Voughtworks: F4U Low Drag Wing Study Part 3

Rework and new fabrication to support the new wing design included:

Lateral control would be through the use of "retractable ailerons" (circular arc spoilers) along with short span conventional ailerons.
Landing flaps will be slotted type extending from the fuselage to approximately 80% of the span of the wing. Whereas the fixed hinge flaps on the F4U-4/-5 only covered 55% of the wing span.
Armament would be 4 20mm guns with 200 rounds of ammunition. Also eight Mark 9 rocket pylons and two center section bomb or fuel carrying pylons. A centerline pylon completes the external stores provisions.
Wing folding would be improved to allow operation in winds up to 55 knots.
Main landing gear would be similar geometry but extensive redesign to fit the low drag wing airfoil. The main tires would change to 30 x 7.7 10-ply high pressure tires instead of the 32 x 8 tires of the F4U-4.
Due to angle changes the wing to fuselage joint would be reworked.
Some strengthening to the aft section and stabilizers would be necessary.

Expected Performance Improvement

The maximum speed at combat power in clean fighter configuration compared to the F4U-5 would be 16 mph at the combat power critical altitude.
The maximum speed difference at sea level would only be 7 mph.
Stalling speed reduction of 1.3 mph than a standard F4U-5 with the flaps down.
Stalling speed increase of 3 to 4 mph with the flaps up over a standard F4U-5.
The angle of bank in the first second and rate of roll is estimated to be as much as a 10% increase at 300 mph over the standard F4U-5.

Four things led to the increased speed estimates:

Higher critical mach number due to the change in airfoil from NACA 230 series to a NACA 64 series.
Improvement in critical mach number for the wing inlet duct
Reduction in drag and surface roughness due to the use of Metalite wherever practical
Elimination of wing flap external hinges.

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