Investigation Of The Aerodynamic Characteristics In Pitch And Sideslip Of A 45 Sweptback Wing Airplane Model With Various Vertical Locations Of The Wing And Horizontal Tail
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| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 39 |
| Release | : 1955 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch of a supersonic airplane configuration at a Mach number of 2.01. The model is equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 with NACA 65A004 airfoil sections, whereas the horizontal tail had a taper ratio of 0.6 with NACA 65A006 airfoil sections.
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 159 |
| Release | : 1955 |
| Genre | : |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 39 |
| Release | : 1955 |
| Genre | : |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch of a supersonic airplane configuration at a Mach number of 2.01. The model is equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 with NACA 65A004 airfoil sections, whereas the horizontal tail had a taper ratio of 0.6 with NACA 65A006 airfoil sections.
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 29 |
| Release | : 1957 |
| Genre | : |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1959 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 159 |
| Release | : 1955 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Clarence L. Gillis |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1960 |
| Genre | : Airplanes |
| ISBN | : |
A test and analysis method is presented for determining airplane lateral stability characteristics, including aerodynamic derivatives, from flight tests of scale models. The method of analysis utilizes the rotating time-vector concept and also a quasi-static approach. Data are presented at transonic speeds for three swept-wing rocket-propelled models differing only in vertical position and dihedral of the wing. The method proved to be adequate for delineating the major effects of the geometric variations on the aerodynamic lateral stability derivatives. The effects of Reynolds number on the linearity of the static stability data for an unswept wing configuration are illustrated.
