Accession Number : ADA111128


Title :   Experimental Analysis of the Effects of Sweep and Aspect Ratio on Incompressible Flow About Forward Swept Wings.


Descriptive Note : Master's thesis,


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING


Personal Author(s) : Savage,Paul W


Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADA111128


Report Date : Dec 1981


Pagination or Media Count : 142


Abstract : Low speed wind tunnel tests were conducted on nine wing planforms to determine the effect of sweep and aspect ratio on forward swept wings in incompressible flow. Sweep angles tested were -15, -30 and -45 degrees. Aspect ratios ranged from 2.05 to 4.79. A NACA 0006 airfoil section perpendicular to the leading edge was used for all models. Results showed increasing negative sweep decreased lift curve slope and shifted the aerodynamic center rearward. Increasing aspect ratio increased lift curve slope, decreased drag coefficient and shifted the aerodynamic center rearward. The wind tunnel aerodynamic data were compared to the Air Force Flight Dynamics Laboratory's Large Aircraft Performance Prediction Program to determine the program's ability to predict forward swept wing aerodynamic coefficients. At incompressible Mach numbers, the program was found to be accurate in predicting lift curve slope in the linear range using a positive sweep input. Drag Polar slope and moment coefficient were accurately predicted for lift coefficients below 0.4 using a negative sweep angle input. Neither positive nor negative angle input predicted maximum lift coefficient accurately. (Author)


Descriptors :   *SWEPTFORWARD WINGS , *THIN WINGS , ANGLES , PITCH(MOTION) , COMPUTER AIDED DESIGN , THESES , VARIATIONS , MATHEMATICAL PREDICTION , COEFFICIENTS , AERODYNAMIC CHARACTERISTICS , AERODYNAMIC DRAG , LIFT , INCOMPRESSIBLE FLOW , ASPECT RATIO , WIND TUNNEL MODELS , DRAG REDUCTION


Subject Categories : Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE