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4 SMITHSONIAN MISCELLANEOUS COLLECTIONS VOL. 95 



was as follows : Dr. John C. Merriani, chairman ; Dr. C. G. Abbot ; 

 Dr. Walter S. Adams ; Dr. Wallace W. Atwood ; Col. Henry Breckin- 

 ridge ; Dr. John A. Fleming ; Col. Charles A. Lindbergh ; Dr. C. F. 

 Marvin ; and Dr. Robert A. Millikan. 



THE ESTABLISHMENT IN NEW MEXICO 



Although much of the eastern part of New Mexico appeared to be 

 suitable country for flights because of clear air, few storms, moderate 

 winds, and level terrain, it was decided to locate in Roswell, where 

 power and transportation facilities were available. 



A shop 30 by 55 feet was erected in September 1930 (pi. 3, figs, i, 

 2), and the 60-foot tower previously used in Auburn and Fort Devens 

 was erected about 15 miles away (pi. 4, fig. i ) . A second tower, 20 feet 

 high (pi. 4, fig. 2) , was built near the shop for static tests, that is, those 

 in which the rocket was prevented from rising by heavy weights, so 

 that the lift and general performance could be studied. These static 

 tests may be thought of as " idling " the rocket motor. A cement gas 

 deflector was constructed under each tower, as may be seen in plate 4, 

 figures I, 2, whereby the gases from the rocket were directed toward 

 the rear, thus avoiding a cloud of dust which might otherwise hide the 

 rocket during a test. 



STATIC TESTS OF 1930-32 



Although, as has been stated, combustion chambers had been con- 

 structed at Clark University which operated satisfactorily, it appeared 

 desirable to conduct a series of thorough tests in which the operating 

 conditions were varied, the lift being recorded as a function of the 

 time. Various modifications in the manner of feeding the liquids 

 under pressure to the combustion chamber were tested, as well as 

 variations in the proportions of the liquids, and in the size and shape 

 of the chambers. The chief conclusions reached were that satisfactory 

 operation of the combustion chambers could be obtained with con- 

 siderable variation of conditions, and that larger chambers afforded 

 better operation than those of smaller size. 



As will be seen from plate 4, figure 2, the supporting frame for the 

 rocket was held down by four steel barrels containing water. Either 

 two or four barrels could be filled, and in the latter case the total weight 

 was about 2,000 lbs. This weight was supported by a strong com- 

 pression spring, which made possible the recording of the lift on a 

 revolving drum (pi. 5, fig. i) driven by clockwork. 



