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Wind Tunnel Tests of a Free-Wing Tilt-Propeller V/STOL Airplane Model.

AD698355

Publication Date	1969
Personal Author	Strand, T.; Levinsky, E. S.
Page Count	61
Abstract	Wind tunnel tests were conducted on a free-wing tilt-propeller V/STOL airplane model to investigate the aerodynamic characteristics of the free-floating wing in the propeller slipstream through the transitional region from cruise to near hover. Lift and drag curves wing-free were obtained as a function of propeller tilt angle and thrust coefficient, and are compared with wing-pinned data. The results indicate that the tilted propeller does not significantly turn the flow past the wing, except at thrust coefficients near unity and at propeller tilt angles near 90 deg. It is found that lift curve slope and maximum lift coefficient are strong functions of thrust coefficient. Provided the cruise static margin is adequate, the free-floating wing with flap and slat retracted behaves in the slipstream with no unusual problems. Based upon these initial test results, the free-wing concept therefore appears to be feasible aerodynamically. Additional wind tunnel tests are required on the free wing with flap and slat extended. (Author)
Keywords	Vertical take-off planes Aerodynamic configurations Wings Propellers(Aerial) Airplane models Model tests Wind tunnel models Hovering Aerodynamic characteristics Lift Drag Thrust Flaps Feasibility studies Free floating wings Tilt propellers Transition flight
NTIS Subject Category	51C - Aircraft 46B - Fluid Mechanics 51A - Aerodynamics
Corporate Authors	Air Vehicle Corp San Diego Calif
Document Type	Technical Report
Title Note	Technical rept. Jun 68-Aug 69.
NTIS Issue Number	197004
Contract Number	F33615-68-C-1672

Wind Tunnel Tests of a Free-Wing Tilt-Propeller V/STOL Airplane Model.

Wind Tunnel Tests of a Free-Wing Tilt-Propeller V/STOL Airplane Model.
AD698355

Publication Date	1969
Personal Author	Strand, T.; Levinsky, E. S.
Page Count	61
Abstract	Wind tunnel tests were conducted on a free-wing tilt-propeller V/STOL airplane model to investigate the aerodynamic characteristics of the free-floating wing in the propeller slipstream through the transitional region from cruise to near hover. Lift and drag curves wing-free were obtained as a function of propeller tilt angle and thrust coefficient, and are compared with wing-pinned data. The results indicate that the tilted propeller does not significantly turn the flow past the wing, except at thrust coefficients near unity and at propeller tilt angles near 90 deg. It is found that lift curve slope and maximum lift coefficient are strong functions of thrust coefficient. Provided the cruise static margin is adequate, the free-floating wing with flap and slat retracted behaves in the slipstream with no unusual problems. Based upon these initial test results, the free-wing concept therefore appears to be feasible aerodynamically. Additional wind tunnel tests are required on the free wing with flap and slat extended. (Author)
Keywords	Vertical take-off planes Aerodynamic configurations Wings Propellers(Aerial) Airplane models Model tests Wind tunnel models Hovering Aerodynamic characteristics Lift Drag Thrust Flaps Feasibility studies Free floating wings Tilt propellers Transition flight
NTIS Subject Category	51C - Aircraft 46B - Fluid Mechanics 51A - Aerodynamics
Corporate Authors	Air Vehicle Corp San Diego Calif
Document Type	Technical Report
Title Note	Technical rept. Jun 68-Aug 69.
NTIS Issue Number	197004
Contract Number	F33615-68-C-1672