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Correlation of the Trim Limits of Stability Obtained for a PB2Y-3 Flying Boat and a 1/8-Size Powered Dynamic Model

Description: Tests of a PB2Y-3 flying boat were made at the U.S. Naval Air Station, Patuxent River, Md., to determine its hydrodynamic trim limits of stability. Corresponding tests were also made of a 1/8-size powered dynamic model of the same flying boat in Langley tank no. 1. During the tank tests, the full-size testing procedure was reproduced as closely as possible in order to obtain data for a direct correlation of the results. As a nominal gross load of 66,000 pounds, the lower trim limits of the full-size and model were in good agreement above a speed of 80 feet per second. As the speed decreased below 80 feet per second, the difference between the model trim limits and full-scale trim limits gradually became larger. The upper trim limit of the model with flaps deflected 0 deg was higher than that of the full-size, but the difference was small over the speed range compared. At flap deflections greater than 0 deg, it was not possible to trim either the model of the airplane to the upper limit with the center of gravity at 28 percent of the mean aerodynamic chord. The decrease in the lower trim limits with increase in flap deflection showed good agreement for the airplane and model. The lower trim limits obtained at different gross loads for the full-size airplane were reduced to approximately a single curve by plotting trim against the square root of C(sub delta (sub o)) divided by C(sub V).
Date: April 22, 1947
Creator: Garrison, Charlie C.; Goldenbaum, David M. & Hacskaylo, Andrew
Partner: UNT Libraries Government Documents Department

Tank tests of a 1/8-size dynamic model of the PB2Y-3 airplane with increased power: NACA model 131

Description: Report presenting a study of the installation of 1800-horsepower engines in the PB2Y-3 airplane in place of the current 1200-horsepower engines. Stability and spray tests were made to determine the performance of the model on the water when tested at both the present and projected conditions of gross load and engine power. Results regarding aerodynamic tests and hydrodynamic tests are provided.
Date: June 1943
Creator: Bell, Joe W. & Havens, Robert F.
Partner: UNT Libraries Government Documents Department

Tank Tests of an Alternate Hull Form for the Consolidated Vultee PB2Y-3 Airplane

Description: From Summary: "Tests have been made in Langley tank no. I of a dynamic model of the Consolidated Vultee PB2Y-3 airplane. These tests were made using an alternate hull form, the purpose of which was to reduce the bow spray and eliminate the landing instability which are objectionable features of the production design. The major differences from the PB2Y-3 hull included a deeper step to improve the landing stability , and a lengthened forebody and increased beam to reduce the sway in the propellers and on the flaps. The tests showed that the spray characteristics of the revised hull form were much better than that to the production design. In addition the take-off and landing stability of the model with the alternate hull were satisfactory."
Date: November 6, 1946
Creator: Land, Norman S. & Posner, Jack
Partner: UNT Libraries Government Documents Department

Tank Tests of a 1/8-Size Dynamic Model of the PB2Y-3 Airplane with Simulated Jet Motors: NACA Models 131J, 131J-1 and 131J-2

Description: Report presenting an investigation to determine the effect of jet motors on the stability of the PB2Y-3 airplane at a gross load of 76,000 pounds. Results regarding Model 131J, Model 131J-1, and Model 131J-2 are provided.
Date: June 1943
Creator: Bell, Joe W. & Havens, Robert F.
Partner: UNT Libraries Government Documents Department