Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effects of Sweep Angle and Thickness Ratio on the Aerodynamic Characteristics in Pitch at M
National Advisory Committee for Aeronautics, 1952 - Aerodynamics, Supersonic - 27 pages
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6-percent–thick addition Aerodynamic Character aerodynamic characteristics Angle and Thickness angle of attack Aspect Ratio balance based on body body length Cambered Wings characteristics in pitch coefficient of body Combinations Having Cambered CONFIDENTIAL configuration Continued corrected Details determine dimensions in inches effects of sweep effects of thickness estimated flow Force Included increased indicate istics at Supersonic lift coefficient Lift coefficient,CL lift-drag ratio Lower Surface Surface Mach number maximum mean aerodynamic chord NACA RM number of 2.0l obtained percent Position presented in figure quarter-chord sweep angles Ratio of 3.5 Root Section Series of Wing-Body shown in figure Stagnation Static station sting summary supersonic pressure tunnel Supersonic Speeds sweep and thickness swept wing TABLE Taper Ratio test section Thickened root thickness ratio tion transition strip Transonic Upper Lower Surface values variation wing series Wing-Body Combinations