BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 50,000 Max Cl/Cd: 28.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43012-il-50000-n5.txt Download as CSV file: xf-v43012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43012-1.58 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3825 0.10949 0.10236 -0.0215 1.0000 0.1090
-9.750 -0.3956 0.10666 0.09963 -0.0249 1.0000 0.1125
-9.500 -0.4190 0.10360 0.09671 -0.0299 1.0000 0.1135
-9.250 -0.3836 0.09957 0.09269 -0.0240 1.0000 0.1208
-9.000 -0.3956 0.09646 0.08969 -0.0265 1.0000 0.1257
-8.750 -0.4286 0.09361 0.08696 -0.0300 1.0000 0.1275
-8.500 -0.4004 0.08956 0.08298 -0.0269 1.0000 0.1341
-8.250 -0.4123 0.08663 0.08015 -0.0270 1.0000 0.1382
-8.000 -0.4522 0.08476 0.07830 -0.0276 1.0000 0.1426
-7.750 -0.4327 0.08061 0.07431 -0.0254 1.0000 0.1491
-7.250 -0.4466 0.07501 0.06883 -0.0225 1.0000 0.1662
-6.250 -0.4638 0.06488 0.05895 -0.0132 1.0000 0.2185
-6.000 -0.4681 0.06226 0.05629 -0.0114 1.0000 0.2228
-5.000 -0.4306 0.05223 0.04412 -0.0057 1.0000 0.1001
-4.750 -0.4160 0.04872 0.04063 -0.0040 1.0000 0.0854
-4.500 -0.3829 0.04610 0.03748 -0.0052 0.9916 0.0753
-4.250 -0.3451 0.04321 0.03431 -0.0079 0.9797 0.0726
-4.000 -0.3062 0.04096 0.03168 -0.0104 0.9665 0.0726
-3.750 -0.2671 0.03889 0.02923 -0.0125 0.9526 0.0723
-3.500 -0.2282 0.03696 0.02695 -0.0143 0.9388 0.0708
-3.250 -0.1877 0.03522 0.02487 -0.0161 0.9259 0.0696
-3.000 -0.1463 0.03360 0.02296 -0.0180 0.9123 0.0694
-2.750 -0.1049 0.03208 0.02126 -0.0199 0.8960 0.0712
-2.500 -0.0598 0.03059 0.01957 -0.0220 0.8786 0.0728
-2.250 -0.0179 0.02920 0.01803 -0.0233 0.8582 0.0732
-2.000 0.0246 0.02794 0.01668 -0.0246 0.8371 0.0739
-1.750 0.0660 0.02691 0.01554 -0.0258 0.8162 0.0757
-1.500 0.1065 0.02588 0.01446 -0.0270 0.7950 0.0790
-1.250 0.1408 0.02502 0.01353 -0.0272 0.7706 0.0822
-1.000 0.1721 0.02432 0.01266 -0.0268 0.7445 0.0849
-0.750 0.1992 0.02383 0.01194 -0.0258 0.7167 0.0878
-0.500 0.2236 0.02326 0.01121 -0.0244 0.6880 0.0931
-0.250 0.2470 0.02293 0.01065 -0.0228 0.6573 0.1006
0.250 0.4211 0.01998 0.00980 -0.0412 0.5628 1.0000
0.500 0.4388 0.02019 0.00968 -0.0391 0.5331 1.0000
0.750 0.4567 0.02044 0.00960 -0.0372 0.5063 1.0000
1.000 0.4750 0.02071 0.00962 -0.0354 0.4802 1.0000
1.250 0.4938 0.02101 0.00962 -0.0337 0.4575 1.0000
1.500 0.5130 0.02135 0.00969 -0.0321 0.4377 1.0000
1.750 0.5326 0.02172 0.00980 -0.0306 0.4211 1.0000
2.250 0.5741 0.02258 0.01025 -0.0281 0.3936 1.0000
2.500 0.5954 0.02304 0.01057 -0.0270 0.3817 1.0000
2.750 0.6169 0.02352 0.01085 -0.0259 0.3716 1.0000
3.000 0.6376 0.02400 0.01128 -0.0247 0.3609 1.0000
3.250 0.6591 0.02450 0.01167 -0.0236 0.3523 1.0000
3.500 0.6801 0.02503 0.01215 -0.0225 0.3440 1.0000
3.750 0.7021 0.02557 0.01254 -0.0214 0.3373 1.0000
4.000 0.7225 0.02616 0.01318 -0.0203 0.3295 1.0000
4.250 0.7440 0.02671 0.01362 -0.0192 0.3231 1.0000
4.500 0.7643 0.02735 0.01427 -0.0180 0.3164 1.0000
4.750 0.7848 0.02799 0.01490 -0.0168 0.3100 1.0000
5.000 0.8071 0.02859 0.01537 -0.0159 0.3048 1.0000
5.250 0.8250 0.02936 0.01628 -0.0145 0.2981 1.0000
5.500 0.8450 0.03002 0.01691 -0.0133 0.2921 1.0000
5.750 0.8661 0.03071 0.01752 -0.0123 0.2869 1.0000
6.000 0.8828 0.03159 0.01857 -0.0107 0.2806 1.0000
6.250 0.9024 0.03233 0.01929 -0.0096 0.2752 1.0000
6.500 0.9240 0.03307 0.01994 -0.0087 0.2707 1.0000
6.750 0.9378 0.03419 0.02132 -0.0069 0.2651 1.0000
7.000 0.9554 0.03513 0.02233 -0.0056 0.2601 1.0000
7.250 0.9765 0.03594 0.02309 -0.0047 0.2561 1.0000
7.500 0.9924 0.03715 0.02444 -0.0034 0.2522 1.0000
7.750 1.0029 0.03862 0.02618 -0.0015 0.2477 1.0000
8.000 1.0172 0.03987 0.02755 0.0000 0.2435 1.0000
8.250 1.0362 0.04085 0.02854 0.0010 0.2399 1.0000
8.500 1.0522 0.04210 0.02986 0.0022 0.2364 1.0000
8.750 1.0515 0.04421 0.03232 0.0049 0.2323 1.0000
9.000 1.0559 0.04605 0.03436 0.0070 0.2285 1.0000
9.250 1.0659 0.04757 0.03600 0.0086 0.2254 1.0000
9.500 1.0815 0.04889 0.03737 0.0096 0.2230 1.0000
9.750 1.0851 0.05099 0.03962 0.0115 0.2206 1.0000
10.000 1.0503 0.05516 0.04415 0.0158 0.2181 1.0000
10.250 0.9903 0.06122 0.05042 0.0198 0.2157 1.0000
10.500 0.8602 0.07930 0.06867 0.0137 0.2107 1.0000
10.750 0.8536 0.08417 0.07358 0.0122 0.2082 1.0000
11.000 0.8696 0.08530 0.07476 0.0130 0.2067 1.0000
11.500 0.7659 0.11070 0.10016 -0.0002 0.1970 1.0000
11.750 0.7642 0.11509 0.10460 -0.0016 0.1954 1.0000
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Polar data table (+)
Polar graphs
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