0115 0.9891 0.0227
-4.500 -0.4026 0.01078 0.00415 -0.0128 0.9846 0.0245
-4.250 -0.3708 0.01049 0.00386 -0.0136 0.9772 0.0267
-4.000 -0.3380 0.01018 0.00357 -0.0146 0.9691 0.0297
-3.750 -0.3043 0.00992 0.00332 -0.0158 0.9575 0.0336
-3.500 -0.2711 0.00967 0.00310 -0.0168 0.9402 0.0389
-3.250 -0.2395 0.00948 0.00289 -0.0173 0.9179 0.0438
-3.000 -0.2115 0.00935 0.00270 -0.0170 0.8878 0.0489
-2.750 -0.1858 0.00929 0.00251 -0.0162 0.8497 0.0536
-2.500 -0.1604 0.00924 0.00236 -0.0154 0.8133 0.0590
-2.250 -0.1340 0.00919 0.00221 -0.0149 0.7889 0.0639
-2.000 -0.1073 0.00909 0.00208 -0.0145 0.7680 0.0716
-1.750 -0.0807 0.00903 0.00195 -0.0140 0.7438 0.0793
-1.500 -0.0544 0.00899 0.00182 -0.0135 0.7128 0.0886
-1.250 -0.0281 0.00892 0.00171 -0.0131 0.6813 0.1068
-1.000 -0.0017 0.00878 0.00162 -0.0127 0.6540 0.1444
-0.750 0.0240 0.00857 0.00151 -0.0123 0.6236 0.2100
-0.500 0.0455 0.00766 0.00136 -0.0116 0.5907 0.4687
-0.250 0.0687 0.00726 0.00133 -0.0107 0.5608 0.6048
0.000 0.0929 0.00708 0.00134 -0.0098 0.5325 0.6911
0.250 0.1177 0.00700 0.00137 -0.0089 0.5070 0.7514
0.500 0.1427 0.00697 0.00140 -0.0080 0.4803 0.8011
0.750 0.1675 0.00698 0.00144 -0.0071 0.4497 0.8456
1.000 0.1926 0.00705 0.00152 -0.0061 0.4153 0.8974
1.250 0.2248 0.00722 0.00163 -0.0066 0.3820 0.9423
1.500 0.2612 0.00744 0.00172 -0.0083 0.3531 0.9650
1.750 0.2933 0.00763 0.00179 -0.0092 0.3274 0.9740
2.000 0.3265 0.00782 0.00186 -0.0103 0.3016 0.9801
2.250 0.3591 0.00804 0.00194 -0.0114 0.2750 0.9858
2.500 0.3929 0.00828 0.00203 -0.0127 0.2464 0.9901
2.750 0.4259 0.00853 0.00213 -0.0139 0.2177 0.9946
3.000 0.4604 0.00875 0.00224 -0.0155 0.1969 0.9982
3.250 0.4903 0.00895 0.00236 -0.0160 0.1854 1.0000
3.500 0.5152 0.00911 0.00247 -0.0153 0.1774 1.0000
3.750 0.5401 0.00930 0.00261 -0.0147 0.1710 1.0000
4.000 0.5653 0.00944 0.00274 -0.0141 0.1665 1.0000
4.250 0.5903 0.00962 0.00290 -0.0135 0.1611 1.0000
4.500 0.6153 0.00982 0.00307 -0.0129 0.1557 1.0000
4.750 0.6407 0.00997 0.00322 -0.0124 0.1518 1.0000
5.000 0.6658 0.01015 0.00340 -0.0118 0.1462 1.0000
5.250 0.6909 0.01036 0.00359 -0.0112 0.1399 1.0000
5.500 0.7164 0.01053 0.00376 -0.0107 0.1327 1.0000
5.750 0.7417 0.01075 0.00394 -0.0102 0.1253 1.0000
6.000 0.7671 0.01097 0.00414 -0.0097 0.1158 1.0000
6.250 0.7925 0.01121 0.00435 -0.0093 0.1063 1.0000
6.500 0.8176 0.01150 0.00459 -0.0088 0.0966 1.0000
6.750 0.8425 0.01182 0.00488 -0.0083 0.0881 1.0000
7.000 0.8676 0.01213 0.00518 -0.0078 0.0816 1.0000
7.250 0.8924 0.01249 0.00552 -0.0074 0.0756 1.0000
7.500 0.9175 0.01280 0.00584 -0.0069 0.0709 1.0000
7.750 0.9421 0.01319 0.00623 -0.0064 0.0660 1.0000
8.000 0.9672 0.01351 0.00659 -0.0060 0.0626 1.0000
8.250 0.9919 0.01387 0.00697 -0.0055 0.0588 1.0000
8.500 1.0161 0.01433 0.00741 -0.0050 0.0549 1.0000
8.750 1.0408 0.01468 0.00783 -0.0046 0.0525 1.0000
9.000 1.0652 0.01508 0.00826 -0.0041 0.0495 1.0000
9.250 1.0888 0.01558 0.00876 -0.0036 0.0464 1.0000
9.500 1.1127 0.01602 0.00926 -0.0031 0.0443 1.0000
9.750 1.1366 0.01645 0.00974 -0.0026 0.0421 1.0000
10.000 1.1600 0.01693 0.01025 -0.0021 0.0399 1.0000
10.250 1.1825 0.01752 0.01085 -0.0015 0.0376 1.0000
10.500 1.2054 0.01801 0.01142 -0.0009 0.0360 1.0000
10.750 1.2284 0.01850 0.01198 -0.0004 0.0345 1.0000
11.000 1.2507 0.01904 0.01257 0.0002 0.0329 1.0000
11.250 1.2721 0.01965 0.01322 0.0009 0.0313 1.0000
11.500 1.2925 0.02037 0.01398 0.0017 0.0297 1.0000
11.750 1.3141 0.02091 0.01463 0.0023 0.0287 1.0000
12.000 1.3349 0.02151 0.01531 0.0030 0.0274 1.0000
12.250 1.3548 0.02217 0.01604 0.0038 0.0260 1.0000
12.500 1.3733 0.02294 0.01686 0.0047 0.0247 1.0000
12.750 1.3911 0.02374 0.01774 0.0057 0.0235 1.0000
13.000 1.4092 0.02445 0.01856 0.0066 0.0223 1.0000
13.250 1.4257 0.02527 0.01945 0.0076 0.0207 1.0000
13.500 1.4398 0.02624 0.02048 0.0089 0.0191 1.0000
13.750 1.4521 0.02716 0.02150 0.0104 0.0175 1.0000
14.000 1.4608 0.02828 0.02268 0.0121 0.0158 1.0000
14.250 1.4674 0.02960 0.02409 0.0138 0.0144 1.0000
14.500 1.4718 0.03117 0.02575 0.0152 0.0131 1.0000
14.750 1.4734 0.03315 0.02782 0.0162 0.0121 1.0000
15.000 1.4742 0.03541 0.03022 0.0167 0.0114 1.0000
15.250 1.4725 0.03818 0.03313 0.0165 0.0109 1.0000
15.500 1.4682 0.04159 0.03667 0.0156 0.0104 1.0000
15.750 1.4605 0.04581 0.04104 0.0137 0.0101 1.0000
16.000 1.4487 0.05104 0.04644 0.0109 0.0099 1.0000
16.250 1.4318 0.05744 0.05302 0.0072 0.0097 1.0000
16.500 1.4091 0.06512 0.06088 0.0027 0.0097 1.0000
16.750 1.3801 0.07404 0.07000 -0.0024 0.0098 1.0000
17.000 1.3456 0.08392 0.08007 -0.0076 0.0100 1.0000
17.250 1.3078 0.09441 0.09074 -0.0130 0.0103 1.0000
17.500 1.2697 0.10510 0.10159 -0.0185 0.0106 1.0000
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