Broncazonk
Materials
- Feb 16, 2015
- 26
I have a question pertaining to the late-war German high altitude fighter, the Ta-152H.
3-view here:
Here is a description of the washout built into the wings of the Ta-152H written by the National Air and Space Museum:
“Kurt Tank chose the same workhorse Jumo 213 powerplant used in the Fw 190D. For the Ta 152H, he selected an uprated version, the Jumo 213E, equipped with a 2-stage, 3-speed mechanical supercharger and MW 50 engine boost. The MW 50 system used methanol-water mixture to boost engine output from 1,312 kw (1,750 hp) to 1,537 kw (2,050 hp) for short periods. Because of aluminum shortages, Focke-Wulf made the wing spars from steel and built the rear fuselage and empennage. The wing contained two steel spars. The front spar extended slightly beyond the landing gear attachment points but the rear spar spanned the entire wing. The wing twisted 3° from the root to the flap-aileron junction. This 'washout' prevented the ailerons from stalling before the center section. This allowed the pilot to maintain roll control during a stall. Armament consisted of one 30mm MK 108 cannon firing 90 rounds through the propeller hub and one 20mm MG 151 cannon firing 150-175 rounds from each wing root.”
And here is another description:
The aircraft had an increased wingspan compared to the previous FW 190 design, as a further accommodation towards better high altitude performance. Due to the war's impact on aluminum availability, the wing was built around two steel spars, the front extending from just past the landing gear attachment points, and the rear spar spanning the entire wing. The wing itself was designed with 3° of washout, from the root to the flap-aileron junction, to prevent the ailerons from stalling before the center section of the wing. This design allowed the pilot to maintain roll control during a stall and extreme flight envelope maneuvers.
Are these descriptions correct? Isn't it more likely that 3° of washout (three degrees of downward twist) was built into the wings beginning at the flap-aileron junction that extended to the wing tips—not and not from the root to the flap-aileron junction?
Would the experts on the list please provide some clarity on this?
Thank you,
Bronc
3-view here:
Here is a description of the washout built into the wings of the Ta-152H written by the National Air and Space Museum:
“Kurt Tank chose the same workhorse Jumo 213 powerplant used in the Fw 190D. For the Ta 152H, he selected an uprated version, the Jumo 213E, equipped with a 2-stage, 3-speed mechanical supercharger and MW 50 engine boost. The MW 50 system used methanol-water mixture to boost engine output from 1,312 kw (1,750 hp) to 1,537 kw (2,050 hp) for short periods. Because of aluminum shortages, Focke-Wulf made the wing spars from steel and built the rear fuselage and empennage. The wing contained two steel spars. The front spar extended slightly beyond the landing gear attachment points but the rear spar spanned the entire wing. The wing twisted 3° from the root to the flap-aileron junction. This 'washout' prevented the ailerons from stalling before the center section. This allowed the pilot to maintain roll control during a stall. Armament consisted of one 30mm MK 108 cannon firing 90 rounds through the propeller hub and one 20mm MG 151 cannon firing 150-175 rounds from each wing root.”
And here is another description:
The aircraft had an increased wingspan compared to the previous FW 190 design, as a further accommodation towards better high altitude performance. Due to the war's impact on aluminum availability, the wing was built around two steel spars, the front extending from just past the landing gear attachment points, and the rear spar spanning the entire wing. The wing itself was designed with 3° of washout, from the root to the flap-aileron junction, to prevent the ailerons from stalling before the center section of the wing. This design allowed the pilot to maintain roll control during a stall and extreme flight envelope maneuvers.
Are these descriptions correct? Isn't it more likely that 3° of washout (three degrees of downward twist) was built into the wings beginning at the flap-aileron junction that extended to the wing tips—not and not from the root to the flap-aileron junction?
Would the experts on the list please provide some clarity on this?
Thank you,
Bronc
