Collection
Technical Report Archive and Image Library
431
National Advisory Committee for Aeronautics Collection
366
Texas Attorney General Opinions
258
Office of Scientific & Technical Information Technical Reports
93
TRAIL Microcard Collection
44
World War Two Collection
24
Government Documents A to Z Digitization Project
23
World War Two Newsmaps
18
Texas State Publications
15
USDA Farmers' Bulletins
4
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841 Matching Results
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Gust-tunnel tests to determine influence of airfoil section characteristics on gust-load factors
Report presenting gust-tunnel testing to determine if gust-load factors for airplanes with low-drag wing sections should be higher than those for airplanes with conventional wing sections. A model with a wing with a low-drag section was used with smooth surfaces and with roughness applied to the leading edge to simulate the flow conditions for a conventional section.
Date:
July 1948
Creator:
Pierce, Harold B. & Trauring, Mitchell
Object Type:
Report
System:
The UNT Digital Library
An evaluation of the characteristics of a 10-percent-thick NACA 66-series airfoil section with a special mean-camber line designed to produce a high critical Mach number
Report presenting testing of the low-speed aerodynamic characteristics of the NACA 66-series airfoil section in the two-dimensional low-turbulence pressure tunnel. Results regarding the critical-speed characteristics and low-speed characteristics are provided.
Date:
July 1948
Creator:
Loftin, Laurence K., Jr. & Cohen, Kenneth S.
Object Type:
Report
System:
The UNT Digital Library
Test of six types of Bakelite-bonded wire strain gages
Report presenting results of testing of 10 gages of each of 6 types of multistrand, single-element, bakelite-bonded wire strain gages. Some of the factors investigated included the uniformity of calibration factors for individual gages of the same type, variation of calibration factor with temperature, creep, effect of current on gage resistance, and variation in gage resistance with temperature.
Date:
July 1948
Creator:
Campbell, William R.
Object Type:
Report
System:
The UNT Digital Library
Effects of compressibility on the flow past thick airfoil sections
Report presenting testing of six, 3-inch-chord symmetrical airfoil sections with systemic variations in thickness and maximum-thickness location at Mach numbers near flight values for propeller-shank sections. The tests were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Results regarding flow characteristics and airfoil force characteristics are provided.
Date:
July 1948
Creator:
Daley, Bernard N. & Humphreys, Milton D.
Object Type:
Report
System:
The UNT Digital Library
Lateral stability and control characteristics of a free-flying model having an unswept wing with an aspect ratio of 2
Report presenting testing in the free-flight tunnel to determine the lateral stability, control, and general flying characteristics of a free-flying model with an unswept wing of aspect ratio 2. Testing occurred with a lift coefficient of 1.0 and covered a range of geometric dihedral angles and vertical-tail areas. Results regarding oscillatory stability, lateral control, and general flight behavior are provided.
Date:
July 1948
Creator:
McKinney, Marion O. & Shanks, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Method for Calculation of Pressure Distributions on Thin Conical Bodies of Arbitrary Cross Section in Supersonic Stream
Note presenting an approximate method for calculating the pressure distribution on conical bodies of noncircular cross section in a supersonic flow field. By a superposition of elementary conical flows due to line sources, the flow about an arbitrary cone may be described.
Date:
July 1948
Creator:
Maslen, Stephen H.
Object Type:
Report
System:
The UNT Digital Library
Critical Axial-Compressive Stress of a Curved Rectangular Panel With a Central Chordwise Stiffener
"The theoretical critical stress is derived for a simply supported curved rectangular panel in axial compression having a central chordwise stiffener offering no torsional restraint. The results are presented in the form of computed curves and a table. Because a panel of moderate or large curvature buckles in compression at a stress considerably below the theoretical value, a method is suggested to aid in determining the critical stress for use in design" (p. 1).
Date:
July 1948
Creator:
Batdorf, S. B. & Schildcrout, Murry
Object Type:
Report
System:
The UNT Digital Library
High-speed wind-tunnel investigation of an NACA 65-210 semispan wing equipped with plug and retractable ailerons and a full-span slotted flap
Report presenting a high-speed wind-tunnel investigation to determine the lateral-control characteristics of plug and retractable ailerons on a thin, low-drag, semispan wing equipped with a 25-percent-chord, full-span, slotted flap. The ailerons investigated covered 49 percent of the wing semispan, were located at 70-percent-chord station, and were perforated and segmented. Results regarding the wing aerodynamic characteristics, lateral-control characteristics with the plug aileron, lateral control characteristics with the retractable aileron, and a comparison of the characteristics are provided.
Date:
July 1948
Creator:
Fischel, Jack & Schneiter, Leslie E.
Object Type:
Report
System:
The UNT Digital Library
A method for determining the aerodynamic characteristics of two-and three-dimensional shapes at hypersonic speeds
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.
Object Type:
Report
System:
The UNT Digital Library
Thermodynamic Charts for the Computation of Fuel Quantity Required for Constant-Pressure Combustion With Diluents
Report presenting charts for calculating the quantity of hydrocarbon fuel required to attain a specific combustion temperature when water, alcohol, water-alcohol mixtures, liquid ammonia, liquid carbon dioxide, liquid nitrogen, liquid oxygen, or their mixtures are added to air as diluents or refrigerants.
Date:
July 1948
Creator:
Bogart, Donald; Okrent, David & Turner, L. Richard
Object Type:
Report
System:
The UNT Digital Library
Interaction between the spars of semimonocoque wings with cutouts
"The stresses in the two spars of a model of a wing having three rectangular cutouts were calculated by the PIBAL method, a modification of Southwell's method of systematic relaxations. The model was built and tested in the Polytechnic Institute of Brooklyn Aeronautical Laboratories and the deflections and strains measured were compared with calculated values. The agreement was found to be satisfactory" (p. 1).
Date:
July 1947
Creator:
Hoff, N. J.; Kase, Harry & Liebowitz, Harold
Object Type:
Report
System:
The UNT Digital Library
An investigation of aircraft heaters 31: summary of laboratory testing of several exhaust-gas and air heat exchangers
Report presenting a comparison of the thermal performance and pressure-drop characteristics of heat exchangers on a heat-exchanger test stand. The exchangers included parallel and cross-flow units as well as extended-surface and all-prime-surface units.
Date:
July 1949
Creator:
Boelter, L. M. K.; Guibert, A. G.; Romie, F. E.; Sanders, V. D. & Rademacher, J. M.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of Aircraft Heaters 26: Development of a Sensitive Plated-Type Thermopile for Measuring Radiation
Report presenting an analysis of the factors determining the power efficiency of radiation thermopiles of the type in which receivers consist of parts of conducts themselves or of coatings or other electrically insulating materials in intimate contact with the conductors. Criterions for maximum power efficiency are calculated for these thermopiles, which can then be applied to general thermopile designs.
Date:
July 1948
Creator:
Boelter, L. M. K.; Dempster, E. R.; Bromberg, R. & Gier, J. T.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of Aircraft Heaters 27: Distribution of Heat-Transfer Rate in the Entrance Section of a Circular Tube
"Experimental data on the variation of the point unit thermal conductance in the entrance section of a circular tube are presented for 16 different flow conditions of the entering air. Results are compared with values calculated from existing analytical solutions. The average (integrated mean with length) unit thermal conductance is also calculated for eight entering-air conditions and is compared with values resulting from analytical methods" (p. 1).
Date:
July 1948
Creator:
Boelter, L. M. K.; Young, G. & Iversen, H. W.
Object Type:
Report
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.
Object Type:
Report
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.
Object Type:
Report
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.
Object Type:
Report
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.
Object Type:
Report
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.
Object Type:
Report
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.
Object Type:
Report
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
Object Type:
Report
System:
The UNT Digital Library
A comparative study of weights and sizes of flat-plate exhaust-gas-to-air heat exchangers with and without fins
Note presenting analytical comparisons of weights and volumes for flat-plate heat exchangers with the same calculated thermal output and friction pressure drop for three different fin configurations, including no fins, fins in both the air and exhaust gas passages, and fins in the air passages only. Two different heat exchangers were used and compared with predicted weights and volumes.
Date:
July 1947
Creator:
Tendeland, Thorval & Steinmetz, Charles P.
Object Type:
Report
System:
The UNT Digital Library
Effect of Normal Pressure on Strength of Axially Loaded Sheet-Stringer Panels
Note presenting tests under combined axial load and normal pressure on 29 24S-T aluminum alloy sheet-stringer panels. Empirical formulas were derived for predicting the effect of normal pressure on the strain for buckling of sheet between stringers. Results of buckling, sheet load, strains, buckling, and failure are provided.
Date:
July 1946
Creator:
McPherson, A. E.; Levy, Samuel & Zibritosky, George
Object Type:
Report
System:
The UNT Digital Library
Icing Zones in a Warm Front System With General Precipitation
Note presenting observation of the icing zones present in a warm front cloud system made during one of a series of flights designed to investigate the meteorological conditions conducive to the formation of ice on aircraft.
Date:
July 1947
Creator:
Lewis, William
Object Type:
Report
System:
The UNT Digital Library