Add to ORKGA method is presented for estimating the rolling moments caused by wing-tail interference for missiles composed of wing-tail-body combination. The considerations involved in determining the structure of the downwash field behind lifting cruciform wing-body combinations and the rolling moment on cruciform wings of various plan forms induced by an infinite line vortex are discussed in detail. Computations of induced rolling moments for several missile designs are compared with experimental results
This proposal describes the first phase of the work comtemplated for the Missile Design Manual . The...
The coefficients of damping in roll and rolling effectiveness (with differential incidence of the ho...
Presented is a limited review of some experiences in flight testing of missiles and of wing flutter ...
The problem of predicting the induced roll phenomena associated with finned missiles at high angles ...
Previous analytical studies endeavoring to account for vortex induced rolling moments on missiles ha...
An analysis of the effects of wing interference on the tail contributions to the rolling stability d...
The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fine...
uNgN;;:;-a;,Y& By autho~ti and drag characte&tics of a missile c configuration having a body...
The method for predicting wing- tail interference whereby the trailing vortex system behind lifting ...
A method of analysis based on slender-wing theory is developed to investigate the characteristics in...
A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems asso...
A summary and analysis has been made of results obtained in a systematic research program concerned ...
A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...
Hybrid Reynolds Average Navier-Stokes (RANS) - Large Eddy Simulations (LES) have been applied to pre...
PDFJournalAerodynamicsFlight dynamicsTheoremsVorticesFlowRollingAerodynamic stabilityControlUnited S...
This proposal describes the first phase of the work comtemplated for the Missile Design Manual . The...
The coefficients of damping in roll and rolling effectiveness (with differential incidence of the ho...
Presented is a limited review of some experiences in flight testing of missiles and of wing flutter ...
The problem of predicting the induced roll phenomena associated with finned missiles at high angles ...
Previous analytical studies endeavoring to account for vortex induced rolling moments on missiles ha...
An analysis of the effects of wing interference on the tail contributions to the rolling stability d...
The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fine...
uNgN;;:;-a;,Y& By autho~ti and drag characte&tics of a missile c configuration having a body...
The method for predicting wing- tail interference whereby the trailing vortex system behind lifting ...
A method of analysis based on slender-wing theory is developed to investigate the characteristics in...
A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems asso...
A summary and analysis has been made of results obtained in a systematic research program concerned ...
A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...
Hybrid Reynolds Average Navier-Stokes (RANS) - Large Eddy Simulations (LES) have been applied to pre...
PDFJournalAerodynamicsFlight dynamicsTheoremsVorticesFlowRollingAerodynamic stabilityControlUnited S...
This proposal describes the first phase of the work comtemplated for the Missile Design Manual . The...
The coefficients of damping in roll and rolling effectiveness (with differential incidence of the ho...
Presented is a limited review of some experiences in flight testing of missiles and of wing flutter ...