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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

Date: December 22, 1949
Creator: Fisher, Lloyd J.
Description: An investigation of a 1/18-scale dynamically similar model of the North American B-45 airplane was made to observe the ditching behavior and determine the proper landing technique to be used in an emergency water landing. Various conditions of damage were simulated to determine the behavior which probably would occur in a full-scale ditching. The behavior of the model was determined from high-speed motion-picture records, time-history acceleration records, and visual observations. It was concluded that the airplane should be ditched at the maximum nose-high attitude with the landing flaps full down for minimum landing speed. During the ditching, the nose-wheel and bomb-bay doors probably will be torn away and the rear of the fuselage flooded. A violent dive will very likely occur. Longitudinal decelerations of approximately 5g and vertical accelerations of approximately -6g (including gravity) will be experienced near the pilots' compartment. Ditching braces installed in the bomb bay will tend to improve the behavior slightly but will be torn away along with the bomb-bay doors. A hydroflap installed ahead of the nose-wheel doors will eliminate the dive and failure of the nose-wheel doors, and substantially reduce the motions and accelerations.
Contributing Partner: UNT Libraries Government Documents Department
Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor

Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor

Date: December 20, 1949
Creator: Bond, Aleck C.
Description: A flight test of the Aero jet Engineering Corporation's 7KS-6000 T-27 Jato rocket motor was conducted at the Langley Pilotless Aircraft Research Station at Wallops Island, Va, to determine the flight performance characteristics of the motor. The flight test imposed an absolute longitudinal acceleration of 9.8 g upon the rocket motor at 2.8 seconds after launching. The total impulse developed by the motor was 43,400 pound-seconds, and the thrusting time was 7.58 seconds. The maximum thrust was 7200 pounds and occurred at 4.8 seconds after launching. No thrust irregularities attributable to effects of the flight longitudinal acceleration were observed. Certain small thrust irregularities occurred in the flight test which appear to correspond to irregularities observed in static tests conducted elsewhere. A hypothesis regarding the origin of these small irregularities is presented.
Contributing Partner: UNT Libraries Government Documents Department
A free-flight technique for measuring damping in roll by use of rocket-powered models and some initial results for rectangular wings

A free-flight technique for measuring damping in roll by use of rocket-powered models and some initial results for rectangular wings

Date: December 20, 1949
Creator: Edmondson, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of effectiveness of coordinated turns and level sideslips for correcting lateral displacement during landing approaches

Comparison of effectiveness of coordinated turns and level sideslips for correcting lateral displacement during landing approaches

Date: December 15, 1949
Creator: Faber, Stanley
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-speed investigation of deflectable wing-tip ailerons on an untapered 45 degrees sweptback semispan wing with and without an end plate

Low-speed investigation of deflectable wing-tip ailerons on an untapered 45 degrees sweptback semispan wing with and without an end plate

Date: December 14, 1949
Creator: Fischel, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary investigation of a variable mass-flow supersonic nose inlet

Preliminary investigation of a variable mass-flow supersonic nose inlet

Date: December 13, 1949
Creator: Hayes, Clyde
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparative tests of the rolling effectiveness of constant-chord, full-delta, and half-delta ailerons on delta wings at transonic and supersonic speeds

Comparative tests of the rolling effectiveness of constant-chord, full-delta, and half-delta ailerons on delta wings at transonic and supersonic speeds

Date: December 12, 1949
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction

Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction

Date: December 12, 1949
Creator: Edwards, Sherman S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees

The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees

Date: December 9, 1949
Creator: Rolls, L Stewart
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

Date: December 8, 1949
Creator: Scher, Stanley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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