NACA-TN-1709

Abstract

An investigation was conducted to determine the effects of a nacelle on the aerodynamic characteristics of a swept wing and the effects of sweep on a wing alone. The aerodynamic characteristics were determined from force and pressure measurements and tuft studies at Mach numbers of 0.13 to 0.61 for the wing-nacelle combination and at 0.13 to 0.70 for the wing alone. The angle of attack was varied from 0&#176; to the stalling angle sat a Mach numbered 0.13 and from -1.65&#176;to 6&#176; at the higher Mach numbers. <br>The results showed that the measured variation of lift-curve slope with sweep angle is in good agreement with theory up to 30&#176; sweep, but at greater sweep angles the theory apparently underestimates the effects of sweep. The presence of the nacelle increased the lift-curve slope about 10 percent with the wing at 45&#176; sweep but decreased the slope slightly at -45&#176; sweep. The nacelle had no effect on the lift-curve slope of the unswept wing. The present of the nacelle did not appreciably alter the stalling characteristics of the wing at sweep angles of 45&#176; but for the unswept wing the addition of the nacelle caused an appreciable reduction in the maximum lift coefficient and in the angle of attack at maximum lift.