A 300 kgf engine was installed in a Junkers 'Junior' aircraft fuselage at Kummersdorf. This was the first rocket engine installation in an aircraft. But the problem to be solved was how to ensure continuous operation of the engine during aircraft manoeuvres. The rocket team finally built a big carousel, capable of testing the engine installation at up to 5 G's.

The missile test range is to be a combined Army / Air Force test ground. Von Braun had found the location in December 1935, after his first choice - Briz on the island of Ruegen - was taken over by the Deutsch Arbeitsfront as a 'Kraft durch Freude' recreation camp. During his Christmas holiday, Von Braun toured the cost, and found Peenemuende. It seemed perfect - 400 km of ocean to the east for use as a missile shooting range, room along the path on the coast for tracking radars.

These would run through August 9, 1938 and included 30 flight tests of 10-in.-diameter motors, in nitrogen-pressured rockets. The series was divided into three sections: A, B, and C. Section A covered development of a nitrogen-pressured flight rocket using 10 in, motors based on the K series and ran from May 11 to November 7, 1936 (L1-L7). Length of the L Series Section A rockets varied from 10 ft 11 in, to 13 ft 6 1/2 in.; diameter 18 in.; empty weight 120 to 202 lb; loaded weight 295 to 360 lb; weight oxygen about 78 lb; weight gasoline 84 lb; weight nitrogen, 4 lb.

The tests showed that the A3 configuration was unstable in flight and that it was going to take a lot of trial and error to identify the correct aerodynamic shape for the supersonic missile. Therefore the decision was taken to go slow on development of the A4 until tests with the A3 were complete. The 25 tonne thrust engine would also have to be built and proven in ground tests to determine its actual characteristics before a lot of effort was put into final design and construction of the rest of the rocket. So a series of test launches of the A3 to test the A4 control and guidance systems were undertaken, while Test Stand I at Peenemuende was prepared for tests of the 25 tonne engine.

First objective is development of the A4 strategic ballistic missile, later dubbed the V-2. The missile is to deliver a one tonne high explosive payload to double the range of the Paris Gun of World War I (250 km - the Paris Gun could deliver a ten kg, 21 cm diameter shell to 125 km range). To provide a reserve, the missile was designed for a 1500 m/s burnout velocity, which resulted in a 275 km range. Accuracy was to be 2 to 3 per mille, versus typical artillery shell accuracy of 4 to 5 per mille. These requirements indicated a 25 tonne thrust engine, powering a 12 tonne missile, with a 2100 m/s exhaust velocity, burning 8 tonnes of propellant in 65 seconds. The requirement to transport the missile by rail limited the diameter to 1.6 m, which in turn led to a 14 m length. Span with the detachable tail fins was 3.5 m.

Several major issues had to be solved during development. The first was what wing and body shapes would be stable at supersonic velocities. Another was building adequate ground facilities for the intensive tests needed to develop the 25 tonne thrust motor. For this purpose a static test facility was built at Peenemuende capable of handling 100 tonne thrust motors, seen as the next step after the A4. Another major problem was developing high-capacity pumps to deliver the liquid oxygen at a temperature of -185 deg C.

Tsien Hsue-shen, at the urging of Theodore von Karman, begins graduate studies at the California Institute of Technology. He will continue there for nearly twenty years, first as a student, finally as the Goddard Professor, becoming one of the leading rocket scientists in the United States.

Following problems with testing of the A3 (a subscale version of the planned V-2) by Dr Hermann, Von Braun proposes to the Germany army that a supersonic wind tunnel be constructed at a cost he estimates as 300,000 Marks. Other parts of the Army are not supportive of the facility, but it is finally built, costing millions more than Von Braun estimated.

Rocket equipped with a cluster of four combustion chambers, each 5.75 in. in diameter; length 13 ft 6.5 in.; altitude about 200 ft; fell near tower. The L series included four proving-stand tests and three flight test attempts, of which all were successful. Average interval between tests 25 days

These were check tests of 5 3/4-in.-diameter chambers with fuels of various volatilities; development of tilting cap parachute release; tests of various forms of exposed movable air vanes; test of retractable air vanes and parachute with heavy shroud lines. The series ran from November 24, 1930-May 19, 1937 (L8-L15).