The Wright-Martin Type V, was a reconnaissance type with tractor propeller, and the observer’s cockpit being placed well forward of the entering wedge of the lower wings.
Specifications from “Practical Aviation,” by Charles Hayward, 1919
Planes
The span of the machine is 39 feet 8 ½ inches, both planes being the same size. The wings are set at a dihedral angle 1 degree 45 minutes, have no sweep back, and are staggered inches. The main spars and the spars of the leading edges are of ection spruce, the trailing edges are of ash, and the ribs are lilt up of spruce battens and poplar webs. The upper plane consists of three sections, that is, engine, or center, panel and the two outboard panels, while the lower plane is in two sections, fitting into either side of the
Fuselage
Exclusive of the ailerons, the area of the upper planes is 223.2 square feet and that of the lower planes 206.8 square feet, the total supporting surface being 430 square feet. The loading is 5.86 pounds per square foot and 1.86 pounds per b.h.p. The chord of the wings is 5 feet 9 ½ inches, the gap is 5 feet 7 inches, and the upper wing is mounted 1 foot forward of the lower.
Tail Unit
The horizontal stabilizer is double cambered and built on an I-beam spruce spar placed 14 inches to the rear of ie leading edge, external bracing being eliminated by the use of lis spar, which also provides the necessary depth for the double-cambered profile. Streamlined steel tubing is employed for the outside stays. The elevator and rudder surfaces are built with light spruce spar placed 10 inches forward of the trailing edge aid in equalizing the load on the ribs, all ribs and spars attached to tubular frame members by sheet-steel socket brazed in place. The area of the horizontal stabilizer is X feet, that of the vertical fin is 17.37 square feet, and the span of the stabilizer is 11 feet 11 inches.
Fuselage
With the exception of the motor mounting, which is of steel, the fuselage frame consists of ash and spruce longerons and cross members, which are braced with vanadium steel wire. From the trailing edge of the planes, the body tapers back sharply, a vertical knife edge serving as a support for the fin and rudder, which are braced by means of nickel-steel tubing held in clevis pins instead of the usual bracing wires. Aluminum is employed for covering the motor and body as far back as the pilot’s seat, the remainder of the body covering being the same as the covering of the wings, that is, linen fabric treated with “dope” and water- proof varnish. The length over all is 27 feet 2 inches.
Controls
Transverse control is affected by means of four ailerons having a total area of 64.6 square feet and operated by double cables, changes in the direction of the latter being provided for by substantial chains passing over stamped steel pulleys. To eliminate lost motion as well as the usual crossing and slacking of these cables, an inclosed rocking shaft forms part of the elevator control mechanism and is placed just back of the pilot’s seat, while pressed steel arms are fitted to all the rear surfaces. The machine may be controlled from either the pilot’s or the observer’s cockpit, the Deperdussin type of control being employed, control cables are removable by withdrawing steel locking pins, and all adjustments may be made from the cockpit.
Power Plant
The motor is a Simplex Model A Hispano-Suiza, developing 150 h.p. at 1450 r.p.m. and directly driving a propeller, having a diameter of 8 feet 4 inches and a pitch of X feet 7 ½ inches, in a counter-clockwise direction. It is water-cooled and, complete with radiator, cooling water, propeller, starting handle, and other accessories, it weighs 595 pounds. The crankshaft passes through the lower part of the radiator which forms the nose of the body. The main fuel tanks are disposed longitudinally just aft of the pilot’s seat and are secured to padded cradles, the gasoline being supplied from these tanks by pressure, a gravity service tank at the rear end of the cowl.
Landing Gear
The landing gear consists of a nickel-steel axle carrying a pair of 26- by 4-inch wheels with pneumatic tires and having a tread of 5 feet 4 inches, the axle being attached to the fuselage by means of ash V struts of streamline section combined with a streamlined system of twin parallel spreader tubes. The struts are attached to the body with steel clip and pin fittings. At the rear there is a conventional tail skid, the weight of the landing gear exclusive of the tail skid being 86 pounds.
Weight
The weight of the complete machine without fuel or oil but including the instruments is 1725 pounds, while its useful load capacity is 445 pounds, of which 330 pounds are allowed for the pilot and observer. A supply of fuel and oil for a six hours’ flight at full speed weighs 400 pounds.