Book Description
Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies.
Author : Ernie L. Anglin
Publisher :
Page : 100 pages
File Size : 37,40 MB
Release : 1971
Category : Airplanes
ISBN :
Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies.
Author : Ernie L. Anglin
Publisher :
Page : 0 pages
File Size : 26,34 MB
Release : 1971
Category : Airplanes
ISBN :
Author : Ernie L. Anglin
Publisher :
Page : 89 pages
File Size : 20,92 MB
Release : 1971
Category : Airplanes
ISBN :
Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies.
Author : Ernie L. Anglin
Publisher :
Page : 89 pages
File Size : 27,71 MB
Release : 1971
Category :
ISBN :
Author : Joseph R. Chambers
Publisher :
Page : 60 pages
File Size : 47,16 MB
Release : 1969
Category : Aircraft
ISBN :
Jet fighter aircraft lateral directional stability at high angles of attack.
Author : Sue B. Grafton
Publisher :
Page : 44 pages
File Size : 37,26 MB
Release : 1971
Category : Airplanes
ISBN :
A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -10 [degree] to 110 [degree] for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to determine the effects of these variables on the stability derivatives. The effect of the vertical and horizontal tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very high angles of attack associated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives.
Author : R. W. Butler
Publisher :
Page : 50 pages
File Size : 33,52 MB
Release : 1981
Category : Angle of attack (Aerodynamics)
ISBN :
A captive testing technique capable of simulating aircraft maneuvers at high angles of attack has been developed and tested in the Aerodynamic Tunnel 16T of the Arnold Engineering Development Center (AEDC). The captive technique uses a closed loop system between wind tunnel, model, and computer. Use of the wind tunnel as an analog forcing function eliminates the requirement for a conventional static data matrix in motion simulation. Various high angle-of-attack maneuvers (rudder roll, aileron roll, wind-up turn, etc.) were generated with the captive system and show good correlation with flight data. (Author).
Author : John W. Draper
Publisher :
Page : 24 pages
File Size : 27,84 MB
Release : 1949
Category : Airplanes
ISBN :
Author : Sue B. Grafton
Publisher :
Page : 60 pages
File Size : 40,26 MB
Release : 1972
Category :
ISBN :
Author :
Publisher :
Page : 410 pages
File Size : 25,82 MB
Release : 1967
Category : Airplanes
ISBN :