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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics

Date: October 16, 1951
Creator: Graham, David & Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail -     high-lift devices and lateral controls

Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls

Date: February 20, 1953
Creator: Franks, Ralph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons

Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons

Date: December 6, 1954
Creator: Franks, Ralph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 15, 1954
Creator: Koenig, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20

Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20

Date: February 16, 1953
Creator: Franks, Ralph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the gust tunnel of a model of the XBM-1 airplane

Tests in the gust tunnel of a model of the XBM-1 airplane

Date: October 1, 1939
Creator: Donely, Philip & Shufflebarger, C C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the NACA two-dimensional low-turbulence tunnel of airfoil sections designed to have small pitching moments and high lift-drag ratios

Tests in the NACA two-dimensional low-turbulence tunnel of airfoil sections designed to have small pitching moments and high lift-drag ratios

Date: September 1, 1943
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report

Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report

Date: August 1, 1937
Creator: Anderson, Raymond F.
Description: At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward

Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward

Date: January 1, 1936
Creator: Jacobs, Eastman N & Pinkerton, Robert M
Description: A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightly cambered section of moderate thickness having a small pitching-moment coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Date: January 1, 1939
Creator: Abbott, Ira H & Greenberg, Harry
Description: Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients.
Contributing Partner: UNT Libraries Government Documents Department