{"id":557514,"date":"2024-11-05T18:18:17","date_gmt":"2024-11-05T18:18:17","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/esdu-140042014\/"},"modified":"2024-11-05T18:18:17","modified_gmt":"2024-11-05T18:18:17","slug":"esdu-140042014","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/esdu\/esdu-140042014\/","title":{"rendered":"ESDU 14004:2014"},"content":{"rendered":"
ESDU 14004 considers the flat plate (deployed in a plane normal
\nto the section chord) and flap (pivoting about a hinge) types of
\nrectangular spoilers on the upper surface of a wing with
\ntrailing-edge flaps undeployed. It discusses the flow behaviour
\nwith variation of spoiler deployment and wing angle of attack, as
\nwell as the effect of spoiler chordwise position on wing lift-curve
\nslope.<\/p>\n
A method is presented for predicting the lift coefficient
\nincrement (usually negative, i.e. a decrement) and rolling moment
\ncoefficient due to spoiler deployment on the upper surface of a
\nwing at subsonic speeds. The two-dimensional lift coefficient
\nincrement characteristics are first determined, and the
\ncorresponding three-dimensional lift coefficient increment and
\nrolling moment coefficient characteristics are then deduced.<\/p>\n
The method is applicable for any form of porosity (perforations,
\nhinge-line gaps, spoiler segmentation or edge castellation) up to
\n0.38 of the spoiler area. Spoiler chordwise locations from 0.4c to
\nthe trailing-edge are covered for spoiler deployment height to wing
\nchord ratios from 0.04 to 0.15. Spoiler deployment height is
\ndefined as the height above the wing surface and it is the height
\nof the spoiler trailing-edge above the wing surface in the case of
\nflap-type spoilers. The method is applicable for both
\nstraight-tapered and cranked wings with spoilers sweptback up to 45
\ndegrees for Mach numbers up to 0.7. Lift increment and rolling
\nmoment behaviour is affected by wing angle of attack, and limits of
\napplicability for both minimum and maximum angles of attack are
\nsuggested. Sketches comparing predicted data with test data show
\nthat in most cases predictions lie within 0.03 for lift coefficient
\nincrement and within 0.003 for rolling moment coefficient.<\/p>\n","protected":false},"excerpt":{"rendered":"
Lift and rolling moment due to spoilers on wings at subsonic speeds with trailing-edge flaps undeployed<\/b><\/p>\n\n\n
\n Published By<\/td>\n Publication Date<\/td>\n Number of Pages<\/td>\n<\/tr>\n \n ESDU<\/b><\/a><\/td>\n 2014-11-01<\/td>\n 68<\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n","protected":false},"featured_media":557523,"template":"","meta":{"rank_math_lock_modified_date":false,"ep_exclude_from_search":false},"product_cat":[2675],"product_tag":[],"class_list":{"0":"post-557514","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\/557514","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\/557523"}],"wp:attachment":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media?parent=557514"}],"wp:term":[{"taxonomy":"product_cat","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_cat?post=557514"},{"taxonomy":"product_tag","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_tag?post=557514"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}