NASA NACA-TR-766-1943 Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body - NACA model 84 series《NACA模型第84系列流线型机身飞行外壳模型系族的空气动力和水.pdf

《NASA NACA-TR-766-1943 Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body - NACA model 84 series《NACA模型第84系列流线型机身飞行外壳模型系族的空气动力和水.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TR-766-1943 Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body - NACA model 84 series《NACA模型第84系列流线型机身飞行外壳模型系族的空气动力和水.pdf（89页珍藏版）》请在麦多课文档分享上搜索。

1、REPORT No. 766AERODYNAMIC AND HYDRODYNAMIC TESTS OF A FAMILY OF MODELS OF FLYING-BOATHULLS DERIVED FROM 1A STREAMLINE BODYNACA MODEL S4 SERIESBy JOHNB. PAIt-SON, ROLANDE. OLSON,EUGENHC. DmmY, and AIzvo A. LUOMA. SUMMARY .A sti of relatedforms of j?ying-boa$ hulls reprtxwtingvarious degrem of comprom

2、tie betweeng.erodynamicand hydro-dynamic requirementswas tated in .Lm.gleytank no. 1 and inth-sLungley S#oot high+eed tunnel. The puxpose of theinvestigationwm to provide information regardi the pen.altiin wa.?erperformancerewdtingjromfurt.b aerodynamicre$ne-meni and, m a corollary, to provide infor

3、mation regarding tlwpenultia in range or pag load malting from the relention ofcvtuin ohtiable hydrodynamic characteristti. 21.e informa-tion shouldform a bti for over-allimprovemerdsin hullform.The reluted moo?e.kof the series were bawd on an arbitrastreandim bodg of revoltiwn. The variations in fo

4、ti weredevelopedin mu% a way as to Aow clearly the eect of con-ventionaldepartuw from the ideal 8treandin.ebodg madein thedesign ofjZying-boathulk.Tlw mode+?-swere 11.486 inehe8 long and the dianwter of thebmic streamlineform tom 16.9g inches. In the hydrodynamicte.%trtx%tunce and trim or trimming m

5、om-antswere mecmuredat d? speeds and lomi%of intere-stand the spray patkrrw werephotographed. Iri the aerodynamic testi, lift, drag, and pitch-ing momentwere meamwedwith transitionjixed at 6 pmceni qfthe length, a$speede up to O mike pm hour, and at Reynotinumber8up to 30,000,000.The rewarying b hei

6、 of it 10wer8the resistance at planing 8peed. A low angle of aerbody keel .rtxuh%in the e+%unatrunning at low sped. Increaing theangle of afterbody ked iweases the trim al which tti m“olentin4zbility rewl.tingfrom too 8h.albw a 8tep will be encountered.(7 E$eet of addition of chineJ?ureChinefire add

7、ed tnia+or to the straighJbottom 8ectwns ofthe forebody h.m on+?ya small eJect on tlhtrem%tanceand trimup to and inchuling the hump speed M rds in a marked(Jimpr ement in cleanmxwof running. Chinejare ad.dkdto theajterbody reductx the rw.8tame at the hump qoeed and dightlyincreases the re8i8tan.ceai

8、 pluming 8peed8.(8) Ejeei of aciliitionof th+d pluning swrfaceThe addition of a thirdplaning wrfaee on tlw modidwith thelowat 8tern hm a neglig+ilh eyed m tlw trim and re8Mancea remarkable remdi becuwe the 8tern 8eciiG-.n4tmhul theplaning tw.ufaceare circular and heavily wetted. The additionOftti ph

9、ni SNXfCZJX80i7MWh41ttWbtl.G84thz? WdtiT-.-Ch-.0,1.,!,t1CA-.8Cr-.m cr=L12 fS- LWFIGUREIL-Mm Stc. Bow%.56A .64z (b)t I t I I.5 1.0 5 20 2.5 3.0 3.5 40 45Speed coefficient - (b) WnhoutChhe flme.IIF OURElZ-Eff.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-