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Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
Date:
December 1, 1949
Creator:
Silvers, H. Norman & Spreeman, Kenneth P.
System:
The UNT Digital Library
Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date:
November 1, 1949
Creator:
Goodson, Kenneth W. & Few, Albert G., Jr.
System:
The UNT Digital Library
Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge
Report presenting a preliminary theoretical and experimental investigation of the supersonic characteristics of blunt-trailing-edge airfoils. Results regarding the drag measurements at zero lift, measurements at angle of attack, and a general discussion of the theoretical and experimental results is provided.
Date:
November 1, 1949
Creator:
Chapman, Dean R.
System:
The UNT Digital Library
Experimental investigation of rim cracking in disks subjected to high temperature gradients
Report presenting the results of an experimental investigation of rim cracking in a welded-blade composite gas-turbine wheel, in two carbon-steel disks, and five tool-steel disks. Various characteristics were investigated, including the effectiveness of holes in preventing crack propagation and the influence of hardness and various types of notch on rim cracking.
Date:
September 1, 1949
Creator:
Wilterdink, P. I.
System:
The UNT Digital Library
Investigation of Internal Regenerative Fuel-Heating System for 20-Inch Ram Jet
Memorandum presenting an investigation conducted to evaluate the effectiveness of a simple internal regenerative fuel preheater for a 20-inch-diameter ram jet. Data obtained at subsonic sea-level conditions indicated that fuel could be successfully preheated in this manner.
Date:
September 1, 1949
Creator:
Baker, Sol & Perchonok, Eugene
System:
The UNT Digital Library
An Experimental Investigation at Large Scale of Single and Twin Naca Submerged Side Intakes at Several Angles of Sideslip
Report presenting the results of an experimental investigation to determine the pressure-recovery and mass-flow characteristics of single and twin NACA submerged intakes on the sides of a fuselage at various angles of sideslip. Tests were conducted with single and twin submerged intakes on a model of a fighter-type airplane.
Date:
August 1, 1949
Creator:
Martin, Norman J. & Holzhauser, Curt A.
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 1: rectangular wing
The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
Date:
March 1, 1949
Creator:
Perkins, Edward W. & Canning, Thomas N.
System:
The UNT Digital Library