DCS: F/A-18C

Dentro del software del avión o en DCSW?

Yo me refería a que en el F18 Rhino, cuando llevas el visor del caso, cuando éste coincide con el HUD, el visor del caso deja de representar el HUD y pasa a ser el principal este último.

Puede que dentro de la página DATA o en el UFC puedas gestionar si se quita o no.

La información del visor desaparece automáticamente cuando miras el HUD, estamos de acuerdo.

Lo que digo es que en la página de gestión del visor hay dos filtros Reject1 y Reject2 que quitan símbología del visor y además se puede activar o desactivar individualmente cada elemento a voluntad.

Por último se puede desactivar el visor a voluntad para no tenerlo siempre conectado.

Ah, pues no me había dado cuenta al ver el vídeo, pensaba que era el piloto (virtual) el que andaba quitando y poniendo el JHMCS.

Pues entonces va a ser un flipe! :o

Copy.

Duplica las funciones de quitar símbolos en el visor al igual que en el HUD.

Genial, gracias.

Una explicación que merece la pena reproducir.

Aircraft Flight with Folded Wings Explanation
With the release of DCS: F/A-18C Hornet, we’ve observed some confusion and false-assumptions regarding how an aircraft can fly, or even take off, with its wings folded up. The answer: physics.

For folded-wing aircraft’s flight characteristics, we conducted calculations for the wings and stabilators in XFLR5 software. The calculations were done using VLM (Vortex Lattice Method) with a non-viscous flow model. The program then determines the characteristics of the linear area of lifting force dependence based on the angle of attack. For horizontal flight, we have the following equation to calculate how the forces are balanced in the vertical plane:

ρv2/2 SСL= mg

The calculations show us that the folded wing configurations results in a 30% reduction in the coefficient of lift. To compensate for this reduction in horizontal flight lift, we need to either increase the angle of attack by 42% or increase the velocity 19%. Because the folded portion of the aircraft resides behind the center of gravity, a folded wing configuration results in reducing the negative pitching moment, which will also result in a reduced rotation speed at takeoff.

Initially, we didn’t take into account the fuselage, stabilators, and flaps lift capabilities, which all add to the total lifting force.

Unfolded wing



Folded wing



For an aircraft with non-folded wings and mass of 35,000 pounds and 8 degrees of angle of attack, the velocity to create the lifting force would be 186 knots without taking into account the fuselage, stabilators, and flaps. For an aircraft with folded wings and a mass of 35,000 pounds and 8 degrees of angle of attack, the estimated velocity for creating lift is 222 knots (i.e. 186 +19% = 221,34 knots). In our model, the velocity for a mass of 35,000 pounds and an angle of attack of 8 degrees is 205 knots due to the fuselage, stabilators, and flaps.

Y eso despreciando todas las superficies del avión que no forman parte de las alas y que realmente contribuyen a generar sustentación... ;)

Interesante, Mirmi, un buen resumen de las físicas que entran en juego en la sustentación.

Alerax's LSO AI Script.

Alerax's LSO AI Script.

Voy a ver si soy capaz en estos días de introducirlo en la plantilla de Cherry Point Senaki.

;) ;) ;)