Low Speed Wind Tunnel Investigation of High Lift Devices on a 65° Swept-Back Supersonic Wing of 3.44 Aspect Ratio

Citation

Thomas, John William (1949) Low Speed Wind Tunnel Investigation of High Lift Devices on a 65° Swept-Back Supersonic Wing of 3.44 Aspect Ratio. Engineer's thesis, California Institute of Technology. doi:10.7907/TYRW-TZ93. https://resolver.caltech.edu/CaltechETD:etd-02242009-092302

Abstract

NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. A low speed investigation was made in the Cal Tech-Merrill Wind Tunnel at Pasadena City College of a 3.44 aspect ratio wing, having a 65° swept-back leading edge and a symretrical double-wedge airfoil section, to determine the characteristics and effectiveness of various high-lift devices. The investigation included tests of trailing edge split flaps and extended split flaps, leading edge flaps and slats, and combined configurations. The tests were carried out using the wing with and without the fuselage and tail surfaces. The results showed that the split flaps increased the lift over the lower regions of the angle of attack only. The extended split flaps were more effective and increased the lift over the whole range. The nose flaps tested did not increase the lift when used by themselves, but the combination of a nose flap with the fuselage and extended split flap produced the greatest lift. The addition of the fuselage added to the lift by increasing the slope of the lift curve. The addition of the tail surface gave additional increments in lift in the upper regions of angle of attack. The maximum lift coefficient, [...], normally occurred at an angle of attack of 38°. The extended split flaps produced large variations in pitching moment, but had stabilizing tendencies except where there were irregularities in the lift curve.

Thesis Files