{"id":557512,"date":"2024-11-05T18:18:16","date_gmt":"2024-11-05T18:18:16","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/esdu-140052014\/"},"modified":"2024-11-05T18:18:16","modified_gmt":"2024-11-05T18:18:16","slug":"esdu-140052014","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/esdu\/esdu-140052014\/","title":{"rendered":"ESDU 14005:2014"},"content":{"rendered":"<p>ESDU 14005 provides an empirical method of predicting the lift<br \/>\ncoefficient increment (usually negative, i.e. a decrement) and<br \/>\nrolling moment coefficient due to upper-surface spoiler deployment<br \/>\non a wing at subsonic speed with trailing-edge flaps deployed.<\/p>\n<p>The method predicts the additional lift coefficient increment<br \/>\nover that obtained when the spoiler is deployed on the wing with<br \/>\nflaps undeployed (calculated using ESDU 14004). The corresponding<br \/>\nchange in rolling moment coefficient due to a spoiler deployed on<br \/>\none semi-span wing panel when flaps are deployed can then be<br \/>\ndetermined. The method of ESDU 14005 is used in conjunction with<br \/>\nthat of ESDU 14004 to obtain the total lift coefficient increment<br \/>\nand total rolling moment coefficient due to spoiler deployment on<br \/>\nwings with deployed flaps.<\/p>\n<p>The method of ESDU 14005 applies to plain, single- or<br \/>\ndouble-slotted flaps having flap\/wing chord ratio of 0.2 to 0.4<br \/>\nwith flap deployment angles up to 60\u00b0 and the same range of wing<br \/>\nplanform and spoiler parameters as the method of ESDU 14004. It<br \/>\napplies for practical Reynolds numbers and Mach numbers up to 0.29<br \/>\nfor wings with or without venting from the lower to upper surface.<br \/>\nSketches comparing predicted data with test data show that in most<br \/>\ncases predictions lie within 0.1 for total lift coefficient<br \/>\nincrement and within 0.01 for total rolling moment coefficient.<br \/>\nSome guidance is included on the effect of lower-surface venting<br \/>\nwhich can increase spoiler effectiveness by 30 per cent for<br \/>\nflap-type spoilers with large deflection angles. Two worked<br \/>\nexamples illustrate the use of the method.<\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Lift and rolling moment due to spoilers on wings at subsonic speeds with trailing-edge flaps deployed<\/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>2014-11-01<\/td>\n<td>83<\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n","protected":false},"featured_media":557521,"template":"","meta":{"rank_math_lock_modified_date":false,"ep_exclude_from_search":false},"product_cat":[2675],"product_tag":[],"class_list":{"0":"post-557512","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\/557512","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\/557521"}],"wp:attachment":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media?parent=557512"}],"wp:term":[{"taxonomy":"product_cat","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_cat?post=557512"},{"taxonomy":"product_tag","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_tag?post=557512"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}