National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

Search Results

Thirty-Ninth Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Reports Nos. 1111 to 1157

Description: This is the fiftieth year since Wilbur and Orville Wright at Kitty Hawk N. C., made their powered flight. That airplane was a fragile and unsteady machine of no immediate utility. It flew for only a minute but it disclosed the solution of the age-old problem of human flight. The Wrights were the first in the history of man to fly. There was no one to teach them. They had to discover principles and to learn the art by cautious and methodical experimenting. From their own research they obtained the practical information needed to design their successful flying machine. The Wrights received no effective aid from the theoretical studies of flight made by the mathematicians of the nineteenth century. The science of aerodynamics was developed in response to the practical demands of aeronautics in the years to follow. In 1908, the Wrights demonstrated at Fort Myer, Va., a vastly improved flyer, the first military airplane. It carried a passenger and flew for more than an hour. Following this public demonstration, the development of the airplane was taken up vigorously. At first France and Germany took the lead, then Great Britain, but the United States lagged behind in the furthering of this greatest American development of the century. With war clouds in view in 1915, the Congress established the National Advisory Committee for Aeronautics to undertake the scientific study of the problems of fight with a view to their practical solution. President Wilson appointed the members of the first Committee, consisting of the heads of the military and civil agencies of the Government concerned with aeronautics and experts from private life.
Date: January 1, 1955
Partner: UNT Libraries Government Documents Department

Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

Description: An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated. Inverted-spin and recovery characteristics of the model were determined for the flight design gross weight loading. The size of the spin-recovery tail parachute necessary to insure satisfactory spin-recovery was determined, and the effect of firing wing-mounded rockets during spins was investigated.
Date: July 1, 1964
Creator: Lee, Henry A. & Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

Description: An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.
Date: June 1, 1964
Creator: Lee, Henry A.
Partner: UNT Libraries Government Documents Department

Detail Calculations of the Estimated Shift in Stick-Fixed Neutral Point Due to the Windmilling Propeller and to the Fuselage of the Republic XF-12 Airplane

Description: Detail calculations are presented of the shifts in stick-fixed neutral point of the Republic XF-12 airplane due to the windmilling propellers and to the fuselage. The results of these calculations differ somewhat from those previously made for this airplane by Republic Aviation Corporation personnel under the direction of Langley flight division personnel. Due to these differences the neutral point for the airplane is predicted to be 37.8 percent mean aerodynamic chord, instead of 40.8 percent mean aerodynamic chord as previously reported.
Date: October 16, 1944
Creator: White, M. D.
Partner: UNT Libraries Government Documents Department

Annual report of the National Advisory Committee for Aeronautics (16th).administrative report including Technical Reports nos. 337 to 364

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1931
Partner: UNT Libraries Government Documents Department

Annual report of the National Advisory Committee for Aeronautics (15th).administrative report including Technical Reports nos. 309 to 336

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1930
Partner: UNT Libraries Government Documents Department

Annual report for the National Advisory Committee for Aeronautics (10th).administrative report including Technical Reports nos. 186 to 209

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1925
Partner: UNT Libraries Government Documents Department

Annual report for the National Advisory Committee for Aeronautics (11th).administrative report including Technical Reports nos. 210 to 232

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1926
Partner: UNT Libraries Government Documents Department

Annual report for the National Advisory Committee for Aeronautics (12th).administrative report including Technical Reports nos. 233 to 256

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1927
Partner: UNT Libraries Government Documents Department

Annual report of the National Advisory Committee for Aeronautics (13th).administrative report including Technical Reports nos. 257 to 282

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1928
Partner: UNT Libraries Government Documents Department

Annual report of the National Advisory Committee for Aeronautics (14th).administrative report including Technical Reports nos. 283 to 308

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: January 1, 1929
Partner: UNT Libraries Government Documents Department

Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Description: Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Partner: UNT Libraries Government Documents Department

The 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics

Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
Date: 1933
Creator: Harris, Thomas A
Partner: UNT Libraries Government Documents Department

The Measurement of Fuel-Air Ratio by Analysis of the Oxidized Exhaust Gas

Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy Fuel Specification, No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs or the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
Date: October 1, 1943
Creator: Memm, J. Lawrence, Jr.
Partner: UNT Libraries Government Documents Department

Summary of Airfoil Data

Description: Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar as possible. The flight data consist largely of drag measurements made by the wake-survey method. Most of the data on airfoil section characteristics were obtained in the Langley two-dimensional low-turbulence pressure tunnel. Detail data necessary for the application of NACA 6-serles airfoils to wing design are presented in supplementary figures, together with recent data for the NACA 24-, 44-, and 230-series airfoils. The general methods used to derive the basic thickness forms for NACA 6- and 7-series airfoils and their corresponding pressure distributions are presented. Data and methods are given for rapidly obtaining the approximate pressure distributions for NACA four-digit, five-digit, 6-, and 7-series airfoils. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed. The data indicate that the effects of surface condition on the lift and drag characteristics are at least as large as the effects of the airfoil shape and must be considered in airfoil selection and the prediction of wing characteristics. Airfoils permitting extensive laminar flow, such as the NACA 6-series airfoils, have much lower drag coefficients at high speed and cruising lift coefficients than earlier types-of airfoils if, and only if, the wing surfaces are sufficiently smooth and fair. The NACA 6-series airfoils also have favorable critical-speed characteristics and do not appear to present unusual problems associated with the application of high-lift and lateral-control devices. Much of the data given in the NACA Advance Confidential Report entitled "Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Number and Low Turbulence," by Eastman N. ...
Date: March 1, 1945
Creator: Stivers, Louis S.; Abbott, Ira H. & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department