Resource Type
Collection
Serial/Series Title
5 Matching Results
Results open in a new window/tab.
Results:
1 - 5 of
5
Zirconium Metal Fines Recovery: Interim Technical Report for May 15, 1950 to December 15, 1950
This report covers the laboratory and pilot plant investigation of the reclamation of the low hafnium zirconium fines resulting from the manufacture of zirconium sponge and zirconium crystal bar. The process investigated involved recovery of the zirconium as zirconium tetrachloride, by drying the fines in an atmosphere of nitrogen and subsequent chlorination of the fines with anhydrous hydrogen chloride at temperatures above the sublimation point of the product.
Date:
January 24, 1951
Creator:
Ogburn, S. C., Jr. & Reader, L. J.
System:
The UNT Digital Library
A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf
Report presenting a study of the effect of sweep on wings with the NACA 65A006 airfoil section in the 8-foot high-speed tunnel. This particular investigation included a wing with that airfoil section, 60 degrees of sweepback at the quarter chord, an aspect ratio of 4, and a taper ratio of 0.6. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date:
January 24, 1951
Creator:
Wood, Raymond B. & Fleming, Frank F.
System:
The UNT Digital Library
Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90
Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.
Date:
January 24, 1951
Creator:
Conner, D. William & Mitchell, Meade H., Jr.
System:
The UNT Digital Library
The effects of camber and twist on the aerodynamic loading and stalling characteristics of a large-scale 45 degree swept-back wing
Report presenting pressure-distribution measurements on two large-scale semispan wing-fuselage models with 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and 10-percent-thick sections normal to the quarter-chord line. Adding camber and twist to a wing significantly improved the upper surface loading of the wing at a lift coefficient of 0.4 through a reduction in the peak negative pressure coefficient. Results regarding loading characteristics and stalling characteristics are provided.
Date:
January 24, 1951
Creator:
Hunton, Lynn W. & Dew, Joseph K.
System:
The UNT Digital Library
Analysis of the effects of wing interference on the tail contributions to the rolling derivatives
From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."
Date:
January 24, 1951
Creator:
Michael, William H., Jr.
System:
The UNT Digital Library