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 · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 ....

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Page 1:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 2:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 3:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 4:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 5:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 6:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 7:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 8:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 9:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 10:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 11:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 12:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 13:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 14:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.
Page 15:  · NACA 6 SERIE Fig. 9 - Airfoil design methodology for the inboard sections of the blade. 438 . NACA 0012 ... 0,4212 and 04213 airfoils. Lift curves at MO = 0.4.

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