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NACA Investigation of Fuels Corresponding to Specification an-F-58 : Results of Studies in Single Combustors of J-33, J-34, J-35, and Nene Turbojet Engines

Description: "The NACA is engaged in a program to evaluate the performance of fuels conforming to AN-F-58 specification in both full-scale engines and single combustors. This research memorandum constitutes an interim report on the results obtained on single cosibustors" (p. 1).
Date: November 16, 1945
Creator: Cleveland Laboratory Staff
Item Type: Refine your search to only Report
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Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Description: Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.
Date: May 7, 1948
Creator: Perkins, Edward W.
Item Type: Refine your search to only Report
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Effect of Centrifugal Force on Critical Flutter Speed on a Uniform Cantilever Beam

Description: Report presenting theoretical calculations made by means of semirigid-flutter theory to determine the effect of centrifugal force on the critical flutter speed of a uniform cantilever beam. Calculations are made on airfoils with fundamental bending frequencies up to 2000 radian per second. Centrifugal force can under certain conditions reduce the critical flutter speed.
Date: June 18, 1948
Creator: Mendelson, Alexander
Item Type: Refine your search to only Report
open access

Lateral-Control Investigation on a 37 Degree Sweptback Wing of Aspect Ratio 6 at a Reynolds Number of 6,800,000

Description: Memorandum presenting the low-speed lateral-control characteristics of a 37 degree sweptback semispan wing of aspect ratio 6 and NACA 64-series airfoil sections in the 19-foot pressure tunnel. The investigation included the measurement of the hinge-moment characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and two configurations of spoilers.
Date: January 27, 1949
Creator: Graham, Robert R. & Koven, William
Item Type: Refine your search to only Report
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The Subsonic Aerodynamic Characteristics of Two Double-Wedge Airfoil Sections Suitable for Supersonic Flight

Description: Memorandum presenting high-speed wind-tunnel testing to investigate the aerodynamic characteristics at subsonic speeds of two symmetrical double-wedge airfoil sections of 4- and 6-percent-chord thickness suitable for application to supersonic aircraft. Section coefficients of lift, drag, and quarter-chord pitching moment are presented for a moderate range of angles of attack at Mach numbers up to approximately 0.93. The double-wedge airfoil exhibits no characteristics other than those common to… more
Date: May 12, 1947
Creator: Solomon, Joseph & Henney, Floyd W.
Item Type: Refine your search to only Report
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The Linear Perturbation Theory of Axially Symmetric Compressible Flow With Application to the Effect of Compressibility on the Pressure Coefficient at the Surface of a Body of Revolution

Description: Memorandum discussing four related methods for the study of compressible flow by means of the linear perturbation theory for the case of three-dimensional flow with axial symmetry. A general method which includes the other is also discussed briefly. In each case, the properties of the compressible flow are obtained from those of a corresponding incompressible flow.
Date: July 18, 1947
Creator: Herriot, John G.
Item Type: Refine your search to only Report
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Theoretical Investigation of the Dynamic Lateral Stability Characteristics of Douglas Design No. 39C, an Early Version of the X-3 Research Airplane

Description: Contains results of calculations made to determine the neutral oscillatory stability boundaries, period and time to damp of the oscillatory mode, and motions following disturbances. The calculations were made for Mach numbers of 0.75 and 2.3 at an attitude of 35,000 feet and for the landing condition at sea level.
Date: January 18, 1949
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
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The use of perforated inlets for efficient supersonic diffusion

Description: Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date: June 25, 1947
Creator: Evvard, John C. & Blakey, John W.
Item Type: Refine your search to only Report
open access

Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Description: Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.
Date: April 7, 1949
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
open access

High-Speed Aerodynamic Characteristics of a Lateral-Control Model 1: NACA 0012-64 Section with 20-Percent-Chord Plain Aileron and 0 Degree and 45 Degrees Sweepback

Description: Memorandum describing wind-tunnel tests made to determine the aerodynamic characteristics of a 20-percent-chord plain aileron on a semispan wing with the NACA 0012-64 section. The report includes the results of tests of the wing unswept and swept back 45 degrees and with the aileron deflected from 0 to 10 degrees.
Date: September 27, 1948
Creator: Anderson, Joseph L. & Krumm, Walter J.
Item Type: Refine your search to only Report
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 3: The Effectiveness of a Constant-Chord Aileron

Description: Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.
Date: November 19, 1948
Creator: Johnson, Ben H., Jr. & Demele, Fred A.
Item Type: Refine your search to only Report
open access

An Investigation of the Characteristics of Three NACA 1-Series Nose Inlets at Subcritical and Supercritical Mach Numbers

Description: Report presenting an investigation of the characteristics of three representative NACA 1-series nose inlets over a Mach number range extending from 0.4 to 0.925 in the high-speed wind tunnel. Results regarding pressure distribution, drag, and some potential design considerations are provided.
Date: January 13, 1949
Creator: Pendley, Robert E. & Smith, Norman F.
Item Type: Refine your search to only Report
open access

A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models

Description: Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date: July 15, 1947
Creator: Jessen, Henry, Jr.
Item Type: Refine your search to only Report
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A Preliminary Theoretical Study of Aerodynamic Instability of a Two-Blade Helicopter Rotor

Description: Report presenting numerical results of flutter calculations for a two-blade helicopter using a see-saw-type rotor. The stability condition for oscillatory motion is expressed in terms of a small number of composite parameters that are evaluated from moments of inertia, angle settings, and aerodynamic parameters of a blade. The analysis indicated that a see-saw rotor with a coning angle is more unstable than an airplane wing with the same parameters.
Date: March 18, 1947
Creator: Coleman, Robert P. & Stempin, Carl W.
Item Type: Refine your search to only Report
open access

Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Item Type: Refine your search to only Report
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Investigation of spark gaps subjected to altitude and air velocity conditions

Description: Report presenting a study of the effects of air velocity on the energy and power of the spark in a constant ignition source and the duration of the spark discharge in the spark gap for various conditions of electrode spacing, electrode diameter, air temperature, and pressure. Energy and average power increased with pressure, velocity, and electrode spacing and electrode diameter and air temperature had negligible effect.
Date: November 24, 1948
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
open access

Yaw Characteristics of a 52 Degree Sweptback Wing of NACA 64(Sub 1)-112 Section With a Fuselage and With Leading-Edge and Split Flaps at Reynolds Numbers From 1.93 X 10(Exp 6) to 6.00 X 10(Exp 6)

Description: Report presenting low-speed testing in the pressure tunnel to determine the aerodynamic characteristics in yaw of a 52 degree sweptback wing with aspect ratio 2.88 and taper ratio 0.625 with NACA 64(sub 1)-112 airfoil sections. Testing included an investigation of the effects on the lateral stability of a fuselage and leading-edge and split flaps. Results regarding the lateral stability parameters of a plain wing, effect of flaps on the lateral stability parameters, effect of scale, and airflow… more
Date: November 8, 1948
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
open access

Estimation of Lift and Drag of Airfoils at Near Sonic Speeds and in the Presence of Detached Shock Waves

Description: Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.
Date: February 23, 1949
Creator: Mayer, John P.
Item Type: Refine your search to only Report
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Measurements of the damping in roll of large-scale swept-forward and swept-back wings

Description: Report presenting wind-tunnel testing of five large-scale tapered wings with a variety of angles of sweep to determine the effects of scale and sweep on the damping-in-roll parameter. Rolling moment and pressure distribution were measured for each plain wing while in steady roll for a range of angles of attack. Results regarding the effects of sweep at zero lift, effects of lift, and aurorotational characteristics are provided.
Date: July 30, 1947
Creator: Hunton, Lynn W. & Dew, Joseph K.
Item Type: Refine your search to only Report
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Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers of 3.30, 2.75, and 2.45

Description: Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure rec… more
Date: November 10, 1948
Creator: Ferri, Antonio & Nucci, Louis M.
Item Type: Refine your search to only Report
open access

Two-dimensional aerodynamic characteristics of 34 miscellaneous airfoil sections

Description: The aerodynamic characteristics of 34 miscellaneous airfoils tested in the Langley two-dimensional low-turbulence tunnels are presented. The data include lift, drag, and in some cases, pitching-moment characteristics, for Reynolds numbers between 3.0 x 10 (exp 6) and 9.0 x 10 (exp 6).
Date: January 31, 1949
Creator: Loftin, Laurence K., Jr. & Smith, Hamilton A.
Item Type: Refine your search to only Report
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The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions

Description: Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.
Date: April 10, 1947
Creator: Allen, H. Julian; Heaslet, Max A. & Nitzberg, Gerald E.
Item Type: Refine your search to only Report
open access

Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Item Type: Refine your search to only Report
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