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UNT Libraries Government Documents Department
Decade:
1940-1949
Year:
1948
Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations
Date: December 31, 1948
Creator: Thompson, Jim Rogers
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57935/
Summary of results of tumbling investigations made in the Langley 20-foot free-spinning tunnel on 14 dynamic models
Date: December 31, 1948
Creator: Stone, Ralph W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57849/
An analytical method of estimating turbine performance
Date: December 29, 1948
Creator: Kochendorfer, Fred D
Description: A method is developed by which the performance of a turbine over a range of operating conditions can be analytically estimated from the blade angles and flow areas. In order to use the method, certain coefficients that determine the weight flow and friction losses must be approximated. The method is used to calculate the performance of the single-stage turbine of a commercial aircraft gas-turbine engine and the calculated performance is compared with the performance indicated by experimental data. For the turbine of the typical example, the assumed pressure losses and turning angles give a calculated performance that represents the trends of the experimental performance with reasonable accuracy. The exact agreement between analytical performance and experimental performance is contingent upon the proper selection of the blading-loss parameter. A variation of blading-loss parameter from 0.3 to 0.5 includes most of the experimental data from the turbine investigated.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57971/
An investigation of aileron oscillations at transonic speeds on NACA 23012 and NACA 65-212 airfoils by the wing-flow method
Date: December 29, 1948
Creator: Crane, Harold L
Description: An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57963/
Calculation of the aerodynamic loading of flexible wings of arbitrary plan form and stiffness
Date: December 24, 1948
Creator: Diederich, Franklin W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57856/
Comparison of National Bureau of Standards ceramic coatings L-7C and A-417 on turbine blades in a turbojet engine
Date: December 22, 1948
Creator: Morse, C Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57997/
Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers III : normal-shock diffuser
Date: December 22, 1948
Creator: Schroeder, Albert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64571/
Longitudinal-stability investigation of high-lift and stall-control devices on a 52 degree sweptback wing with and without fuselage and horizontal tail at a Reynolds number of 6.8 x 10(exp 6).
Date: December 20, 1948
Creator: Foster, Gerald V
Description: Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ratio 2.88, taper ratio 0.625, and NACA 64 (sub 1)-112 airfoil sections normal to the 0.282-chord line, in combination with split flaps, leading-edge flaps, and upper-surface fences. Low-wing and midwing-fuselage aerodynamic characteristics are presented with and without a horizontal tail at various vertical locations. Tests were conducted at a Reynolds number of 6.8 x 10(exp 6).
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57957/
Wind-tunnel investigation of horizontal tails III : unswept and 35 degrees swept-back plan forms of aspect ratio 6
Date: December 17, 1948
Creator: Dods, Jules, B , jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57847/
Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model
Date: December 16, 1948
Creator: Dods, Jules B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57810/