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Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel
"The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces" (p. 1).
Date:
July 1941
Creator:
Greenberg, Harry
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
System:
The UNT Digital Library
Considerations of the Total Drag of Supersonic Airfoil Sections
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 different conditions, the circular-arc airfoil may have a higher drag.
Date:
July 1947
Creator:
Ivey, H. Reese & Klunker, E. Bernard
System:
The UNT Digital Library
Principal Effects of Axial Load on Moment-Distribution Analysis of Rigid Structures
"This thesis presents the method of moment distribution modified to include the effect of axial load upon the bending moments. This modification makes it possible to analyze accurately complex structures, such as rigid fuselage trusses, that heretofore had to be analyzed by approximate formulas and empirical rules. The method is simple enough to be practicable even for complex structures, and it gives a means of analysis for continuous beams that is simpler than the extended three-moment equation now in common use" (p. 1).
Date:
July 1935
Creator:
James, Benjamin Wylie
System:
The UNT Digital Library
Effect of exhaust pressure on the performance of a 12-cylinder liquid-cooled engine
Report presenting a dynamometer-stand investigation to determine the effect of exhaust pressure on the performance of a 12-cylinder liquid-cooled aircraft engine equipped with a conventional exhaust collector. The results are presented in the form of curves that show the effect of exhaust pressure on engine power, charge-air flow, volumetric efficiency, inlet-manifold mixture temperature, exhaust-gas temperature, cylinder-head temperature, and heat rejected to the coolant.
Date:
July 1947
Creator:
Desmon, Leland G. & Doyle, Ronald B.
System:
The UNT Digital Library
Theoretical and experimental data for a number of NACA 6A-series airfoil sections
Report presenting theoretical and experimental data for NACA 6A-series basic thickness airfoils, which were designed to eliminate the trailing-edge cusp present in NACA 6-series sections. Results indicated that the section minimum-drag and maximum-lift characteristics of the 6-series and 6A-series airfoil sections are essentially the same. Drag, lift, pitching-moment characteristics, and aerodynamic center are also provided.
Date:
July 1947
Creator:
Loftin, Laurence K., Jr.
System:
The UNT Digital Library
Effect of Geometric Dihedral on the Aerodynamic Characteristics of Two Isolated Vee-Tail Surfaces
Note presenting force tests of two isolated vee-tail surfaces with various amounts of dihedral made to provide an experimental verification of a simplified vee-tail theory and the results are presented which were found to be in good agreement with calculations of previous reports. Plots of the basic test data and summaries of the data in the form of plots of the variation of static-stability derivatives and control-effectiveness parameters with dihedral angle are included.
Date:
July 1947
Creator:
Schade, Robert O.
System:
The UNT Digital Library
Correlation of Experimental and Calculated Effects of Product of Inertia on Lateral Stability
Report presenting a correlation of the experimental and calculated effects of the product of inertia on the stability of lateral oscillations of airplanes. The experimental and calculated boundaries were in good agreement with one another, but neglecting the product of inertia led to wide discrepancies. Results regarding stability and its influence on general flight behavior are provided.
Date:
July 1947
Creator:
McKinney, Marion O., Jr. & Drake, Hubert M.
System:
The UNT Digital Library
Charts for the Determination of Supersonic Air Flow Against Inclined Planes and Axially Symmetric Cones
Report presenting a set of charts for the convenient determination of flow conditions behind a shock wave and at the surface of inclined planes and axially symmetric cones located in a uniform frictionless supersonic air stream. Shock angle, static-pressure coefficient, static-pressure ratio, total-pressure ratio, Mach number ratio, and velocity ratio for two-dimensional and conical flow fields are plotted for a range of free-stream Mach numbers.
Date:
July 1947
Creator:
Moeckel, W. E. & Connors, J. F.
System:
The UNT Digital Library
Experimental Studies of the Knock-Limited Blending Characteristics of Aviation Fuels 2: Investigation of Leaded Paraffinic Fuels in an Air-Cooled Cylinder
Note presenting the relation between knock limit and blend composition of selected aviation fuel components individually blended with virgin base and with alkylate as determined in a full-scale air-cooled aircraft-engine cylinder. Results regarding mixture-response curves, relation of knock limit to blend composition, and correlation of knock ratings are provided.
Date:
July 1947
Creator:
Wear, Jerrold D. & Sanders, Newell D.
System:
The UNT Digital Library
Comparisons of Theoretical and Experimental Lift and Pressure Distributions on Airfoils in Cascade
Note presenting comparisons of theoretical and experimental airfoil lift coefficients and pressure distributions made for two cascades of entrance vanes and three cascades of blower blades with NACA 6-series airfoils, and for one cascade of turbine blades. Results regarding the entrance vanes, blower blades, turbine blades, and possibilities of three-dimensional effects are provided.
Date:
July 1947
Creator:
Katzoff, S.; Bogdonoff, Harriet E. & Boyet, Howard
System:
The UNT Digital Library
Numerical determination of indicial lift and moment functions for a two-dimensional sinking and pitching airfoil at Mach numbers 0.5 and 0.6
Report presenting the indical lift and moment functions for sinking and pitching motion at Mach numbers 0.5 and 0.6. The functions are determined from a knowledge of existing oscillatory coefficients at low reduced frequencies and from approximate expressions of the coefficients at high reduced frequencies. Results regarding determination of indical functions, considerations for indical lift due to penetration of a sharp-edge gust, and approximation of indical functions by analytic expressions are provided.
Date:
July 1952
Creator:
Mazelsky, Bernard & Drischler, Joseph A.
System:
The UNT Digital Library
Experimental investigation of the local and average skin friction in the laminar boundary layer on a flat plate at a Mach number of 2.4
Report presenting average and local skin-friction coefficients for laminar flow on a plate plate at Mach number 2.4 and compared with the laminar-boundary-layer theory of Chapman and Rubesin. The average skin-friction coefficients were calculated by the momentum-loss method from impact-pressure surveys of the boundary layer.
Date:
July 1952
Creator:
Maydew, Randall C. & Pappas, Constantine C.
System:
The UNT Digital Library
Plastic Stress-Strain Relations for Combined Tension and Compression
Note presenting an investigation to determine the validity of the plasticity theories and the correctness of various assumptions made in these theories. Plastic stress-strain relations for biaxial tension-compression principal stresses were determined for a 14S-T4 aluminum alloy. Since the constant-stress-ratio tests cannot distinguish between the flow and deformation theories, variable-stress-ratio tests and special biaxial tests were conducted.
Date:
July 1952
Creator:
Marin, Joseph & Wiseman, H. A. B.
System:
The UNT Digital Library
A probability analysis of the meteorological factors conducive to aircraft icing in the United States
Report presenting an analysis of meteorological icing data obtained in flight and some methods developed for the determination of the various simultaneous combinations of the three basic icing parameters (liquid-water content, drop diameter, and temperature) which would have equal probability of being exceeded in flight, the probability of exceeding any specified group of values of liquid-water content associated with temperature and drop-diameter values in specified ranges. These methods can be used to design ice prevention equipment for aircraft.
Date:
July 1952
Creator:
Lewis, William & Bergrun, Norman R.
System:
The UNT Digital Library
Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects
Note presenting a solution to second order in thickness derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency.
Date:
July 1953
Creator:
Van Dyke, Milton D.
System:
The UNT Digital Library
Low tip Mach number stall characteristics and high tip Mach number compressibility effects on a helicopter rotor having an NACA 0009 tip airfoil section
Report presenting an investigation conducted on the helicopter test tower to determine experimentally the low tip Mach number stall and high tip Mach number drag divergence characteristics of a helicopter rotor with an NACA 0009 tip airfoil section. Results regarding rotor hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.
Date:
July 1958
Creator:
Powell, Robert D., Jr. & Carpenter, Paul J.
System:
The UNT Digital Library
Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4
Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date:
July 1958
Creator:
Fournier, Paul G.
System:
The UNT Digital Library
Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8
Report presenting an investigation using rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack.
Date:
July 1955
Creator:
Sears, R. I. & Merlet, C. F.
System:
The UNT Digital Library
Effects of Thermal Relaxation and Specific-Heat Changes on Measurements With a Pneumatic-Probe Pyrometer
"Equations are derived which evaluate the effects of thermal vibrational relaxation and specific-heat changes on pneumatic-probe pyrometer measurements in the region 1000 to 3000 degrees K and Mach numbers between 0.3 and 2.0. Examples are given for typical probes in two combustion mixtures" (p. 1).
Date:
July 1957
Creator:
Kuhns, P. W.
System:
The UNT Digital Library
Low-speed experimental determination of the effects of leading-edge radius and profile thickness on static and oscillatory lateral stability derivatives for a delta wing with 60 degrees of leading-edge sweep
Report presenting an investigation to determine the effects of leading-edge radius and profile thickness on the oscillatory lateral stability derivatives for a series of delta wings with 60 degrees of leading-edge sweep. The wings were oscillated in yaw about their vertical axes. Results indicated that there were noticeable decreases in all the derivatives due to increase in leading-edge radius at angles of attack above approximately 12 degrees.
Date:
July 1958
Creator:
Fletcher, Herman S.
System:
The UNT Digital Library
Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap
Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date:
July 1958
Creator:
Johnson, Joseph L., Jr.
System:
The UNT Digital Library
Preliminary investigation of propane combustion in a 3-inch-diameter duct of inlet-air temperatures of 1400 to 1600 F
Report presenting a determination of ignition delays and combustion efficiencies for propane injected into a heated airstream. Two types of flames were observed for multipoint fuel injectors: a diffusion flame that stabilized at the injector orifices and an ignition-stabilized flame that formed a flame front downstream of the fuel injector. Results regarding combustion of injector-stabilized flames and combustion of ignition-stabilized flames are provided.
Date:
July 1957
Creator:
Lezberg, Erwin A.
System:
The UNT Digital Library
Boundary-layer development and skin friction at mach number 3.05
Experimental and theoretical results are presented for boundary layer studies consisting of Schlieren observations and momentum surveys made on hollow cylinder models with their axes aligned parallel to the stream. Results were obtained for three model diameters and for natural and artificially induced turbulent boundary layer flows.
Date:
July 1952
Creator:
Brinich, Paul F. & Diaconis, Nick S.
System:
The UNT Digital Library