Author: Jack Norman NielsenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
Book Description
A Method for Calculating the Lift and Center of Pressure of Wing-body-tail Combinations at Subsonic, Transonic, and Supersonic Speeds
Author: Jack Norman NielsenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
Book Description
A Method for Calculating the Aerodynamic Loading on Wing-body Combinations at Small Angles of Attack in Supersonic Flow
Author: Charlie M. JacksonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions.
Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack
Author: A. Gerald RaineyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Report
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 90
Book Description
Normal Force, Center of Pressure, and Zero-lift Drag of Several Ballistic-type Missiles at Mach Numbers of 4.05
Author: Edward F. UlmannPublisher:
ISBN:
Category : Ballistic missiles
Languages : en
Pages : 34
Book Description
Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.
An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies
Author: Frankie Gale MoorePublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 148
Book Description
Report
Author: Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies
Author: Thomas C. KellyPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 86
Book Description
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Author: 
Author: