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Static WingRib Tests

Static WingRib Tests November, 1934 AIRCRAFT ENGINEERING. 301 A Method of Calculating Approximate Values for the Loads to be Applied B y A . W . Clegg, B.Sc. A.F.R.Ae.S. H E strength of main plane ribs for use tion of load due to transference of part of the tribution curves of various British and German on all British aircraft is determined by load through the covering to the leading and aerofoils for eight centres of pressure ranging static tests of single representative ribs trailing edges. It is assumed for this purpose from 0-238 to 0-663 of the chord, the distances under conditions of loading determined from tha t the rib spacing is 0-133 of the chord, along the chord chosen for the loading positions th e characteristics of the aerofoil. with no nose ribs present. The actual method being those given in Table 1. of calculation is described in Aeronautical The Customary Method Research Committee Reports and Memoranda Approximate Curves I n the method of test usually adopted, 443, the end loads in the rib due to tension On plotting the percentage load at any one the rib is supported at the spars and load is of the covering being neglected. position against the centre of pressure, it ap­ applied through strings or tapes at a number peared that, although the location of the points of positions along the chord. These points A Laborious Process was somewhat irregular, it was possible, for are grouped by means of a scries of links, The work involved in calculating the loads each position, to draw a curve which repre­ so tha t the application of a single load applies for any given load distribution is considerable, sented the variation of the proportional loads the correct proportion of load at each string. even when a curve for the aerofoil giving the without undue error in the individual cases. The link system generally adopted is arranged required centre of pressure is available . Usually, A further examination of the sixteen curves t o apply sixteen loads along the chord. however, it is necessary t o interpolate between showed that it was possible to satisfy the Supplementary links may be used, sub­ several curves in order to obtain one giving condition that, for centres of pressure lying dividing the sixteen loads to any number the required centre of pressure, and this greatly between 0-2 and 0-7 of the chord, the sum of up to thirty-two; where, for example, the size increases the time required for the calculation. th e loads corresponding to any given centre of the rib makes it desirable to have loads at A method of obtaining approximate values of pressure was one hundred. These sixteen closer intervals than would be given by the for the loads t o be applied without calculating curves are given in Figs. ], 2 and 3. sixteen positions. from pressure curves would therefore decrease An examination of the pressure distribution In calculating the percentage of the nett both the cost and the time required for testing curves for various normal aerofoils shows that lift t o be applied a t each of the sixteen positions, an y particular rib. for the same centres of pressure their general allowance is made for the probable redistribu­ shapes are similar (although the centre of The loads to be applied, as previously described, were calculated from pressure dis­ pressure will not necessarily be the same for * R.A.F. Crown Copyright reserved. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Static WingRib Tests

Clegg, A.W.
Aircraft Engineering and Aerospace Technology , Volume 6 (11): 1 – Nov 1, 1934
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029871
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Abstract

November, 1934 AIRCRAFT ENGINEERING. 301 A Method of Calculating Approximate Values for the Loads to be Applied B y A . W . Clegg, B.Sc. A.F.R.Ae.S. H E strength of main plane ribs for use tion of load due to transference of part of the tribution curves of various British and German on all British aircraft is determined by load through the covering to the leading and aerofoils for eight centres of pressure ranging static tests of single representative ribs trailing edges. It is assumed for this purpose from 0-238 to 0-663 of the chord, the distances under conditions of loading determined from tha t the rib spacing is 0-133 of the chord, along the chord chosen for the loading positions th e characteristics of the aerofoil. with no nose ribs present. The actual method being those given in Table 1. of calculation is described in Aeronautical The Customary Method Research Committee Reports and Memoranda Approximate Curves I n the method of test usually adopted, 443, the end loads in the rib due to tension On plotting the percentage load at any one the rib is supported at the spars and load is of the covering being neglected. position against the centre of pressure, it ap­ applied through strings or tapes at a number peared that, although the location of the points of positions along the chord. These points A Laborious Process was somewhat irregular, it was possible, for are grouped by means of a scries of links, The work involved in calculating the loads each position, to draw a curve which repre­ so tha t the application of a single load applies for any given load distribution is considerable, sented the variation of the proportional loads the correct proportion of load at each string. even when a curve for the aerofoil giving the without undue error in the individual cases. The link system generally adopted is arranged required centre of pressure is available . Usually, A further examination of the sixteen curves t o apply sixteen loads along the chord. however, it is necessary t o interpolate between showed that it was possible to satisfy the Supplementary links may be used, sub­ several curves in order to obtain one giving condition that, for centres of pressure lying dividing the sixteen loads to any number the required centre of pressure, and this greatly between 0-2 and 0-7 of the chord, the sum of up to thirty-two; where, for example, the size increases the time required for the calculation. th e loads corresponding to any given centre of the rib makes it desirable to have loads at A method of obtaining approximate values of pressure was one hundred. These sixteen closer intervals than would be given by the for the loads t o be applied without calculating curves are given in Figs. ], 2 and 3. sixteen positions. from pressure curves would therefore decrease An examination of the pressure distribution In calculating the percentage of the nett both the cost and the time required for testing curves for various normal aerofoils shows that lift t o be applied a t each of the sixteen positions, an y particular rib. for the same centres of pressure their general allowance is made for the probable redistribu­ shapes are similar (although the centre of The loads to be applied, as previously described, were calculated from pressure dis­ pressure will not necessarily be the same for * R.A.F. Crown Copyright reserved.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Nov 1, 1934

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