{"id":558972,"date":"2024-11-05T18:22:34","date_gmt":"2024-11-05T18:22:34","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/esdu-900102014\/"},"modified":"2024-11-05T18:22:34","modified_gmt":"2024-11-05T18:22:34","slug":"esdu-900102014","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/esdu\/esdu-900102014\/","title":{"rendered":"ESDU 90010:2014"},"content":{"rendered":"<p>\n\tESDU 90010 provides a method that applies to a rigid aircraft at<br \/>\nlow angles of attack and relies on summing the separate<br \/>\ncontributions of the body, wing and tailplane with an allowance for<br \/>\nthe interference effect of the body on the wing. The body<br \/>\ncontribution to the pitching moment derivative is calculated from a<br \/>\nsemi-empirical equation in which the body lift-curve slope from<br \/>\nslender body theory is modified for body fineness ratio and<br \/>\ncross-section shape and for afterbody geometry. The body<br \/>\ncontribution to the lift derivative is negligible. For the wing<br \/>\ncontribution to both derivatives, strip theory is also modified<br \/>\nempirically for straight-tapered wings while for delta and<br \/>\ncropped-delta wings it is found that data derived from Multhopp&#039;s<br \/>\nlifting-line theory can be applied directly. Other wing planforms<br \/>\nare converted to straight-tapered through the equivalent wing<br \/>\nconcept of ESDU 76003. The tailplane contribution is found<br \/>\nmost-closely to match the available data if it is treated as an<br \/>\nisolated surface (with lift-curve slope derived from ESDU 70011).<br \/>\nThe body interference on the wing is accounted for by the use of<br \/>\nthe gross planform and a shift in aerodynamic centre position for<br \/>\nthe body carry-over lift. The accuracy of the predictions is<br \/>\ndiscussed, and sketches of experimental results plotted against<br \/>\npredictions are given for the moment derivative, for body and wing<br \/>\nalone and for wing-body combinations. Two worked examples, one for<br \/>\na typical transport configuration and one for a typical interceptor<br \/>\naircraft, illustrate the use of the methods. A computer program of<br \/>\nthe method is provided as ESDUpac A9010.\n\t<\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Pitching moment and lift force derivatives due to rate of pitch for aircraft at subsonic speeds<\/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>2014-12-01<\/td>\n<td>58<\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n","protected":false},"featured_media":558981,"template":"","meta":{"rank_math_lock_modified_date":false,"ep_exclude_from_search":false},"product_cat":[2675],"product_tag":[],"class_list":{"0":"post-558972","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\/558972","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\/558981"}],"wp:attachment":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media?parent=558972"}],"wp:term":[{"taxonomy":"product_cat","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_cat?post=558972"},{"taxonomy":"product_tag","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_tag?post=558972"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}