File:Cx ogives de fusées.png
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[edit]DescriptionCx ogives de fusées.png |
Français : Cx frontal des ogives de fusées selon leur forme d'après le Hoerner "Drag". Hoerner annonce même des Cx négatifs pour la première ogive (apparemment parabolique), mais ce n'est que le Cx de pression.[1], [2].
English: Frontal Cd of rocket noses according to their form after the Hoerner "Drag". Hoerner even gave negative Cd for the first nose (apparently parabolic), but it is only the pressure Cd.[3]. |
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Author | Bernard de Go Mars |
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Annotations InfoField | This image is annotated: View the annotations at Commons |
Les cités ici sont tous des frontaux (c.-à-d. établis en référence à la section frontale des ogives).
Entre 10 et 60° de demi angle au sommet, les résultats d’essais de cônes en tant qu’avant corps (c.-à-d. sans de culot, donc en tant qu’ogives)[4] , [5] , [6] peuvent être linéarisés sous la forme :
étant le demi angle au sommet du cône en degrés. Cette linéarisation n’est valide qu'en subsonique, c.-à-d. pour .
Entre 10 et 60° de demi angle au sommet, les résultats d’essais de cônes en tant qu’avant corps (c.-à-d. sans de culot, donc en tant qu’ogives)[7] , [8] , [9] peuvent être linéarisés sous la forme :
étant le demi angle au sommet du cône en degrés. Cette linéarisation n’est valide qu'en subsonique, c.-à-d. pour .
Le Cx de l’ogive hémisphérique annoncé par Hoerner est très bas, surtout en comparaison du tableau du Vol de la fusée de Planète Sciences[10] qui annonce pour cette ogive hémisphérique un de 0,8 (il est probable que tous les chiffres de ce tableau sont mélangés, voir à ce sujet la Note technique NASA D-3388[11]) qui confirme la valeur relayée par Hoerner.
- ↑ p49, S. F. Hoerner, Résistance à l'avancement dans les fluides, Gauthier-Villars |éditeur, Paris, 1965
- ↑ p3-12, S. F. Hoerner, Fluid-dynamic drag : theoretical, experimental and statistical information, 1992
- ↑ p3-12, S. F. Hoerner, Fluid-dynamic drag : theoretical, experimental and statistical information, 1992
- ↑ AN INVESTIGATION OF VARIOUS PARAMETERS AFFECTING THE STRUCTURAL WEIGHT OF ROCKET VEHICLE NOSE CONES, by Clyde D. Nevins and Benny W. Helton, MARSHALL SPACE FLIGHT CENTER [1]
- ↑ AERODYNAMIC CHARACTERISTICS OF SPHERICALLY BLUNTED CONES AT MACH NUMBERS FROM 0.5 TO 5.0 , NASA TN D-3088,by Robert V. Owens, George C. Marshall Space Flight Center Huntsville, Ala. [2]
- ↑ THE AERODYNAMIC CHARACTERISTICS OF LARGE ANGLED CONES WITH RETROROCKETS, Contract N° NAS 7-576, by Philip O. Jarvinen and Richard H. Adams, February 1970 [[ http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720005324_1972005324.pdf]]
- ↑ AN INVESTIGATION OF VARIOUS PARAMETERS AFFECTING THE STRUCTURAL WEIGHT OF ROCKET VEHICLE NOSE CONES, by Clyde D. Nevins and Benny W. Helton, MARSHALL SPACE FLIGHT CENTER [3]
- ↑ AERODYNAMIC CHARACTERISTICS OF SPHERICALLY BLUNTED CONES AT MACH NUMBERS FROM 0.5 TO 5.0 , NASA TN D-3088,by Robert V. Owens, George C. Marshall Space Flight Center Huntsville, Ala. [4]
- ↑ THE AERODYNAMIC CHARACTERISTICS OF LARGE ANGLED CONES WITH RETROROCKETS, Contract N° NAS 7-576, by Philip O. Jarvinen and Richard H. Adams, February 1970 [[ http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720005324_1972005324.pdf]]
- ↑ Le Vol de la fusée, Stabilité et Trajectographie, Version 2.0 - juillet 2008,Planète Sciences [5]
- ↑ EFFECTS OF BLUNTNESS ON THE SUBSONIC DRAG OF AN ELLIPTICAL FOREBODY, NASA TECHNICAL NOTE D-3388, by John D. Norris and Robert J. McGhee [6]
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