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Low Speed Wind Tunnel Investigation of Propeller Slipstream Aerodynamic Effects on Different Nacelle/Wing Combinations. Part 1. Total Forces and Moments and Pressure Distributions on Nacelle/Wing at Different Angles of Attack and Yaw and at Different Thrust Coefficients.

N8813302

Publication Date	1987
Personal Author	Samuelsson, I.
Page Count	73
Abstract	A wind tunnel investigation of propeller slipstream/nacelle/wing aerodynamic interference effects was carried out for 4 nacelle/wing combinations, with different angles of attack and yaw, freestream speeds (33 to 61 m/sec) and thrust coefficients (CF: 0.05 to 0.57). Results show significant propeller slipstream induced lateral nacelle loads (side force, yawing moment, and rolling moment). For an axisymmetrical nacelle (wing/off) set at incidence at zero yaw, the cyclic thrust variation on the propeller blades creates an asymmetrical pressure field in the slipstream. When this asymmetrical slipstream washes the nacelle surfaces there are lateral loads acting on the nacelle. For an nonaxisymmetrical (high) nacelle lateral nacelle loads develop even at zero incidence and zero yaw, due to asymmetrical interference between the propeller swirl, slipstream, and pressure field and the nacelle surfaces. There are also significant effects of CF on the development of the lateral nacelle loads.
Keywords	Angle of attack Body-wing configurations Nacelles Pressure distribution Propeller slipstreams Thrust distribution Wind tunnel tests Yaw Stability derivatives Aerodynamic loads Low speed wind tunnels Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51A - Aerodynamics
Corporate Authors	Aeronautical Research Inst. of Sweden, Stockholm.; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	Sponsored by Swedish Board for Technical Devolopment.
Document Type	Technical Report
NTIS Issue Number	198808

Low Speed Wind Tunnel Investigation of Propeller Slipstream Aerodynamic Effects on Different Nacelle/Wing Combinations. Part 1. Total Forces and Moments and Pressure Distributions on Nacelle/Wing at Different Angles of Attack and Yaw and at Different Thrust Coefficients.

Low Speed Wind Tunnel Investigation of Propeller Slipstream Aerodynamic Effects on Different Nacelle/Wing Combinations. Part 1. Total Forces and Moments and Pressure Distributions on Nacelle/Wing at Different Angles of Attack and Yaw and at Different Thrust Coefficients.
N8813302

Publication Date	1987
Personal Author	Samuelsson, I.
Page Count	73
Abstract	A wind tunnel investigation of propeller slipstream/nacelle/wing aerodynamic interference effects was carried out for 4 nacelle/wing combinations, with different angles of attack and yaw, freestream speeds (33 to 61 m/sec) and thrust coefficients (CF: 0.05 to 0.57). Results show significant propeller slipstream induced lateral nacelle loads (side force, yawing moment, and rolling moment). For an axisymmetrical nacelle (wing/off) set at incidence at zero yaw, the cyclic thrust variation on the propeller blades creates an asymmetrical pressure field in the slipstream. When this asymmetrical slipstream washes the nacelle surfaces there are lateral loads acting on the nacelle. For an nonaxisymmetrical (high) nacelle lateral nacelle loads develop even at zero incidence and zero yaw, due to asymmetrical interference between the propeller swirl, slipstream, and pressure field and the nacelle surfaces. There are also significant effects of CF on the development of the lateral nacelle loads.
Keywords	Angle of attack Body-wing configurations Nacelles Pressure distribution Propeller slipstreams Thrust distribution Wind tunnel tests Yaw Stability derivatives Aerodynamic loads Low speed wind tunnels Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51A - Aerodynamics
Corporate Authors	Aeronautical Research Inst. of Sweden, Stockholm.; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	Sponsored by Swedish Board for Technical Devolopment.
Document Type	Technical Report
NTIS Issue Number	198808