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Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine
Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.
Date:
April 15, 1954
Creator:
McKann, Robert E. & Petynia, William W.
System:
The UNT Digital Library
Rocket-Powered Model Investigation of Lift, Drag, and Stability of a Body-Tail Configuration at Mach Numbers From 0.8 to 2.3 and Angles of Attack Between Plus or Minus 6.5 Degrees
Report presenting testing of a configuration with a body of fineness ratio 16.6, an unswept horizontal tail of aspect ratio 2.7, and a highly swept vertical tail, which were aeropulsed continuously in pitch during free flight with and without a sustainer rocket motor operating. Results regarding the pitching response, cross coupling, sustainer motor, angle of attack at zero normal force and tail flip, model aerodynamic center, induced jet effect are provided.
Date:
April 15, 1954
Creator:
Gillespie, Warren, Jr. & Dietz, Albert E.
System:
The UNT Digital Library
Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3
Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.
Date:
April 15, 1954
Creator:
Walters, Richard E.
System:
The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
Report presenting an investigation with the objective of eliminating destabilizing changes of pitching moment through the use of wing modifications for two airplane models with triangular wings of aspect ratio 2 and 3. Models were tested with horizontal tails above the extended wing chord plane and with the tail off.
Date:
April 15, 1954
Creator:
Koenig, David G.
System:
The UNT Digital Library
Preliminary investigation of a technique for stability studies of a self-propelled model of a submerged submarine
Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled dynamic submarine model in Langley tank no. 1. Two types of control systems were evaluated, but only one provided satisfactory results at the desired test speeds. Results regarding the qualitative analysis of the control systems, dive paths, equations of motion, and comparison with experimental paths are provided.
Date:
April 15, 1954
Creator:
McKann, Robert E. & Petynia, William W.
System:
The UNT Digital Library