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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Experimental investigation of the stability, control, and induced rolling moments of a canard missile airframe at a Mach number of 1.7

Experimental investigation of the stability, control, and induced rolling moments of a canard missile airframe at a Mach number of 1.7

Date: September 23, 1952
Creator: Chubb, R. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes

A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes

Date: February 25, 1958
Creator: Nusbaum, W. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Date: August 6, 1957
Creator: Brooks, J. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9

Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9

Date: April 24, 1957
Creator: Davis, O. H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculated performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield

Calculated performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield

Date: February 1, 1951
Creator: Doyle, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Date: May 13, 1958
Creator: Kowalski, K. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A flight and analog study of the effect of elevating the radar-boresight axis upon stability and tracking performance of an automatically controlled interceptor

A flight and analog study of the effect of elevating the radar-boresight axis upon stability and tracking performance of an automatically controlled interceptor

Date: October 16, 1957
Creator: Cheatham, D. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on Joukowski Wings

Pressure Distribution on Joukowski Wings

Date: December 1, 1979
Creator: Blumenthal, O.
Description: The hydrodynamics and mathematical models as applied to the potential flow about a Joukowski wing are presented.
Contributing Partner: UNT Libraries Government Documents Department
Elements of the Wing Section Theory and of the Wing Theory

Elements of the Wing Section Theory and of the Wing Theory

Date: December 1, 1979
Creator: Munk, Max M.
Description: Results are presented of the theory of wings and of wing sections which are of immediate practical value. They are proven and demonstrated by the use of the simple conceptions of kinetic energy and momentum only.
Contributing Partner: UNT Libraries Government Documents Department
Flow and Force Equations for a Body Revolving in a Fluid

Flow and Force Equations for a Body Revolving in a Fluid

Date: December 1, 1979
Creator: Zahm, A. F.
Description: A general method for finding the steady flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle is described. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. The application of the steady flow method for calculating the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms is presented and graphs those quantities for the latter forms. In some useful cases experimental pressures are plotted for comparison with theoretical. The pressure, and thence the zonal force and moment, on hulls in plane curvilinear flight are calculated. General equations for the resultant fluid forces and moments on trisymmetrical bodies moving through a perfect fluid are derived. Formulas for potential coefficients and inertia coefficients for an ellipsoid and its limiting forms are presented.
Contributing Partner: UNT Libraries Government Documents Department