{"id":558332,"date":"2024-11-05T18:20:43","date_gmt":"2024-11-05T18:20:43","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/esdu-810142013\/"},"modified":"2024-11-05T18:20:43","modified_gmt":"2024-11-05T18:20:43","slug":"esdu-810142013","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/esdu\/esdu-810142013\/","title":{"rendered":"ESDU 81014:2013"},"content":{"rendered":"<p>\n\tESDU 81014 presents a method of estimating the planform<br \/>\ncontribution to the yawing moment due to roll-rate, (Np)w, and the<br \/>\nsideforce due to roll rate, (Yp)w, of swept wings at subsonic<br \/>\nspeeds. The method applies to wings without dihedral, camber or<br \/>\ntwist, in the &#034;clean condition&#034;, i.e. with any high-lift devices<br \/>\nretracted. The method was originally developed for untapered wings<br \/>\nbut data have been provided to take into account the small effect<br \/>\nof wing taper. The method for the sideforce derivative applies only<br \/>\nover the range of lift coefficients for which the flow is attached<br \/>\nto the wing surface and (Yp)w varies linearly with lift<br \/>\ncoefficient. In the case of the yawing moment derivative, however,<br \/>\nthe data provide an empirical means of extending the estimation<br \/>\ninto the range of lift coefficients in which areas of flow<br \/>\nseparation exist and (Np)w varies non-linearly with lift<br \/>\ncoefficient and often changes sign at a moderate to high lift<br \/>\ncoefficient. The knowledge provided by the data of where such a<br \/>\nchange in sign occurs is very important to the designer in<br \/>\nassessing the stability of an aircraft. The data cover an aspect<br \/>\nratio range from 2 to 12, wing sweepback angles up to 60 degrees<br \/>\nand Atan? \u00bc = 6. The first-order effects of subsonic Mach number<br \/>\nare also catered for. A computer program of the method is provided<br \/>\nas ESDUpac A8114.\n\t<\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Contribution of wing planform to derivatives of yawing moment and side force due to roll rate at subsonic speeds, (Np)w and (Yp)w<\/b><\/p>\n<table style=\"width: 100%\" border=\"0\" cellspacing=\"0\" cellpadding=\"0\">\n<tbody>\n<tr>\n<td>Published By<\/td>\n<td>Publication Date<\/td>\n<td>Number of Pages<\/td>\n<\/tr>\n<tr>\n<td><a href=\"https:\/\/pdfstandards.shop\/product-category\/publishers\/esdu\/\"><b>ESDU<\/b><\/a><\/td>\n<td>2013-08-01<\/td>\n<td>36<\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n","protected":false},"featured_media":558341,"template":"","meta":{"rank_math_lock_modified_date":false,"ep_exclude_from_search":false},"product_cat":[2675],"product_tag":[],"class_list":{"0":"post-558332","1":"product","2":"type-product","3":"status-publish","4":"has-post-thumbnail","6":"product_cat-esdu","8":"first","9":"instock","10":"sold-individually","11":"shipping-taxable","12":"purchasable","13":"product-type-simple"},"_links":{"self":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product\/558332","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product"}],"about":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/types\/product"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media\/558341"}],"wp:attachment":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media?parent=558332"}],"wp:term":[{"taxonomy":"product_cat","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_cat?post=558332"},{"taxonomy":"product_tag","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_tag?post=558332"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}