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Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229

Description: Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date: December 9, 1947
Creator: King, Douglas A.
Partner: UNT Libraries Government Documents Department
open access

A summary and analysis of data on dive-recovery flaps

Description: From Summary: "The results of numerous unrelated tests of dive-recovery flaps are collected in this report and presented in a form suitable for use in the preliminary design of dive-recovery flap installations. Since the data were obtained for airplane models of quite widely varying configurations, and are limited largely to a Mach number of 0.80, it is recommended that each new installation be carefully flight-tested before final approval. A flight-test procedure is outlined which will insure … more
Date: September 9, 1947
Creator: Boddy, Lee E. & Williams, Walter C.
Partner: UNT Libraries Government Documents Department
open access

Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229

Description: Report presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a dynamic model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The model skipped out of the water and experienced maximum normal accelerations up to 7.4g and maximum longitudinal accelerations up to 4.5g. Results of landing the basic model and landing the modified model that has a slightly different fuselage are provided.
Date: December 9, 1947
Creator: King, Douglas A.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Air Loads Over a Double Slotted Flap on the NACA 65(216)-215, a = 0.8 Airfoil Section

Description: Report presenting an investigation at low speed and high Reynolds number to determine the air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section. Results indicated that the loads on the flap change slowly with variation of angle of attack but quickly with the flap deflected. The main effect of the double-slotted flap is that it causes the airfoil to carry a greater load without stalling.
Date: April 9, 1947
Creator: Visconti, Fioravante
Partner: UNT Libraries Government Documents Department
open access

On Similarity Rules for Transonic Flows

Description: "A method used by Tsien to derive similarity rules for hypersonic flows is utilized to derive Von Karman's similarity rules for transonic flows. At the lower limit of the transonic region of flow the theory yields a formula for the critical stream Mach numbers of a given family of symmetrical profiles. It is further shown that this formula can also be obtained by means of the Prandtl-Glauert small-perturbation method" (p. 83).
Date: December 9, 1947
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department
open access

Theoretical motions of hydrofoil systems

Description: "Results are presented of an investigation that has been undertaken to develop theoretical methods of treating the motions of hydrofoil systems and to determine some of the important parameters. Variations of parameters include three distributions of area between the hydrofoils, two rates of change of downwash angle with angle of attack, three depths of immersion, two dihedral angles, two rates of change of lift with immersion, three longitudinal hydrofoil spacings, two radii of gyration in pit… more
Date: May 9, 1947
Creator: Imlay, Frederick H.
Partner: UNT Libraries Government Documents Department
open access

Use of 1-Ascorbic Acid as a Colorimetric Reagent for Uranium

Description: Abstract: "Hexavalent uranium in weakly acid solution produces with a large excess of ascorbic acid a yellow-brown color whose intensity under certain conditions is a linear function of uranium concentration. Chloride, nitrate, perchlorate, along with Fe, Cd, Mn, Na, Ca, Sn, Mg and Th are without effect on the color while phosphate, sulfate, fluoride, citrate, tartrate, oxalate, chromium, and vanadium and moderate amounts of Ni, Zn, Mo and Al interfere. A rapid ether extraction procedure for pu… more
Date: June 9, 1947
Creator: Rothenberger, C. D. & Grimes, W. R.
Partner: UNT Libraries Government Documents Department
open access

Modified Simpson Methane Flow Proportional Alpha Counter and Fission Counter

Description: Abstract: This technical report consists of series of drawings of the instrument with the following explanation. The modification of the Simpson Methane flow proportional counter consists of a means for inserting and replacing samples into the chamber through an air-lock device which avoids the introduction of even a small quantity of air into the active volume of the chamber. This is accompanied by sweeping out the small volume of the air-lock containing the sample with methane gas before the… more
Date: July 9, 1947
Creator: Freedman, M. S.
Partner: UNT Libraries Government Documents Department
open access

A comparison of three theoretical methods of calculating span load distribution on swept wings

Description: From Summary: "Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl, and J. Weissinger, have been applied to five swept wings. The angles of sweep ranged from -45 degrees to +45 degrees. These methods were examined to establish their relative accuracy and case of application. Experimentally determined loadings were used as a basis for judging accuracy. For the convenience of the readers the computing forms and all information requisite to their ap… more
Date: June 9, 1947
Creator: Van Dorn, Nicholas H. & DeYoung, John
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Development of Means to Alleviate Buffeting of the North American XP-82 Airplane at High Speeds

Description: "This report presents the results of wind-tunnel tests of a 0.22-scale model of the North American XP-82 airplane with several modifications designed to reduce the buffeting of the airplane. The effects of various modifications on the air flow over the model are shown by means of photographs of tufts. The drag, lift, and pitching-moment coefficients of the model with several of the modifications are shown" (p. 1).
Date: January 9, 1947
Creator: Anderson, Joseph L.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Loads on a Conventional Front and Rear Sliding Canopy

Description: "As one phase of a comprehensive canopy load investigation, conventional front and rear sliding canopies which are typified by installation on the SB2C-4E airplane, were tested in the Langley full-scale tunnel to determine the pressure distributions and the aerodynamic loads on the canopies. A preliminary analysis of the results of these tests is presented in this report. Plots are presented that show the distribution of pressure at four longitudinal stations through each canopy for a range of … more
Date: July 9, 1947
Creator: Dexter, Howard E. & Rickey, Edward A.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Tunnel Tests of a 1/24-Scale Model of the Grumman XTB3F-1 Airplane, TED No. NACA DE304

Description: In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for t… more
Date: May 9, 1947
Creator: Berman, Theodore
Partner: UNT Libraries Government Documents Department
open access

A Low-Speed Investigation of a Fuselage-Side Air Inlet for use at Transonic Flight Speeds

Description: "A low-speed investigation in the Langley propeller-research tunnel of annular air inlets designed to avoid compression shocks and attendant boundary-layer separation on the fuselage ahead of the inlets at transonic flight speeds by maintaining substream flow velocities on the fuselage nose was reported in NACA RM No. L6J04. In the present investigation, one of the original annular inlets was converted by the installation of a canopy and a nose-wheel fairing into a twin side inlet in order to s… more
Date: April 9, 1947
Creator: Nichols, Mark R. & Goral, Edwin B.
Partner: UNT Libraries Government Documents Department
open access

Vibration Survey of Blades in 19XB Axial-Flow Compressor 2: Dynamic Investigation

Description: "Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data" (p. 1).
Date: April 9, 1947
Creator: Meyer, André J., Jr. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 4 - Performance and Windmilling Drag Characteristics

Description: The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions.
Date: April 9, 1947
Creator: Fleming, William A. & Dietz, Robert O., Jr.
Partner: UNT Libraries Government Documents Department
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