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Aviation History
1927
1927 - 0829.PDF
October 27, 1927 Supplement to FLIGHT ENGINEERINGSECTION Edited by C. M. POULSEN October 27, 1927 CONTENTS A Simple The..re,ical M,thod .„ Analv.i,,, and Pr,,,» t, I'crformaiic.-. Ii> Ivan H. UriS(i> Ita- Reduction HI Flight Test Data to Standard Atm Conditions. Hy Lieiit.-C'ul. J. I). Blyth. C.U.E., M.I.At.K. Tut iinical Lit«*ratur»' ... ... . . Airplane sphere t* K4 EDITORIAL VIEWS With this issue of THE AIRCRAFT KM.IXEKR the article on "A Simple Theoretical Method of Analysing and Predicting Airplane Performance." by Mr. Jvan H. Driggs. comes to a close. It i.s regretted that it has been necessarv to divide this article into three instalments, since this causes a certain amount of inconvenience for reference purjx>ses. However, it is thought that most readers collect their numbers of TIIK AIRCRAFT KXMXKER as a separate volume, indepen- dent of KuiaiT. in which ease it is only necessary to look through three mini tiers. As regards the article itself, it is realised that it lias been difficult for readers to express an opinion on the Driggs method until the entire article was published. Now that this is the case, it is hofH'd that Uritish designers and others interested in the subject of performance will peruse the article carefully and. by giving us their views, give readers of TKK AIRCRAFT EMUXKKH the benefit of their intimate knowlegc of the subject. Apart from the question of whether or not the Drigus method is rational and logical, and to be reganled as sufficientiv accurate for general use. we think it will l>e airreed that the information concerning American aircraft which is given in the course of the checking of the I)rigL's method is of very considerable interest, and provides a number of jK>rforinance figures which are very welcome at a time when in this eountrv a jrreat deal of seerecv surrounds the iK*rforrnance of British aircraft. Lieut.-Col. Hlvth contributes this week an article on " The i, ........... ... iKeduction of Flight Test Data to Standard Atmosphere Conditions." The metho<l enploved is explained in detail. and also the basis upon which it works, while the chart enables one to reduce easily, rapidly and without the use of tables or calculations of any sort, observed data to conditions of standard atmosphere. The standard atmosphere used by C-ol. Blyth is that employed in America, which is based upon relative density and pressure l>eing taken as unitv at a height of 0 ft., at which altitude the temjierature is 15 C. and the pressure 29-92 in. of mercurv. Mr. .J. D. North has. we regret to say. l>een indisposed recently, and has not. therefore, been able to contribute his final article on " Aircraft Performance." A SIMPLE THEORETICAL METHOD OF ANALYSING AND PREDICTING AIRPLANE PERFORMANCE. Bv IVAX H. DSIGGS. Concluded from• />. 62. j Lxmnplc II.—A — CO — 6 Airplane. Case I is used. Data : — Total weight 4.5B3 lbs. Wing area (R.A.F. 15) ... ... ... 500 sq. feet. Span both wings ... ... ... 48 feet. (-Jap ... ... ... ... ... (> feet. Power ... ... ... ... ... 420 at 1.700. Profile drag of airfoil ... ... ... 0-000025. A, of structure (from detail analysis! ... 14-1 sq. ft. ^— = Tg = C'' 125 K'' =" 1-1175 from Fig. 2. , 420 */• = 45(i3 ~ (''^" , . ,„ F, = ~~- z = 0-529 "^' II to x 48)- 0-000025 \ 500 • 1 * • = \ 1*" 1 — cTW327 45fi;? iruti it t t ,j(.^ — \ max — 1—I' ill.p.it. c __ j _ 0 425 2- .35 11-94 a 54-5 — 0-745 Jv,' — l suut » (),>j. — > max. E" * max. Jv,, » max. — T-. — y' WlWOi. > max. £et y _. (jo m.p.h, 0-00392 0-00392 Let V = 100 ni.p.h. 0-092 x 0-745 X 100 0-529 1'lotting these two points as ordinates on this respective values of V as abscissa1 and connecting with a straight line to intersect the curve of 0-00000872 V4 gives V n,ax. as 123 m.p.h. Fig. .">. 750a D 2
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