Caspar CLE II
Type
1 + 2-seat passenger plane
Engine
1 Siemens Sh 5
Dimensions
Length 6.72 m, height 2.20 m, span 12.00 m, wing area 19.00 m2
Weights
Empty 450 kg, fuel 83 kg, oil 8 kg, crew 80 kg, payload 209 kg, flying weight 830 kg
Performance
Max. speed at sea level 160 km/h, cruising speed at sea level 145 km/h, climb 2.10 m7sec., service ceiling 3000 m, range 800 km, max. endurance 6.0 h,
landing speed 65 km/h
Type
Werk.Nr
Registration
History
   
D-294
Built in 1923.  Took part in the International Air Exhibition in Gothenburg (Sweden) in July 1923. Static and
also performed some flights.
The second machine exhibited by the Caspar Werke is a commercial monoplane of small capacity, the cabin being arranged to carry but two people, seated vis-A-vis one another in a very narrow cabin. This machine is known as the type C.L.E. II, and is fitted with a Siemens radial seven-cylinder engine of 80 h.p. Thus the power expenditure per paying passenger is but 40 h.p., which should be a good commercial proposition. If the machine is piloted by its owner, and used for touring with a couple of friends, so that it becomes legitimate to count in the pilot in the useful load, the economy becomes even greater, i.e., 26.7 h.p. per occupant. Thus, for use on feeder lines joining up with main air routes, on which there is insufficient traffic to make a larger machine pay, the Caspar C.L.E. II should be a very useful and economical little machine.
As cheapness of construction was one of the desiderata, and clean aerodynamic design another, Ingenieur von Loessl chose the cantilever monoplane type, but incorporated a fuselage composed entirely of straight lines and flat surfaces, which could be easily and cheaply covered with ply-wood panels. It is, of course, well known that these panels can be bent around a cylinder but not around a barrel, i.e., not around a double curvature. Nevertheless, if the panels can be used without bending, their application to the internal framework becomes so much easier. In the C.L.E. II the fuselage is of rectangular section, with an inverted V roof and a V bottom in the forward part. Aft of the undercarriage the bottom is flat.
The undercarriage is of the form first made popular by Dornier, i.e., the axle is enclosed in a casing of thick aerofoil section, and the rubber shock absorbers are attached to the ends of this, cantilever fashion, giving a wide wheel track.
The wing is in three sections, a large centre portion and two relatively small end pieces, attached to the main wing by special quick-release fittings. In the centre, above the " roof tree " of the fuselage, the wing is attached by simple hooks, and is braced farther out by struts sloping out at a fairly flat angle.
Behind the trailing edge of the wing is the pilot's cockpit, and immediately under the wing the tiny cabin with accommodation for two passengers. The space is rather cramped, especially as regards leg-room, and also to a certain extent as regards head-room. One passenger faces aft and the other forward, and the cabin is of only sufficient width to give elbow space, and not much of that if the passengers be Germans of average, bulk. As in the case of the biplane, the monoplane is covered entirely with three-ply, and it was noticed that in the bottom of the fuselage there were no diagonal members to stiffen the ply, which was not more than 1 or 1,5 mm. thick.
The main characteristics of the Caspar C.L.E. II are as follows : Weight, empty, 450 kg. (1,000 lbs.) ; useful load, 360 kg. (790 lbs.) ; total loaded weight, 810 kg. (1,790 lbs.). The maximum speed is 160 km. (100 m.p.h.), and the landing speed 80 km. (50 m.p.h.). The range is approximately800 km. (500 miles).

1 Shows the arrangement of the rubber shock absorbers on the end of the wing-section fairing over the axle. An aileron crank lever is shown in 2, while 3 is a perspective view of the machine as she was exhibited-on a steep left-hand banked turn.