The Tachikawa R-52 was completed in September 1952 and was the first aircraft built entirely from Japanese materials and powered by a Japanese engine (a 130 hp Shinphu 2 radial) to be completed after World War 2.
Derived from the pre-war R-38, the R-52 tandem two-seat parasol-wing trainer was the first product of the Shin Tachikawa Kasushiki Kaisha, and the prototype was presented by the Yomiuri Press for student instruction. The R-52 is of mixed construction with fabric covering.
Engine: 130 hp Shinphu 2 Wingspan: 35 ft Length: 24 ft 3 in Height: 9 ft 2 in Empty weight: 1500 lb Loaded weight: 2105 lb Max speed: 124 mph Cruise: 93 mph ROC: 722 fpm Range: 310 mi
On 8 September 1943, instructions were issued to redesign the Nakajima Ki-84 Hayate all-metal single-seat fighter for wooden construction because of the increasingly critical light alloy supply situation. The task of redesigning the airframe was assigned to the Tachikawa Hikoki which was to collaborate with the Army Aerotechnical Research Institute at Tachikawa.
Assigned the designation Ki-106, the wooden fighter was intended to utilise a high proportion of semi-skilled labour in its construction and to be broken down into components to be built by small wood-working shops grouped around designated assembly points.
Prototype construction was sub-contracted to Ohjo Koku, but the first of three prototypes was not flown until July 1945. The external characteristics of the Ki-84 were faithfully retained by the Ki-106, apart from some minor revision of the vertical tail, the first prototype being powered by the 2,000 hp Nakajima Ha-45-21 engine and carrying an armament of four 20-mm cannon. Appreciably heavier than the standard Ki-84, the Ki-106 was subjected to various weight saving measures, one of these being a reduction in the armament to two 20-mm cannon, and the second prototype flew with this armament during the last week of the war.
Engine: 2,000 hp Nakajima Ha-45-21 Length 32 ft 7 in (9.92 m) Wing span: 36.8 ft (11.21 m) Height: 3.59 m / 11 ft 9 in Wing area: 21 sq.m / 226.04 sq ft Max take-off weight: 3900 kg / 8598 lb Empty weight: 2948 kg / 6499 lb Max. speed: 620 km/h / 385 mph at 21,325ft (6 500m) Range (+1.5 hr res): 800 km / 497 miles Time to 16,405ft (5 000m): 7.85min
Defeat in the Battle of Midway essentially left Japan without means to project their aerial power over distant territories and started the three-year long retreat towards their home islands. Since 1942, US strategic bombers began regularly raiding imperial territories, and it culminated with the raid on Tokyo on the night of 9-10 March 1945 that included 334 B-29 heavy bombers and resulted in the almost total obliteration of mostly wooden civilian structures over 40 km2 of the Japanese capital, and the death of over 100,000 people.
The Japanese army command had considered such possibilities beforehand, and the means to deter long-range bombing raids were being developed from 1942. Koku Hombu, the aviation HQ of the Imperial Army, placed an order with the Tachikawa Hikoki HK company for a high altitude interceptor that would be able to destroy enemy bombers.
The initial requirements were the fighter was supposed to have a range of 3,000 km, up to 800 km/h speed, and a pressurized cockpit. Tachikawa started the Ki-94 project that was later split into two completely different designs – the Ki-94-I and Ki-94-II.
The Ki-94-I was a large twin-boom monoplane with two tandem 18-cylinder Mitsubishi Ha-211 Ru piston engines located in the front and rear sections of the fuselage. The rear-pushing propeller was located between the tail booms. The designers expected that this scheme would provide speeds of up to 780 km/h at a 10-kilometer altitude. The Ki-94 was supposed to carry two 37-mm Ho-204 and two 30-mm Ho-155 cannons, located in the wings.
By the end of 1943, Tachikawa had a wooden model built but the Koku Hombu technical department considered it to be exceedingly difficult to produce, and the high expectations of the aircraft’s characteristics were deemed overly enthusiastic. As a result, the design was discarded and the role of the fighter-interceptor was handed over to Nakajima Ki-87, while Tachikawa focused on the sister Ki-94-II design.
Ki-94 Engine: 1 x Nakajima Ha-44, 1835kW Max take-off weight: 6450 kg / 14220 lb Empty weight: 4690 kg / 10340 lb Wingspan: 14 m / 45 ft 11 in Length: 12 m / 39 ft 4 in Height: 4.65 m / 15 ft 3 in Wing area: 28 sq.m / 301.39 sq ft Max. speed: 712 km/h / 442 mph Cruise speed: 440 km/h / 273 mph Ceiling: 14680 m / 48150 ft Range: 2100 km / 1305 miles Crew: 1 Armament: 2 x 30mm cannons, 2 x 20mm cannons, 500kg of bombs
In 1937 army air headquarters authorized the construction of two prototypes of a two seat army cooperation aircraft developed by Ryokichi Endo’s design team from Tachikawa Hikoki K K (Tachikawa Aircraft Company).
The first of two prototypes was flown on 20 April 1938 flew from Tachikawa airfield, the Tachikawa Ki-36 was a cantilever low-wing monoplane of all-metal basic structure, covered by a mix of light alloy and fabric. Landing gear was of fixed tailwheel type, the main units enclosed in speed fairings, and power was provided by a 336kW (450-hp) Hitachi Ha-13 radial engine. The two-man crew was enclosed by a long ‘greenhouse’ canopy and both men had good fields of view, that of the observer being improved by clear-view panels in the floor.
The aircraft was very sensitive to the controls and fully satisfied the army, although later production aircraft incorporated a 2′ wing washout to counter a tendency to stall which had become apparent during very tight manoeuvring.
Ki-36
The type was ordered into production in November 1938 as the Army Type 98 Direct Co- Operation Plane. Generally similar to the prototypes, the type was armed with two 7.7mm (0.303-in) Type 89 machine guns, one in the engine cowling synchronized to fire through the propeller, and the other on a flexible mounting operated by the observer, and introduced the more powerful Hitachi Ha-13a engine. Up to 150 kg (330 lb) of bombs were carried on underwing racks. In 1939 Kawasaki joined the production programme.
Ki-36
When construction ended in January 1944, a total of 1,334 had been built by Tachikawa (862) and Kawasaki (472).
The handling characteristics and reliability of the Ki-36 made the army realize that it was ideal for use as an advanced trainer, resulting in development of the Ki-55, intended specifically for this role and having armament reduced to a single forward-firing machine-gun. Following the testing of a prototype in September 1939, the army ordered this aircraft as the Army Type 99 Advanced Trainer; when production was terminated in December 1943 a total of 1,389 had been built by Tachikawa (1,078) and Kawasaki (311).
Tachikawa Ki-55
Both versions were allocated the Allied codename ‘Ida’, and the Ki-36 was first deployed with considerable success in China. However, when con¬fronted by Allied fighters at the begin¬ning of the Pacific War it was found to be too vulnerable, being redeployed in China where it was less likely to be confronted by such aircraft.
Ki 36s were employed against the Allies from December 1941, but were withdrawn from 1943 onwards, in which role, with wheel spats removed and necessary equipment modifications, they were very successful, so much so that production as the Army Type 99 Advanced Trainer or Ki 55 was initiated by both Tachikawa and Kawasaki. . In the closing months of the war, many examples of both versions were pressed into service as suicide bombers carrying a 250 kg (550 1b) or 500 kg (1100 lb) bomb. Allied name for all models was Ida.
Twenty-four Ki-55 served with the RTAF throughout the period of Japanese ascendancy and the immediate post war period. One survives.
Ki-36 Engine: one 380-kW (510-hp) Hitachi Ha- l3a radial Maximum speed 348 km/h (216 mph) at 1800 m(5905 ft) Cruising speed 235 km/h (146 mph) Service ceiling: 8l50 m (26740 ft) Range 1235 km (767 miles) Empty weight 1247 kg (2749 lb) Maximum take-off 1660 kg (3,660 lb) Wing span 11.80 m (38 ft 8.6 in) Length 8.00 m (25 ft 3 in) Height 3.64 m (11 ft 11.3 in) Wing area 20.00 sq.m (215.29 sq.ft) Armament: two 7.7-mm (0.303-in) machine-guns Bombload: 150 kg (331 lb) Crew: 2
Ki-55 Engine: 1 x Hitachi Ha-13a, 380kW Span: 11.8 m (38 ft 9 in) Length: 8 m (26 ft 3 in) Height 3.64 m (11 ft 11.3 in) Wing area 20.00 sq.m (215.29 sq.ft) Empty weight: 1292 kg / 2848 lb Gross weight: 1721 kg (3794 lb) Maximum speed: 348 km/h (216 mph). Cruising speed 235 km/h (146 mph) Ceiling: 8200 m / 26900 ft Range: 1060 km / 659 miles Crew: 2
The third prototype of the Ki 9, intended as a primary trainer, was flown in early 1935 but exhibited poor handling qualities because of its smaller, lighter engine and the consequent displacement of the centre of gravity. The Ki 9 was therefore abandoned as a primary trainer, and the army air force asked Tachikawa to produce, later that year, two prototypes of a new primary trainer biplane, the Ki 17.
The Tachikawa Ki-17 biplane had a slimmer fuselage, more square-cut equal-span wings and a redesigned tailplane, engine uncowled and a simplified landing gear.
The first of two prototypes was flown in July 1935 powered by a 150 hp Hitachi Ha 12 seven¬ cylinder radial engine driving a two blade propeller. Trials were successful and the only major change made to subsequent production aircraft was the deletion of the upperwing ailerons to eliminate oversensitive control inputs.
Between 1936 and 1943 Tachikawa completed 658 series Ki-17s and the type was used at four major flying schools and the Army Air Academy. The Ki-17 bore the official designation Army Type 95 III Primary Trainer, Allied codename ‘Cedar’. Some Ki 17s were later transferred to liaison or communications duties.
Ki-17 Engine: 1 x Hitachi Ha-12, 112kW Max take-off weight: 914 kg / 2015 lb Loaded weight: 639 kg / 1409 lb Wingspan: 9.82 m / 32 ft 3 in Length: 7.85 m / 26 ft 9 in Height: 2.95 m / 10 ft 8 in Wing area: 26.2 sq.m / 282.01 sq ft Max. speed: 170 km/h / 106 mph Ceiling: 5300 m / 17400 ft Crew: 2
The Ki 9 had been designed in 1934 by Ryokichi Endo to satisfy a Japanese army air force requirement for a primary and intermediate trainer, capable in the latter case of 220 km/h (137 mph) and an endurance of 3½ hours.
First flown on January 7, 1935, the first and second prototypes were each powered by a 350 hp / 261kW Hitachi Ha 13a nine cylinder radial engine; the third aircraft, prototype for the primary trainer version, had a lower powered Nakajima NZ seven cylinder radial engine of 150 hp / 112kW.
Tests indicated centre of gravity problems for the proposed primary trainer and the Ki-9 was developed in the higher-powered intermediate training role only. As Tachikawa had suggested, the army air force found that one aircraft could not successfully carry out both duties, and accordingly the Ki 9 was ordered into production in 1935 only as the Type 95 1 Medium Grade (intermediate) Trainer.
Production deliveries began in 1935. Designated the Army Type 95-1 Medium Grade Trainer Model A and later given the Allied codename ‘Spruce’, the Tachikawa biplane had complex split-axle landing gear with fairings over the top of the wheels. In 1939 this was modified and simplified, the fuselage slightly shortened and all-up weight reduced. The resulting Army Type 95-1 Model B or Ki-9 Kai had improved manoeuvrability and flight characteristics. Both versions were used widely for blind-flying training with a folding hood over the rear cockpit, and at least one was modified with a glazed canopy over the rear cockpit for use as a staff officer transport.
Production by Tachikawa ended in 1942 after completing 2395 (in addition to the three prototypes), but in 1944 45 a further 220 were manufactured by the Tokyo Koku K.K.
It served with the army air force throughout the remainder of the 1930s and until the end of the Second World War. Some Ki 9s were used for reconnaissance or communications duties, and the type also served with the air forces of Cochin China, Manchuria and Thailand during the Pacific war. After the war, captured examples were employed for a time by the insurrectionist Indonesian forces.
The Ki-9 received the allied code name ‘Spruce’.
Ki-9 Model A Engine: 1 x Hitachi Ha-13a, 261kW Max take-off weight: 1580 kg / 3483 lb Loaded weight: 1120 kg / 2469 lb Wingspan: 10.32 m / 33 ft 10 in Length: 7.52 m / 24 ft 8 in Height: 3.1 m / 10 ft 2 in Max. speed: 240 km/h / 149 mph Ceiling: 5800 m / 19050 ft Crew: 2
In 1930, at Holland, Michigan, Szekely Corp made small single-seat low-wing cantilever monoplane called Flying Dutchman.
Priced at $2,200, three were built, registered NX4448, N9455, and N910.
An open cockpit, low wing monoplane powered by a 150hp Hisso A, one was built for W C Williams of San Antonio TX (N910). It crashed in October 1927 as a reported “total washout.”
The Székely IV Parasol of 1913 was designed and built by the Hungarian Mihály Székely (Hungary then part of the K.u.k – Austro-Hungary). A typical parasol wing machine with the pilot and passenger sitting in a nacelle beneath the wing-tractor configuration, with the engine high before the wing and petrol tanks above.
1913 Szekely IV 2-seater “parasol” monoplane received 2nd altitude prize achieving 610 meters.
Evolved from the Vidervol-Szaraz VS-1, the Szaraz SD-1A Daphne is a homebuilt aircraft that was designed by Art Szaraz and Bernie Darmstadt for efficiency competitions.
The Daphne is a two place side-by-side configuration strut-braced high-wing, conventional landing gear equipped homebuilt. The fuselage uses welded steel tubing with aircraft fabric covering. The wings are wood, with one-piece plywood ribs. Both ailerons and flaperons have been installed on the design.
The first three examples were built on the same jigs at Art Szaraz’s workshop. At least fifteen were built. At least 26 were under construction by Jan 1970.
Known examples: N960Z (c/n 1) built by Arpad Szaraz, ff: 1963 N962Z built by Nick Stanich, ff: 2/28/65 N961Z built by B D Darmstadt, ff: 6/18/65
SD-1A Daphne Engine: 1 × Continental C-85-12F, 85 hp (63 kW) Propeller: 2-blade Wingspan: 26 ft (7.9 m) Wing area: 130 sq ft (12 sq.m) Airfoil: NACA 4412 Length: 19 ft 7 in (5.97 m) Empty weight: 820 lb (372 kg) Gross weight: 1,300 lb (590 kg) Maximum speed: 130 kn; 241 km/h (150 mph) Cruise speed: 104 kn; 193 km/h (120 mph) Stall speed: 35 kn; 64 km/h (40 mph) Never exceed speed: 148 kn; 274 km/h (170 mph) Service ceiling: 14,500 ft (4,400 m) Rate of climb: 1,000 ft/min (5.1 m/s) Capacity: 2
All Aero 