A series of charts is given showing the variation of the velocity gained and the altitude lost in dive pullouts with the initial indicated air speed and the dive angle. The effects of the maximum load factor, the drag parameter K, the initial altitude, and the type of recovery on the velocity gained and the altitude lost are also considered. The results were obtained from a step-by-step solution of the equations of motion in which mean values of the air density and the airplane drag coefficient were used. The load-factor variation with time is arbitrarily specified in various ways to simulate pull-out procedures, some of which might be encountered in flight
The effects of boundary layer flows along the walls of wind tunnels were studied to validate the tra...
These investigations consisted chiefly of measurements of the take-off distance under various starti...
The chief defect of the investigations up to now was the assumption of a more or less arbitrary "mea...
A detailed table of the standard equilibrium velocity and standard equilibrium time is presented for...
The most important factors in evaluating performance of gliders are minimum sinking speed and minimu...
To obtain the absolute velocity of an airship by knowing the speed at which two routes are covered, ...
Following the description of the new propulsion system and the definition of the propulsive efficien...
An empirical method is given for estimating the aerodynamic effect of ordinary and split flaps on ai...
An analysis is made of the stability of an airplane with ailerons free, with particular attention to...
A procedure which takes into account the aerodynamic span effect is given for the determination of t...
Lift (L) and drag (D) characteristics have been obtained in flight for the X-29A airplane (a forward...
Report presents the results of an investigation conducted to determine some of the effects of airfoi...
After a survey of the customary procedures for appraising the profile drag in which pressure drag wa...
This note is the fifth of a series covering an investigation of a number of related airfoils. It pre...
This investigation was made to determine the pressure distribution over a rib of the wing and over a...
The effects of boundary layer flows along the walls of wind tunnels were studied to validate the tra...
These investigations consisted chiefly of measurements of the take-off distance under various starti...
The chief defect of the investigations up to now was the assumption of a more or less arbitrary "mea...
A detailed table of the standard equilibrium velocity and standard equilibrium time is presented for...
The most important factors in evaluating performance of gliders are minimum sinking speed and minimu...
To obtain the absolute velocity of an airship by knowing the speed at which two routes are covered, ...
Following the description of the new propulsion system and the definition of the propulsive efficien...
An empirical method is given for estimating the aerodynamic effect of ordinary and split flaps on ai...
An analysis is made of the stability of an airplane with ailerons free, with particular attention to...
A procedure which takes into account the aerodynamic span effect is given for the determination of t...
Lift (L) and drag (D) characteristics have been obtained in flight for the X-29A airplane (a forward...
Report presents the results of an investigation conducted to determine some of the effects of airfoi...
After a survey of the customary procedures for appraising the profile drag in which pressure drag wa...
This note is the fifth of a series covering an investigation of a number of related airfoils. It pre...
This investigation was made to determine the pressure distribution over a rib of the wing and over a...
The effects of boundary layer flows along the walls of wind tunnels were studied to validate the tra...
These investigations consisted chiefly of measurements of the take-off distance under various starti...
The chief defect of the investigations up to now was the assumption of a more or less arbitrary "mea...