The Arado Ar TEW 16/43-15 concept was born out of an in-house research project studying the possibilities of jet-powered fighter aircraft. The design appeared as early as March of 1943 and became yet another example of the forward-thinking in aircraft technology as sponsored by the many German engineering firms of World War 2. The intent of the Ar TEW 16/43-15 design was to mate a jet engine with rocket-fueled power to complement all-out performance above 32,800 feet. The design never materialized passed the "paper" stage however.
Design was wholly Arado and made use of some distinct features. A pair of low-mounted, swept-back wings were fitted at the center of the tubular fuselage with slab sides. The wings sported some dihedral and featured curved tips. The single pilot would have sat in a pressurized cockpit fitted just aft of a short nose-cone assembly. Vision to the front quadrant from under the single-piece glass canopy would have been excellent. The fuselage tapered off at the rear to which sat a high-mounted "Tee" style tail system sporting two vertical fins. The horizontal tail surfaces were swept while the vertical fins were nearly triangular in shape. Perhaps the most notable design element of the TEW 16/43-15 was its positioning of the jet engine, this mounted along the top of the fuselage spine with the intake wrapped around and aft of the canopy. The engine compartment ran some distance behind amidships and exhausted between the twin vertical tail fins. Fuel for the two powerplants was dispersed about the internal fuselage, in positions both central and aft.
The TEW 16/43-15 was to be another Arado design to make use of the patented DVL 1940 spherical tires. The aircraft would have used these special space-saving wheels across two main landing gear legs and a nose landing gear leg in a tricycle arrangement. The nose landing gear retracted under and forward of the cockpit floor while the main legs retracted into each wing root. Each of the landing gear systems retracted forwards into their respective bays.
Performance specifications were, of course, estimated. Power could possibly have been derived from a Heinkel-brand He S 011 series jet engine of 2,866lbs thrust. Rocket propulsion was to be a Walter HWK 509A series bi-fuel rocket thruster. The fuel for the thruster consisted of the volatile C-Stoff and T-Stoff fuel combination. A top speed of 572 miles per hour was envisioned as was an optimistic ceiling of 61,600 feet with a range of 745 miles.
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