BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 50,000 Max Cl/Cd: 26.18 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13009-il-50000.txt Download as CSV file: xf-v13009-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5382 0.09933 0.09241 0.0202 1.0000 0.3159
-7.750 -0.5284 0.09602 0.08912 0.0213 1.0000 0.3349
-7.500 -0.5346 0.09376 0.08696 0.0218 1.0000 0.3573
-7.250 -0.5136 0.08983 0.08302 0.0240 1.0000 0.3814
-7.000 -0.5020 0.08693 0.08017 0.0263 1.0000 0.4136
-6.750 -0.5001 0.08486 0.07816 0.0291 1.0000 0.4506
-6.500 -0.4725 0.08110 0.07438 0.0319 1.0000 0.4898
-6.250 -0.4753 0.07957 0.07294 0.0355 1.0000 0.5307
-6.000 -0.4354 0.07493 0.06825 0.0368 1.0000 0.5715
-5.750 -0.4119 0.07165 0.06497 0.0389 1.0000 0.6186
-5.500 -0.5163 0.04922 0.04120 -0.0170 1.0000 0.1882
-5.250 -0.4954 0.04474 0.03610 -0.0174 1.0000 0.1669
-5.000 -0.4749 0.04111 0.03161 -0.0169 1.0000 0.1538
-4.750 -0.4537 0.03783 0.02815 -0.0161 1.0000 0.1515
-4.500 -0.4322 0.03528 0.02514 -0.0150 1.0000 0.1524
-4.250 -0.4096 0.03298 0.02234 -0.0139 1.0000 0.1546
-4.000 -0.3861 0.03048 0.01977 -0.0130 1.0000 0.1578
-3.750 -0.3623 0.02868 0.01776 -0.0119 1.0000 0.1658
-3.500 -0.3374 0.02681 0.01567 -0.0109 1.0000 0.1738
-3.250 -0.3122 0.02531 0.01398 -0.0099 1.0000 0.1866
-3.000 -0.2859 0.02379 0.01246 -0.0091 1.0000 0.2020
-2.750 -0.2586 0.02228 0.01113 -0.0084 1.0000 0.2228
-2.500 -0.2318 0.02096 0.00996 -0.0077 1.0000 0.2525
-2.250 -0.0771 0.01720 0.00875 -0.0219 1.0000 1.0000
-2.000 -0.0629 0.01694 0.00826 -0.0203 1.0000 1.0000
-1.750 -0.0506 0.01673 0.00789 -0.0182 1.0000 1.0000
-1.500 -0.0400 0.01658 0.00761 -0.0159 1.0000 1.0000
-1.250 -0.0308 0.01649 0.00741 -0.0133 1.0000 1.0000
-1.000 -0.0219 0.01647 0.00728 -0.0106 1.0000 1.0000
-0.750 -0.0134 0.01651 0.00721 -0.0079 1.0000 1.0000
-0.500 -0.0045 0.01662 0.00722 -0.0053 1.0000 1.0000
-0.250 0.0057 0.01680 0.00730 -0.0030 1.0000 1.0000
0.000 0.0175 0.01704 0.00745 -0.0012 1.0000 1.0000
0.250 0.0306 0.01736 0.00767 0.0003 1.0000 1.0000
0.500 0.0445 0.01775 0.00800 0.0014 1.0000 1.0000
0.750 0.0590 0.01823 0.00842 0.0022 1.0000 1.0000
1.000 0.0736 0.01881 0.00896 0.0027 1.0000 1.0000
1.250 0.0882 0.01951 0.00962 0.0028 1.0000 1.0000
1.500 0.1725 0.02052 0.01069 -0.0094 0.9705 1.0000
1.750 0.2776 0.02069 0.01103 -0.0235 0.9245 1.0000
2.000 0.3598 0.02026 0.01079 -0.0316 0.8806 1.0000
2.250 0.4083 0.01996 0.01058 -0.0332 0.8373 1.0000
2.500 0.4417 0.01979 0.01042 -0.0317 0.7925 1.0000
2.750 0.4663 0.01976 0.01031 -0.0286 0.7454 1.0000
3.000 0.4877 0.01987 0.01027 -0.0252 0.6960 1.0000
3.250 0.5089 0.02011 0.01030 -0.0220 0.6450 1.0000
3.500 0.5303 0.02052 0.01043 -0.0192 0.5949 1.0000
3.750 0.5522 0.02116 0.01080 -0.0169 0.5479 1.0000
4.000 0.5745 0.02198 0.01145 -0.0152 0.5064 1.0000
4.250 0.5977 0.02283 0.01213 -0.0138 0.4729 1.0000
4.500 0.6210 0.02375 0.01295 -0.0126 0.4448 1.0000
4.750 0.6447 0.02463 0.01368 -0.0115 0.4206 1.0000
5.000 0.6678 0.02561 0.01467 -0.0105 0.3975 1.0000
5.250 0.6916 0.02656 0.01554 -0.0094 0.3772 1.0000
5.500 0.7146 0.02771 0.01670 -0.0085 0.3579 1.0000
5.750 0.7372 0.02898 0.01807 -0.0076 0.3392 1.0000
6.000 0.7595 0.03029 0.01945 -0.0067 0.3210 1.0000
6.250 0.7816 0.03174 0.02100 -0.0057 0.3042 1.0000
6.500 0.8032 0.03329 0.02264 -0.0048 0.2880 1.0000
6.750 0.8237 0.03503 0.02452 -0.0038 0.2729 1.0000
7.000 0.8430 0.03710 0.02681 -0.0029 0.2597 1.0000
7.250 0.8619 0.03914 0.02904 -0.0019 0.2468 1.0000
7.500 0.8835 0.04107 0.03095 -0.0010 0.2361 1.0000
7.750 0.8953 0.04405 0.03441 0.0000 0.2259 1.0000
8.000 0.9080 0.04714 0.03778 0.0008 0.2175 1.0000
8.250 0.9169 0.05079 0.04178 0.0015 0.2111 1.0000
8.500 0.9278 0.05415 0.04534 0.0022 0.2047 1.0000
8.750 0.9162 0.06027 0.05196 0.0019 0.2020 1.0000
9.000 0.8980 0.06727 0.05925 0.0005 0.2017 1.0000
9.250 0.8748 0.07509 0.06722 -0.0021 0.2039 1.0000
9.500 0.8520 0.08317 0.07536 -0.0056 0.2081 1.0000
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Polar data table (+)
Polar graphs
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