{"id":558188,"date":"2024-11-05T18:20:18","date_gmt":"2024-11-05T18:20:18","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/esdu-790061999\/"},"modified":"2024-11-05T18:20:18","modified_gmt":"2024-11-05T18:20:18","slug":"esdu-790061999","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/esdu\/esdu-790061999\/","title":{"rendered":"ESDU 79006:1999"},"content":{"rendered":"

\n\tESDU 79006 gives a correlation of experimental data drawn from a wide range of sources in the literature. Values of Nv for a yawing axis at mid-body position are predicted by an empirical equation in terms of body side area and a parameter that allows for different fore- and after-body shapes. An equation for Yv is also given involving empirical factors shown graphically, one depending on body geometry and wing height, and one depending on wing geometry; the value of Yv can then be used to convert Nv to a different yawing axis position. The method is developed using data at low incidence for small wing sweeps; the effects of incidence, and sweep and dihedral angle, are discussed. . For the effect of nacelles only a few data were available for models tested both with and without free flow nacelles. Rear-fuselage mounted nacelles affect only the contribution due to fin and tailplane (see ESDU 82010) and it is not possible to derive a generalised method for estimating their effect on the derivatives. For two underwing nacelles\/pylons a method is given for predicting their contribution to Yv as a function of the width of the nacelle and its distance below the wing, and hence the contribution to Nv which is additionally a function of the position of the inlet plane and nacelle internal diameter. Configurations with four nacelles are treated by summing the effects of two pairs. ESDU 82011 gives a comprehensive example showing the prediction of those derivatives for a complete aircraft using ESDU data. ESDU 79006 contains worked examples to illustrate the prediction of the contributions of wing, fuselage and nacelles.\n\t<\/p>\n","protected":false},"excerpt":{"rendered":"

Wing-body yawing moment and side force derivatives due to sideslip: N sub v and Y sub v (with Addendum A for nacelle effects)<\/b><\/p>\n\n\n\n\n
Published By<\/td>\nPublication Date<\/td>\nNumber of Pages<\/td>\n<\/tr>\n
ESDU<\/b><\/a><\/td>\n1999-03-01<\/td>\n28<\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n","protected":false},"featured_media":558198,"template":"","meta":{"rank_math_lock_modified_date":false,"ep_exclude_from_search":false},"product_cat":[2675],"product_tag":[],"class_list":{"0":"post-558188","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\/558188","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\/558198"}],"wp:attachment":[{"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/media?parent=558188"}],"wp:term":[{"taxonomy":"product_cat","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_cat?post=558188"},{"taxonomy":"product_tag","embeddable":true,"href":"https:\/\/pdfstandards.shop\/wp-json\/wp\/v2\/product_tag?post=558188"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}