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Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber

Description: From Introduction: "The difficulties experienced in cooling the exhaust-valve seats of the rear-row cylinders have been overcome to a considerable extent by improving the mixture distribution through application of the injection impeller (reference 1) and by augmenting the flow of cooling air to the critical baffles (reference 2). Flight tests of this airplane (reference 3) indicated that the temperatures of exhaust-valve seats on rear-row cylinders were markedly lowered by these modifications … more
Date: March 14, 1946
Creator: Marble, Frank E.; Miller, Marlon A. & Bell, E. Barton
Item Type: Refine your search to only Report
open access

Analysis of Deep Rectangular Shear Web Above Buckling Load

Description: From Introduction: "An analysis of a square web above the buckling load was presented in reference 1. The analysis of reference 1 therefore was repeated for a shear web with depth/width = 2.5. Comparison of the results with those for the square web then would indicate the effect in the depth-width ratio."
Date: March 1946
Creator: Levy, Samuel; Woolley, Ruth M. & Corrick, Josephine N.
Item Type: Refine your search to only Report
open access

Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane

Description: An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver… more
Date: March 1946
Creator: Pearson, Henry A. & Aiken, William S., Jr.
Item Type: Refine your search to only Report
open access

Analysis of X-ray Powder Diffraction Data on Crystalline Uranium Hexafluoride.

Description: From introduction: "The concluding remarks of the report on the electron diffraction study of UF6 suggest two alternate explanations for the apparent discrepancy between the structure proposed for this compound as deduced from X-ray diffraction work on single crystals and from the electron diffraction investigation of the vapor. The second explanation is based on the premise that the difference may be due to essentially unlike methods of treating the diffraction data. In this report we shall an… more
Date: March 5, 1946
Creator: Bauer, S. H. (Simon Harvey), 1911- & Palter, H.
Item Type: Refine your search to only Report
open access

Approximate Formulas for the Computation of Turbulent Boundary-Layer Momentum Thicknesses in Compressible Flows

Description: Report presenting approximate formulas for the computation of the momentum thickness of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow given in the form of integrals that can be conveniently computed. Results for skin-friction formulas, laminar boundary layers, and full thickness of boundary layer are provided.
Date: March 1946
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
open access

Charts for Critical Combinations of Longitudinal and Transverse Direct Stress for Flat Rectangular Plates

Description: Report presenting the use of the energy method to derive interaction equations that define the critical combinations of longitudinal and transverse direct stress for isotropic flat rectangular plates with four different edge conditions. Charts based on the interaction equations are presented for the four cases.
Date: March 1946
Creator: Libove, Charles & Stein, Manuel
Item Type: Refine your search to only Report
open access

Comparison of Tail and Wing-Tip Spin-Recovery Parachutes as Determined by Tests in the Langley 20-Foot Free-Spinning Tunnel

Description: Report presenting tests of spin-recovery parachutes on six models of typical fighter and trainer airplanes conducted in the 20-foot free-spinning tunnel to obtain data for correlating model and full-scale results. Parachutes attached to the tail of the models, to the outer wing tip, to the inner wing tip, and to both wing tips were tested. Results regarding parachute construction, loading variations, effect of test altitude, and action of spin-recovery parachutes are provided.
Date: March 1946
Creator: Kamm, Robert W. & Malvestuto, Frank S., Jr.
Item Type: Refine your search to only Report
open access

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudde… more
Date: March 1946
Creator: Kayten, Gerald G. & Koven, William
Item Type: Refine your search to only Report
open access

A Condition on the Initial Shock

Description: "Initial shocks of the type that occur on airfoils at stream Mach numbers less than unity are shown to satisfy a certain condition, namely, that the local Mach number behind the shock wave tends to approach unity. This result is, in nature, similar to the classic condition of Kutta on the circulation" (p. 1).
Date: March 1946
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
open access

Consideration of Dynamic Loads on the Vertical Tail by the Theory of Flat Yawing Maneuvers

Description: "Dynamic yawing effects on vertical-tail loads are considered by a theory of flat yawing maneuvers. A comparison is shown between computed loads and the loads measured in flight on a fighter airplane. The dynamic effects were investigated on a large flying boat for both an abrupt rudder deflection and sinusoidal rudder deflection" (p. 91).
Date: March 15, 1946
Creator: Boshar, John & Davis, Philip
Item Type: Refine your search to only Report
open access

Critical Combinations of Longitudinal and Transverse Direct Stress for an Infinitely Long Flat Plate With Edges Elastically Restrained Against Rotation

Description: Report presenting a theoretical investigation of the buckling of an infinitely long flat plate with edges elastically restrained against rotation under combinations of longitudinal and transverse direct stress. Interaction curves are presented that give the critical combinations of stress for several different degrees of elastic edge restraint, including simple support and complete fixity.
Date: March 1946
Creator: Batdorf, S. B.; Stein, Manuel & Libove, Charles
Item Type: Refine your search to only Report
open access

Determination of Towline Tension and Stability of Spin-Recovery Parachutes

Description: Report presenting testing of a number of spin-recovery parachutes varying in size in order to determine the force exerted by the parachutes on the towline and the stability of the parachutes. The effects of modifications to the parachutes regarding towline tension and stability are also provided. Results regarding the parachute motions, air forces on parachutes, shock loads, and effects of modifications to line length and canopy vent are provided.
Date: March 1946
Creator: Wood, John H.
Item Type: Refine your search to only Report
open access

Development of Wing Inlets

Description: Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic … more
Date: March 1946
Creator: Racisz, Stanley F.
Item Type: Refine your search to only Report
open access

Effect of Rotor-Tip Speed on Helicopter Hovering Performance and Maximum Forward Speed

Description: Report presenting a study of several sample helicopters in order to evaluate the effect of rotor-tip speed on hovering performance and limiting forward speed. The main purpose of the study was to determine whether hovering performance could be increased by the use of lower tip speeds without undue sacrifice in maximum forward speed. Results regarding typical helicopters, low-solidity helicopters, and high-speed helicopters are provided.
Date: March 1946
Creator: Gustafson, F. B. & Gessow, Alfred
Item Type: Refine your search to only Report
open access

Effects of Fuel-Vapor Loss on Knock-Limited Performance and Inspection Properties of Aviation Fuels

Description: Report discussing the results of testing to discover the effects of fuel-vapor loss on F-3 and F-4 knock-limited performance ratings and inspection properties of two aviation fuels, 28-R and 33-R. The percentage of loss at several temperatures, ability to meet Army-Navy fuel specifications, and antiknock rating change is described.
Date: March 1946
Creator: Barnett, Henry C. & Marsh, Edred T.
Item Type: Refine your search to only Report
open access

An Evaluation of the Knock-Limited Performance of Triptane

Description: Report discussing an investigation of the knock-limited performance of triptane in F-3 and F-4 rating engines, two full-scale air-cooled aircraft cylinders, and flight tests on a full-scale multicylinder engine. Information about the lead susceptibility and effect of engine operating conditions is also provided.
Date: March 1946
Creator: Barnett, Henry C.
Item Type: Refine your search to only Report
open access

Extension of the Chaplygin Proofs on the Existence of Compressible-Flow Solutions to the Supersonic Region

Description: "It has been known for some time that the velocity of sound is not the upper limit for potential flow. S. A. Chaplygin in his paper "On Gas Jets" (NACA TM No. 1063) carried out some interesting proofs on the existence of solutions and gave proofs relating to maxima and minima of certain functions. In the present paper these proofs are extended to include the supersonic potential air-flow field adjacent to the subsonic region treated by Chaplygin" (p. 1).
Date: March 1946
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
open access

Flight Investigation at High Speeds of Profile Drag of Wing of a P-47d Airplane Having Production Surfaces Covered With Camouflage Paint

Description: Report presenting a flight investigation made at high speeds to determine the profile drag of a P-47D airplane wing with production surfaces covered with camouflage paint. The results indicated that a minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach numbers less than 0.67.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
open access

Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
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