National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

Search Results

Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data
Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Ditching Tests With 1/10-Size Model of the Army a-20a Airplane 1: Calm-Water Tests in NACA Tank No.2
Report presenting tests to determine the behavior of landplanes when they are forced to land on the water. The report is incomplete.
The De Havilland 61 "Canberra" (British): A 6-8 Passenger Airplane
Made for an Australian buyer, the Canberra is capable of carrying a payload of 1900 lbs. with a top speed of 126 M.P.H. At 105-110 M.P.H. it has a range of about 475 miles. It has a single Jupiter VI engine.
The Armstrong Whitworth A.W. 16 Military Airplane (British): A Single-Seat Biplane
Circular presenting a description of the A.W. XVI, which is a single-bay staggered biplane of metal construction with a clean external design. A description of the tail unit, control system, cockpit, fuselage, characteristics, performance, drawings, and photographs are provided.
Nieuport-Delage 640 (French): Commercial High-Wing Monoplane
The Nieuport Delage 640 is a single engine commercial high-wing monoplane of all wood construction, including the fuselage and tail. It's landing gear is hinged in two parts.
The Mureaux "Brunet 3C2" Pursuit Airplane
Designed by Engineer Brunet, the 3C2 is an all metal monoplane with two engines and provision for six machine guns and 12 10 Kg. bombs. A description of the design, components, characteristics, flying qualities, drawings, and photographs are provided.
Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds
Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
The "I.A.R." Pursuit Airplane (Roumanian) : A One-Place Cantilever Low-Wing Monoplane
Circular presenting a description of the I.A.R. pursuit airplane. Details of the design, ailerons, fuselage, fuel tanks, landing gear, and flying qualities are provided.
The Dewoitine D 33 Commercial Airplane (French): A Low-Wing Cantilever Monoplane
Circular describing the Dewoitine D 33 commercial airplane, which is a low-wing cantilever monoplane. Details of the wing, fuel tanks, fuselage, landing gear, controls, engine, characteristics, drawings, and photographs are provided.
The development and application of high-critical-speed nose inlets
From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was undertaken in the Langley 8-foot high-speed tunnel to establish the effects of nose-inlet proportions on critical Mach number and to develop a rational method for the design of high-critical-speed nose inlets to meet desired requirements."
An Experimental Investigation of Rectangular Exhaust-Gas Ejectors Applicable for Engine Cooling
Report presenting an experimental investigation of rectangular exhaust-gas ejector pump to provide data that would serve as a guide to the design of ejector applications for aircraft engines with marginal cooling. With a decrease in the quantity of air pumped and an increase in the length of an ejector, the ejector pressure rise increases to optimum values. Results regarding straight ejectors, diffuser ejectors, curved ejectors, ejector aspect ratio, divided ejectors, multistage ejectors, and nozzle-exit effects are provided.
Lift Theory of Supporting Surfaces: Second Article
Memorandum presenting a description of the hydrodynamic lift theory of supporting services. This report is mainly about the task of finding suitable wing sections for given lift conditions. Formulas are given for lift magnitude and moment, which make it possible to obtain solutions of great simplicity and clearness.
The S.A.B.C.A. "S.XI" Commercial Airplane (Belgian): A High-Wing Semicantilever Monoplane
Circular describing the S.A.B.C.A. S.XI commercial airplane, which is a high-wing semicantilever monoplane. Details of the history of its creation, its design, components, engines, fuel tanks, characteristics, performances, drawings, and photographs are provided.
Wind-Tunnel Investigation of the Effects of Spoilers on the Characteristics of a Low-Drag Airfoil Equipped With a 0.25-Chord Slotted Flap
Report discussing the effects of circular-arc spoilers on the section characteristics of an NACA 66,2-216 airfoil with a 0.25-chord slotted flap. Spoilers were tested on the upper surface of the airfoil, on the lower surface, and on both simultaneously. Only the simultaneous placement of spoilers was found to provide satisfactory results as a lateral control device.
The S.P.C.A. 30 M.4 Military Airplane (French): A Multiplace Low-Wing Airplane
Circular describing the S.P.C.A. 30 M.4 multiplace, which is an aircraft designed to carry four people that can be used as a fighter aircraft or a day or night bomber. Details of the design, components, engines, characteristics, performance, drawings, and photographs are provided.
The Bernard 80 G.R. Long-Distance Airplane (French) : A Two-Place Cantilever Monoplane
Circular presenting a description of the Bernard 80 aircraft. Details are provided on the body shape, wings, ribs, fuel requirements, and flight characteristics.
Reciprocity relations in aerodynamics
From Introduction: "The purpose of the present paper is twofold. First, a close connection will be established between reverse-flow theorems in subsonic and supersonic, steady-state wing theory and known reciprocity relations between two solutions of the equation the flow field."
Les Mureaux "130.a2" Observation Airplane (French): A High-Wing Two-Seat Monoplane
Circular presenting Les Mureaux 130.A2, which is a high-wing two-seat observation monoplane. A description of the design, performances, components, performance qualities, photographs, and drawings are provided.
Effect of Roughness on Properties of Airfoils
The first group of a large series of contemplated experiments on the effect of roughness was intended to show the effect of great roughness on airfoils of various sizes and attitudes.
An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 5: Effect of Thermal System on Airplane Cruise Performance
Report presenting flight tests conducted to evaluate the effect of a thermal ice prevention system on the aerodynamic performance of a C-46 cargo airplane. The installation of the thermal ice-prevention system was found to reduce the indicated airspeed by about 6 miles per hour. Results regarding the overall performance change resulting from the installation of the thermal system, reduction of power attributed to heat-exchanger exhaust-gas back pressure, reduction of power attributed to the internal and external drag of the thermal system, and the additional airplane gross weight attributed to the thermal system are provided.
Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26
Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Blériot-Spad 91 Airplane (French): Pursuit Single-Seater, Type "Jockey"
Report presenting a description of the design of the Blériot-Spad 91 airplane. This aircraft has announced a speed of 270 km per hour at 4000 m. It is of all metal construction.
On the Flow of a Compressible Fluid by the Hodography Method 1: Unification and Extension of Present-Day Results
Report presenting elementary basic solutions of the equations of motion of a compressible fluid in the hodograph variables are developed and used to provide a basis for comparison in the form of velocity correction formulas, of corresponding compressible and incompressible flows.
D.H. 86 "Express Air Liner" (British): A Four-Engine Biplane
Circular describing the De Havilland Express Air Liner, which is a four-engine two-bay biplane of clean and well-streamlined form. Details of the cabin, controls, fuselage, tail, wings, engines, cockpit, characteristics, performance, drawings, and photographs are provided.
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report
In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
Lioré-Olivier Airplane: Type 12 Night-Bomber or Type 20 Commercial
Report presenting a description of the Lioré-Olivier Type 12 night bomber, which can also be converted into the Type 20 commercial. A description of the cell of the wings, fuselage, power plant, landing gear, and flight characteristics is provided.
An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 3: Description of Thermal Ice-Prevention Equipment for Wings, Empennage, and Windshield
Report presenting an investigation of a thermal ice-prevention system for a Curtiss-Wright C-46 airplane, including the equipment for the wings, empennage, and windshield. The report is the third in a series and focuses on the revisions to the components for thermal ice prevention, the temperature- and pressure-measurement equipment installed in the airplane to determine the performance of the system, and the results of static-load structural tests of a specimen of the wing outer-panel leading edge.
The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates
"The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the truss, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Raleigh-Rite method of finding upper limits" (p. 1).
Flight Measurements of the Effect of Various Amounts of Aileron Droop on the Low-Speed Lateral-Control Characteristics of an Observation Airplane
Report presenting tests of the low-speed lateral-control characteristics of an observation airplane with ailerons and spoilers in combination and with the spoilers disconnected and the ailerons used alone with various amounts of droop. The results indicated that in unstalled flight at low speeds and with flaps deflected, little or no aerodynamic benefit was derived by changing the lateral-control system from the aileron and spoiler combination to a normal aileron installation either with or without aileron droop.
The Comper "Streak" Single Seat Airplane (British): A Low-Wing Cantilever Monoplane
Circular describing the Comper Streak single-seat low-wing cantilever monoplane. Details of the fuselage, construction, wing, stabilizer, engine, landing gear, characteristics, drawings, and photographs are provided.
An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 4: Results of Flight Tests in Dry-Air and Natural-Icing Conditions
Report presenting an investigation of a thermal ice-prevention system for a C-46 cargo airplane, which involved flight tests in dry-air and natural-icing conditions at two different laboratories. The purpose of the investigation was to determine the effectiveness of the C-46 airplane ice-prevention system and to continue the develop of thermal ice-prevention equipment. Results regarding the wing outer panel, wing tips, wing center panel, horizontal stabilizers, vertical fin, windshields, ice-removal tests, unprotected surfaces, and heat exchangers are provided.
The S.P.C.A. 40 T Commercial Airplane (French): An All-Metal Cantilever Monoplane
Circular describing the S.P.C.A. 40 T, which is a commercial all-metal cantilever airplane that was guided by the two essential requirements of economy and safety in its design. Details of the design, power, test results, fuel tanks, characteristics, performances, drawings, and photographs are provided.
The Unsteady Lift of a Finite Wing
Note discussing the lift of a finite wing including the calculations and constants for each step of the lift. This information is compared against the lift of an infinite wing. From Summary: "Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less. The calculations indicate that the distribution of lift near the start is similar to the final distribution."
Determination of General Relations for the Behavior of Turbulent Boundary Layers
Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System
Report presenting an analysis of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers
Report presenting flight measurements made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. Pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel.
The Use of Geared Spring Tabs for Elevator Control
Report discussing the use of two types of geared spring tabs for elevator control: ordinary (or ungeared) spring tabs and geared spring tabs. Their use in airplanes of various sizes and in comparison to conventional control systems is described.
The D.H. "Fox Moth" Commercial Airplane (British): A Three-Passenger Light Cabin Biplane
Circular describing the D.H. 83 "Fox Moth", which is a three-passenger light cabin biplane that is considered a commercial airplane despite taking many of its components from the company's existing two-seat touring and training light airplanes. A description of these components, design, flight characteristics, performance, drawings, and photographs are provided.
Avia Pursuit Airplane B.H. 21
Built by the 'Czecho-Slovakian' aircraft factory, AVIA, the B.H. 21, has a top speed of 250 MPH, and carries 120 kg of gasoline and 20 kg of oil, giving it a radius of action of 600-650 km. It is equipped with a Hispano-Suiza engine capable of 300 HP. Details of the design, structure, wings, stabilizer, fuselage, controls, fuel tanks, landing gear, tail, characteristics, performances, drawings, and photographs are provided.
A general representation for axial-flow fans and turbines
From Summary: "A general representation of fan and turbine arrangements on a single classification chart is presented which is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed."
The Hanriot H 431 Military Airplane (French): A General Purpose Biplane
Circular presenting a description of the Hanriot H 431, which was designed to meet the requirements of the French War Ministry for general purpose airplanes. Details are provided for the design, flying qualities, and improvements over other aircraft designs.
An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 6: Dry-Air Performance of Thermal System at Several Twin- and Single-Engine Operating Conditions at Various Altitudes
Report presenting flight tests to establish the dry-air-performance characteristics of a thermal ice-prevention system at various operating conditions and altitudes. Results regarding twin-engine tests and single-engine tests of characteristics such as skin temperatures and location of heating are provided.
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.
The Short "Valetta" Commercial Seaplane (British): A High-Wing All-Metal Twin-Float Monoplane
Circular presenting the Valetta, which is a twin-float seaplane and flying boat with a power plant comprised of three Bristol "Jupiter" XI F geared engines. A description of the design, characteristics, performance, blueprints, and photographs are provided.
An Investigation of Aircraft Heaters 9: Measured and Predicted Performance of Two Exhaust Gas-Air Heat Exchangers and an Apparatus for Evaluating Exhaust Gas-Air Heat Exchangers
Report presenting laboratory testing to determine the thermal output and pressure drop characteristics of the Airesearch and Solar fluted-type exhaust gas-air heat exchangers. The apparatus used in these tests consisted of a natural gas furnace of 3,000,000 Btu per hour thermal capacity, a centrifugal blower, and a system of ducting and various measuring devices. Results regarding the method of analysis, the Airesearch heat exchanger tests, the solar heat exchanger tests, and a comparison of the two heat exchangers are provided.
Baynes Bee Light Airplane (British): A Two-Seat High-Wing Monoplane
Circular presenting a description of the Baynes Bee, which is a light two-seat high-wing monoplane. Details of its unique qualities, design, components, flying qualities, drawings, and photographs are provided.
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
Report presenting tests on an exhaust-gas turbine with four separate nozzle boxes each covering a 90 degree arc of the nozzle diaphragm and each connected to a pair of adjacent cylinders in a Pratt & Whitney R-1340-12 nine-cylinder radial engine. Results regarding the power output of the engine and turbine, effect of the turbine on engine power, turbine power output and speed characteristics, mean turbine efficiency, effect of the blowdown turbine on exhaust-gas temperature, and condition of the blowdown turbine after tests are provided.
Nieuport-Delage 590 Military Airplane (French): A Two-Place High-Wing Cantilever Monoplane
Circular presenting a description of the Nieuport-Delage 590 three-engine colonial cantilever monoplane, which meets the requirements of the program established by the French Government. Information is provided regarding the design, construction, and instruments are provided.
The Bleriot 110 Airplane (French): A Long-Distance High-Wing Monoplane
Circular presenting a description of the Bleriot 110 which is a long-distance airplane mainly distinguished by its fineness and lightness. Details of the fuselage, shape, wing, and power plant are provided.
Breguet 390 T Commercial Airplane (French): A Ten-Seat All-Steel Sesquiplane
Circular presenting a description of the Breguet 390 T, which is a three-engine all-metal transport sesquiplane with the same structural principles as the Breguet military airplane. This aircraft design replaces a girder fuselage with an orthodox rectangular fuselage with accommodations for ten passengers and baggage. Details of the design, components, flying qualities, drawings, and photographs are provided.
Back to Top of Screen