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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Some flight measurements of pressure-distribution and boundary-layer characteristics in the presence of shock

Some flight measurements of pressure-distribution and boundary-layer characteristics in the presence of shock

Date: July 23, 1948
Creator: Luke, Ernest P & Zalovicik, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing

An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing

Date: May 27, 1948
Creator: Hopkins, Edward J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Date: July 30, 1948
Creator: Perchonok, Eugene; Wishnek, George & Wilcox, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Stability results obtained with Douglas D-558-1 airplane (BuAero No. 37971) in flight up to a Mach number of 0.89

Stability results obtained with Douglas D-558-1 airplane (BuAero No. 37971) in flight up to a Mach number of 0.89

Date: April 22, 1949
Creator: Lilly, Howard C & Barlow, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of 16-inch diameter supersonic ram-jet unit

Free-flight investigation of 16-inch diameter supersonic ram-jet unit

Date: May 28, 1948
Creator: Kinghorn, George F & Disher, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining preliminary values of span-load, shear, bending-moment, and accumulated-torque distributions of swept wings of various taper ratios

Charts for determining preliminary values of span-load, shear, bending-moment, and accumulated-torque distributions of swept wings of various taper ratios

Date: July 6, 1948
Creator: Wollner, Bertram C
Description: Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Date: July 21, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Date: October 7, 1948
Creator: Fisher, Lloyd J & Hoffman, Edward L
Description: Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditching station. The airplane will settle in the water rapidly to the level of the wings with only gradual changes in attitude. The maximum longitudinal deceleration will be between 1.2g and 1.7g in a calm-water ditching.
Contributing Partner: UNT Libraries Government Documents Department
Summary of results of tumbling investigations made in the Langley 20-foot free-spinning tunnel on 14 dynamic models

Summary of results of tumbling investigations made in the Langley 20-foot free-spinning tunnel on 14 dynamic models

Date: December 31, 1948
Creator: Stone, Ralph W , Jr & Bryant, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Initial experiments on flutter of unswept cantilever wings at Mach number 1.3

Initial experiments on flutter of unswept cantilever wings at Mach number 1.3

Date: January 6, 1949
Creator: Tuovila, W J; Baker, John E & Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department