BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 88.4 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13009-il-1000000.txt Download as CSV file: xf-v13009-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4856 0.11817 0.11654 0.0063 1.0000 0.0188
-11.250 -0.4871 0.11409 0.11247 0.0051 1.0000 0.0195
-10.750 -0.9695 0.03360 0.03063 -0.0274 1.0000 0.0145
-10.500 -0.9618 0.03068 0.02744 -0.0263 1.0000 0.0147
-10.250 -0.9496 0.02834 0.02486 -0.0252 1.0000 0.0148
-10.000 -0.9341 0.02643 0.02275 -0.0242 1.0000 0.0150
-9.750 -0.9169 0.02474 0.02085 -0.0232 1.0000 0.0152
-9.500 -0.8985 0.02317 0.01909 -0.0222 1.0000 0.0155
-9.250 -0.8788 0.02180 0.01754 -0.0213 1.0000 0.0157
-9.000 -0.8575 0.02072 0.01632 -0.0205 1.0000 0.0161
-8.750 -0.8358 0.01972 0.01517 -0.0196 1.0000 0.0164
-8.500 -0.8139 0.01869 0.01399 -0.0187 1.0000 0.0166
-8.250 -0.7914 0.01782 0.01299 -0.0179 1.0000 0.0167
-8.000 -0.7685 0.01707 0.01212 -0.0170 1.0000 0.0169
-7.750 -0.7459 0.01627 0.01122 -0.0161 1.0000 0.0170
-7.500 -0.7268 0.01462 0.00939 -0.0147 1.0000 0.0174
-7.250 -0.7051 0.01374 0.00845 -0.0136 1.0000 0.0177
-7.000 -0.6823 0.01315 0.00781 -0.0126 1.0000 0.0181
-6.750 -0.6592 0.01266 0.00729 -0.0116 1.0000 0.0185
-6.500 -0.6360 0.01221 0.00681 -0.0107 1.0000 0.0189
-6.250 -0.6128 0.01178 0.00634 -0.0097 1.0000 0.0193
-6.000 -0.5897 0.01137 0.00591 -0.0086 1.0000 0.0198
-5.750 -0.5664 0.01104 0.00555 -0.0076 1.0000 0.0203
-5.500 -0.5431 0.01076 0.00524 -0.0066 1.0000 0.0208
-5.250 -0.5210 0.01023 0.00466 -0.0054 1.0000 0.0214
-5.000 -0.4869 0.00973 0.00416 -0.0068 0.9981 0.0224
-4.750 -0.4512 0.00942 0.00385 -0.0085 0.9958 0.0235
-4.500 -0.4145 0.00913 0.00355 -0.0104 0.9934 0.0248
-4.250 -0.3790 0.00877 0.00318 -0.0119 0.9889 0.0265
-4.000 -0.3416 0.00847 0.00291 -0.0139 0.9850 0.0295
-3.750 -0.3074 0.00819 0.00266 -0.0152 0.9770 0.0338
-3.500 -0.2732 0.00796 0.00246 -0.0164 0.9646 0.0402
-3.250 -0.2413 0.00782 0.00233 -0.0170 0.9461 0.0454
-3.000 -0.2135 0.00765 0.00215 -0.0167 0.9205 0.0518
-2.750 -0.1872 0.00763 0.00204 -0.0160 0.8909 0.0551
-2.500 -0.1612 0.00750 0.00186 -0.0154 0.8656 0.0612
-2.250 -0.1345 0.00747 0.00176 -0.0149 0.8434 0.0656
-2.000 -0.1078 0.00739 0.00163 -0.0144 0.8208 0.0721
-1.750 -0.0810 0.00735 0.00152 -0.0140 0.7980 0.0785
-1.500 -0.0542 0.00727 0.00141 -0.0136 0.7731 0.0908
-1.250 -0.0278 0.00712 0.00132 -0.0132 0.7485 0.1257
-1.000 -0.0021 0.00681 0.00121 -0.0128 0.7222 0.2109
-0.750 0.0204 0.00597 0.00105 -0.0121 0.6936 0.4477
-0.500 0.0441 0.00551 0.00099 -0.0113 0.6652 0.5985
-0.250 0.0687 0.00528 0.00098 -0.0105 0.6371 0.6947
0.000 0.0938 0.00519 0.00099 -0.0098 0.6075 0.7573
0.250 0.1187 0.00513 0.00101 -0.0089 0.5776 0.8139
0.500 0.1437 0.00512 0.00104 -0.0080 0.5486 0.8577
0.750 0.1692 0.00515 0.00108 -0.0072 0.5206 0.8935
1.000 0.1951 0.00522 0.00114 -0.0064 0.4926 0.9291
1.250 0.2246 0.00538 0.00122 -0.0065 0.4609 0.9579
1.500 0.2583 0.00561 0.00129 -0.0076 0.4211 0.9739
1.750 0.2972 0.00589 0.00139 -0.0099 0.3774 0.9857
2.000 0.3361 0.00615 0.00147 -0.0123 0.3379 0.9905
2.250 0.3698 0.00640 0.00154 -0.0136 0.3002 0.9941
2.500 0.4056 0.00665 0.00162 -0.0154 0.2643 0.9961
2.750 0.4409 0.00689 0.00170 -0.0171 0.2317 0.9984
3.000 0.4742 0.00712 0.00180 -0.0184 0.2056 1.0000
3.250 0.4990 0.00729 0.00189 -0.0178 0.1910 1.0000
3.500 0.5239 0.00743 0.00198 -0.0172 0.1828 1.0000
3.750 0.5489 0.00758 0.00209 -0.0165 0.1760 1.0000
4.000 0.5741 0.00771 0.00220 -0.0159 0.1710 1.0000
4.250 0.5991 0.00788 0.00233 -0.0153 0.1650 1.0000
4.500 0.6244 0.00801 0.00246 -0.0147 0.1603 1.0000
4.750 0.6498 0.00814 0.00257 -0.0141 0.1553 1.0000
5.000 0.6749 0.00832 0.00273 -0.0136 0.1496 1.0000
5.250 0.7004 0.00845 0.00286 -0.0130 0.1451 1.0000
5.500 0.7260 0.00859 0.00298 -0.0125 0.1396 1.0000
5.750 0.7512 0.00879 0.00315 -0.0119 0.1326 1.0000
6.000 0.7770 0.00891 0.00328 -0.0115 0.1267 1.0000
6.250 0.8023 0.00912 0.00344 -0.0109 0.1174 1.0000
6.500 0.8274 0.00936 0.00362 -0.0104 0.1051 1.0000
6.750 0.8523 0.00966 0.00385 -0.0099 0.0932 1.0000
7.000 0.8774 0.00995 0.00410 -0.0094 0.0856 1.0000
7.250 0.9026 0.01023 0.00437 -0.0089 0.0793 1.0000
7.500 0.9277 0.01055 0.00467 -0.0084 0.0736 1.0000
7.750 0.9530 0.01085 0.00498 -0.0080 0.0686 1.0000
8.000 0.9783 0.01114 0.00527 -0.0076 0.0644 1.0000
8.250 1.0029 0.01155 0.00565 -0.0071 0.0589 1.0000
8.500 1.0285 0.01180 0.00594 -0.0067 0.0560 1.0000
8.750 1.0532 0.01220 0.00631 -0.0063 0.0518 1.0000
9.000 1.0780 0.01257 0.00669 -0.0058 0.0486 1.0000
9.250 1.1032 0.01288 0.00703 -0.0055 0.0461 1.0000
9.500 1.1275 0.01330 0.00744 -0.0050 0.0432 1.0000
9.750 1.1516 0.01375 0.00791 -0.0045 0.0408 1.0000
10.000 1.1767 0.01405 0.00825 -0.0041 0.0393 1.0000
10.250 1.2011 0.01443 0.00866 -0.0037 0.0376 1.0000
10.500 1.2246 0.01491 0.00914 -0.0032 0.0358 1.0000
10.750 1.2472 0.01551 0.00978 -0.0026 0.0340 1.0000
11.000 1.2716 0.01584 0.01017 -0.0022 0.0331 1.0000
11.250 1.2955 0.01622 0.01061 -0.0017 0.0320 1.0000
11.500 1.3188 0.01667 0.01108 -0.0012 0.0306 1.0000
11.750 1.3406 0.01726 0.01169 -0.0006 0.0289 1.0000
12.000 1.3628 0.01780 0.01227 0.0000 0.0276 1.0000
12.250 1.3861 0.01817 0.01271 0.0005 0.0265 1.0000
12.500 1.4083 0.01865 0.01322 0.0010 0.0250 1.0000
12.750 1.4282 0.01937 0.01395 0.0018 0.0231 1.0000
13.000 1.4503 0.01980 0.01445 0.0024 0.0217 1.0000
13.250 1.4705 0.02042 0.01508 0.0031 0.0196 1.0000
13.500 1.4893 0.02114 0.01585 0.0040 0.0174 1.0000
13.750 1.5054 0.02207 0.01678 0.0052 0.0150 1.0000
14.000 1.5215 0.02294 0.01772 0.0063 0.0135 1.0000
14.250 1.5335 0.02410 0.01892 0.0078 0.0121 1.0000
14.500 1.5444 0.02515 0.02007 0.0095 0.0114 1.0000
14.750 1.5520 0.02627 0.02127 0.0116 0.0109 1.0000
15.000 1.5568 0.02763 0.02271 0.0136 0.0104 1.0000
15.250 1.5584 0.02932 0.02451 0.0153 0.0099 1.0000
15.500 1.5552 0.03165 0.02696 0.0166 0.0095 1.0000
15.750 1.5537 0.03412 0.02955 0.0171 0.0093 1.0000
16.000 1.5530 0.03680 0.03237 0.0168 0.0091 1.0000
16.250 1.5491 0.04015 0.03585 0.0159 0.0089 1.0000
16.500 1.5415 0.04434 0.04019 0.0141 0.0088 1.0000
16.750 1.5292 0.04961 0.04562 0.0113 0.0087 1.0000
17.000 1.5106 0.05625 0.05242 0.0075 0.0087 1.0000
17.250 1.4828 0.06470 0.06106 0.0026 0.0087 1.0000
17.500 1.4449 0.07504 0.07160 -0.0032 0.0088 1.0000
17.750 1.3941 0.08761 0.08437 -0.0097 0.0090 1.0000
18.000 1.3351 0.10171 0.09865 -0.0169 0.0093 1.0000
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Polar data table (+)
Polar graphs
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