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in creator/contributor: "Ivey, H. Reese"  
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Considerations of the Total Drag of Supersonic Airfoil Sections

Description: The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under … more
Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils

Description: Report presenting a velocity-correction formula for the purpose of calculating, from the known Mach number distribution for a diamond-shaped airfoil at a stream Mach number of 1.0, Mach number distributions on the same airfoil at speeds from a Mach number of about 0.8 to shock-attachment Mach number. An expression for the rate of change of local Mach number with stream Mach number is derived and an explicit equation for the drag coefficient as a function of stream Mach number and thickness rat… more
Date: November 1951
Creator: Ivey, H. Reese & Harder, Keith C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Heat-Capacity Lag on the Flow Through Oblique Shock Waves

Description: Report presenting an analysis of the effects of variable heat capacity on the flow parameters for oblique shock waves at high supersonic speeds at sea level. Two sets of data are provided: one for conditions immediately behind the shock wave at active degrees of freedom and another for asymptotic conditions behind the shock wave where all degrees of freedom are in equilibrium.
Date: October 1950
Creator: Ivey, H. Reese & Cline, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Supersonic Lift and Drag Characteristics of Symmetrical Wedge-Shape-Airfoil Sections as Affected by Sweepback Outside the Mach Cone

Description: "The theoretical supersonic section lift and drag characteristics of thin wedge-shape, untapered airfoils with sweepback are presented. The results apply to those parts of the wing in two dimensional flow and are not applicable to wings swept back within the Mach cone of the center section. The results may also be applied to swept-forward wings if the angle of sweep is not enough to put the wing within the Mach cone from the tips" (p. 1).
Date: March 1947
Creator: Ivey, H. Reese & Bowen, Edward N., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Notes on the theoretical characteristics of two-dimensional supersonic airfoils

Description: The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical sup… more
Date: January 1947
Creator: Ivey, H. Reese
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An approximate determination of the lift of slender cylindrical bodies and wing-body combinations at very high supersonic speeds

Description: Report presenting a theory for very high supersonic flow as applied to determine a first approximation to the pressure distribution, lift, and drag due to lift for a slender cylindrical body of revolution and a wing-body combination. The method indicates that the flow effectively separates from the body before reaching the widest part of the cross section.
Date: October 1948
Creator: Ivey, H. Reese & Morrissette, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Charts for determining the characteristics of sharp-nose airfoils in two-dimensional flow at supersonic speeds

Description: Solutions of the Hugoniot shock equations and Meyer expansion equations are plotted in such a manner as to permit the pressure distribution, the local Mach number, and the angles of shock waves on arbitrary sharp-nose airfoils at supersonic speeds to be obtained directly. (author).
Date: January 1947
Creator: Ivey, H. Reese; Stickle, George W. & Schuettler, Alberta
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for determining the aerodynamic characteristics of two-and three-dimensional shapes at hypersonic speeds

Description: Report presenting a method for calculating the pressures on aerodynamic shapes at very high supersonic speeds in dense air with the ratio of specific heats equal to 1. It is applicable to any body of revolution at zero angle of attack and to any two-dimensional profile. Some aerodynamic characteristics of several shapes are calculated, and lift and drag coefficients are shown to be dependent on thickness ratio, thickness distribution, and angle of attack.
Date: July 1948
Creator: Ivey, H. Reese; Klunker, E. Bernard & Bowen, Edward N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Introduction to the Problem of Rocket-Powered Aircraft Performance

Description: An introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating th… more
Date: December 1947
Creator: Ivey, H. Reese; Bowen, Edward N., Jr. & Oborny, Lester F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance Selection Charts for Gliders and Twin-Engine Tow Planes

Description: Report presenting performance charts for gliders and twin-engine tow planes with different degrees of aerodynamic and structural refinement. The glider charts display the gliding angle, useful load, stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various speeds. The tow-plane charts show the stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various sp… more
Date: May 1945
Creator: Ivey, H. Reese; Fitch, G. M. & Schultz, Wayne F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Generalized performance selection charts for single-engine pursuit airplanes

Description: Report presenting an investigation of the effect of wing loading, power loading, and aspect ratio on the performance of pursuit airplanes. The study is based on data combined from specifications, wind-tunnel, and flight tests of various airplanes and presented in graphs.
Date: February 1943
Creator: Ivey, H. Reese; Stickle, George W. & Brevoort, Maurice J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Supersonic Aerodynamic Heating With Continuous Fluid Injection

Description: From Introduction: "The aerodynamic heating problem assumes considerable importance at high-supersonic speeds. Sanger and Bredt (reference 1) have calculated the high-speed aerodynamic forces and equilibrium surface temperature at extremely high altitudes where the molecular mean free path is large (free-molecule-flow region) compared with a characteristic body dimension. The theoretical investigation of Lees (reference 2) on the stability of the laminar boundary layer in compressible flow ind… more
Date: September 29, 1949
Creator: Klunker, E. B. & Ivey, H. Reese
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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