BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| 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: 72.9 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13009-il-500000.txt Download as CSV file: xf-v13009-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6240 0.08817 0.08587 -0.0052 1.0000 0.0310
-9.250 -0.6358 0.07844 0.07611 -0.0162 1.0000 0.0310
-9.000 -0.6656 0.06941 0.06700 -0.0210 1.0000 0.0313
-8.750 -0.6643 0.06609 0.06365 -0.0215 1.0000 0.0316
-8.500 -0.6605 0.06286 0.06038 -0.0221 1.0000 0.0319
-8.000 -0.7077 0.03682 0.03309 -0.0235 1.0000 0.0262
-7.750 -0.6987 0.03208 0.02799 -0.0220 1.0000 0.0247
-7.500 -0.6922 0.02672 0.02207 -0.0200 1.0000 0.0243
-7.250 -0.6780 0.02326 0.01813 -0.0182 1.0000 0.0243
-7.000 -0.6595 0.02101 0.01555 -0.0167 1.0000 0.0245
-6.750 -0.6389 0.01939 0.01366 -0.0154 1.0000 0.0248
-6.500 -0.6171 0.01817 0.01224 -0.0143 1.0000 0.0252
-6.250 -0.5950 0.01710 0.01099 -0.0131 1.0000 0.0257
-6.000 -0.5739 0.01563 0.00944 -0.0120 1.0000 0.0265
-5.750 -0.5511 0.01497 0.00875 -0.0110 1.0000 0.0273
-5.500 -0.5282 0.01433 0.00807 -0.0099 1.0000 0.0280
-5.250 -0.5055 0.01372 0.00741 -0.0088 1.0000 0.0288
-5.000 -0.4828 0.01315 0.00679 -0.0077 1.0000 0.0297
-4.750 -0.4600 0.01268 0.00626 -0.0066 1.0000 0.0306
-4.500 -0.4385 0.01193 0.00549 -0.0054 1.0000 0.0320
-4.250 -0.4162 0.01153 0.00512 -0.0043 1.0000 0.0337
-4.000 -0.3936 0.01129 0.00488 -0.0033 1.0000 0.0359
-3.750 -0.3592 0.01079 0.00438 -0.0047 0.9974 0.0394
-3.500 -0.3181 0.01051 0.00413 -0.0075 0.9936 0.0444
-3.250 -0.2793 0.01009 0.00377 -0.0098 0.9879 0.0515
-3.000 -0.2387 0.00975 0.00346 -0.0125 0.9835 0.0596
-2.750 -0.2001 0.00958 0.00329 -0.0146 0.9747 0.0664
-2.500 -0.1643 0.00917 0.00294 -0.0162 0.9630 0.0751
-2.250 -0.1301 0.00890 0.00267 -0.0173 0.9483 0.0834
-2.000 -0.0984 0.00867 0.00245 -0.0178 0.9292 0.0935
-1.750 -0.0702 0.00839 0.00222 -0.0176 0.9079 0.1118
-1.500 -0.0447 0.00797 0.00203 -0.0169 0.8855 0.1763
-1.250 -0.0257 0.00666 0.00177 -0.0156 0.8619 0.4904
-1.000 -0.0056 0.00603 0.00172 -0.0138 0.8364 0.6693
-0.750 0.0169 0.00580 0.00171 -0.0121 0.8131 0.7585
-0.500 0.0403 0.00568 0.00171 -0.0106 0.7894 0.8194
-0.250 0.0636 0.00563 0.00172 -0.0089 0.7629 0.8747
0.000 0.0895 0.00569 0.00175 -0.0079 0.7358 0.9141
0.250 0.1189 0.00580 0.00178 -0.0076 0.7075 0.9411
0.500 0.1539 0.00596 0.00182 -0.0087 0.6774 0.9616
0.750 0.1926 0.00616 0.00186 -0.0107 0.6437 0.9774
1.000 0.2382 0.00638 0.00190 -0.0143 0.6053 0.9882
1.250 0.2842 0.00660 0.00192 -0.0181 0.5646 0.9965
1.500 0.3207 0.00677 0.00191 -0.0200 0.5271 1.0000
1.750 0.3459 0.00692 0.00191 -0.0195 0.4915 1.0000
2.000 0.3708 0.00711 0.00192 -0.0190 0.4531 1.0000
2.250 0.3956 0.00732 0.00195 -0.0185 0.4113 1.0000
2.500 0.4201 0.00759 0.00201 -0.0179 0.3681 1.0000
3.000 0.4688 0.00814 0.00220 -0.0167 0.2925 1.0000
3.250 0.4932 0.00843 0.00233 -0.0160 0.2608 1.0000
3.500 0.5175 0.00870 0.00247 -0.0154 0.2368 1.0000
3.750 0.5422 0.00894 0.00262 -0.0147 0.2194 1.0000
4.000 0.5668 0.00918 0.00278 -0.0141 0.2064 1.0000
4.250 0.5918 0.00938 0.00295 -0.0135 0.1975 1.0000
4.500 0.6166 0.00962 0.00314 -0.0128 0.1898 1.0000
4.750 0.6415 0.00983 0.00333 -0.0122 0.1825 1.0000
5.000 0.6661 0.01010 0.00356 -0.0116 0.1756 1.0000
5.250 0.6914 0.01028 0.00375 -0.0110 0.1687 1.0000
5.500 0.7159 0.01059 0.00401 -0.0104 0.1614 1.0000
5.750 0.7417 0.01074 0.00419 -0.0099 0.1553 1.0000
6.000 0.7663 0.01107 0.00447 -0.0094 0.1472 1.0000
6.250 0.7925 0.01118 0.00464 -0.0090 0.1400 1.0000
6.500 0.8178 0.01144 0.00487 -0.0085 0.1312 1.0000
6.750 0.8434 0.01166 0.00507 -0.0081 0.1211 1.0000
7.000 0.8689 0.01192 0.00532 -0.0077 0.1107 1.0000
7.250 0.8938 0.01226 0.00562 -0.0072 0.1007 1.0000
7.500 0.9183 0.01267 0.00599 -0.0067 0.0919 1.0000
7.750 0.9427 0.01309 0.00639 -0.0061 0.0848 1.0000
8.000 0.9668 0.01356 0.00688 -0.0056 0.0789 1.0000
8.250 0.9909 0.01402 0.00734 -0.0050 0.0737 1.0000
8.500 1.0138 0.01464 0.00798 -0.0043 0.0688 1.0000
8.750 1.0384 0.01503 0.00843 -0.0038 0.0651 1.0000
9.000 1.0614 0.01561 0.00900 -0.0032 0.0612 1.0000
9.250 1.0835 0.01632 0.00976 -0.0024 0.0582 1.0000
9.500 1.1074 0.01677 0.01029 -0.0019 0.0559 1.0000
9.750 1.1310 0.01723 0.01079 -0.0014 0.0533 1.0000
10.000 1.1510 0.01813 0.01168 -0.0005 0.0499 1.0000
10.250 1.1749 0.01851 0.01215 0.0000 0.0480 1.0000
10.500 1.1982 0.01896 0.01267 0.0005 0.0460 1.0000
10.750 1.2204 0.01950 0.01326 0.0011 0.0441 1.0000
11.000 1.2395 0.02038 0.01416 0.0020 0.0421 1.0000
11.250 1.2592 0.02118 0.01505 0.0029 0.0405 1.0000
11.500 1.2812 0.02167 0.01566 0.0036 0.0390 1.0000
11.750 1.3023 0.02222 0.01627 0.0042 0.0373 1.0000
12.000 1.3215 0.02293 0.01702 0.0050 0.0357 1.0000
12.250 1.3345 0.02423 0.01837 0.0065 0.0339 1.0000
12.500 1.3549 0.02474 0.01903 0.0072 0.0327 1.0000
12.750 1.3733 0.02539 0.01976 0.0081 0.0310 1.0000
13.000 1.3895 0.02618 0.02059 0.0091 0.0293 1.0000
13.250 1.3965 0.02754 0.02203 0.0111 0.0277 1.0000
13.500 1.4118 0.02821 0.02283 0.0123 0.0260 1.0000
13.750 1.4232 0.02916 0.02384 0.0136 0.0243 1.0000
14.000 1.4214 0.03118 0.02591 0.0154 0.0228 1.0000
14.250 1.4318 0.03242 0.02732 0.0162 0.0214 1.0000
14.500 1.4372 0.03420 0.02920 0.0168 0.0201 1.0000
14.750 1.4363 0.03679 0.03187 0.0168 0.0192 1.0000
15.000 1.4263 0.04078 0.03598 0.0158 0.0185 1.0000
15.250 1.4242 0.04424 0.03962 0.0145 0.0179 1.0000
15.500 1.4177 0.04861 0.04415 0.0123 0.0173 1.0000
15.750 1.4071 0.05391 0.04961 0.0093 0.0170 1.0000
16.000 1.3921 0.06013 0.05599 0.0057 0.0167 1.0000
16.250 1.3723 0.06728 0.06331 0.0017 0.0166 1.0000
16.500 1.3485 0.07518 0.07136 -0.0026 0.0166 1.0000
16.750 1.3222 0.08343 0.07976 -0.0069 0.0166 1.0000
17.000 1.2955 0.09178 0.08824 -0.0111 0.0166 1.0000
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Polar data table (+)
Polar graphs
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