11 - Supersonic parachutes Lingard.pdf

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Supersonic Inflation subsonic flow: KK = vv ss tt ii / DD 00 supersonic flow: KK(ρρ CC / ρρ 00) ) = vv ss tt ii / DD 00 - Greene KK(uu 11 / uu 22) ) = vv ss tt ii / DD 00 these these are virtually equivalent since for continuity uu 1 1 ρρ 11 = uu 2 2 ρρ 22 across a shock wave
Inflation distance as function of Mach number L / (Do K) 6 5 4 3 2 1 0 0 1 2 3 4 5 Mach Number velocity ratio density ratio
Page 1 and 2:
Parachute Seminar 3rd International
Page 3 and 4:
Requirements high drag to weight ra
Page 5 and 6:
Ribbon parachute drag coefficient
Page 7 and 8:
Supersonic parachute behavior Cd 0.
Page 9 and 10:
Supersonic Flow Compressibility Hig
Page 11 and 12: Flow around a hollow hemisphere Mac
Page 13 and 14: Hemisflo - M 1.9 Shock waves
Page 15 and 16: Flow around a hollow hemisphere and
Page 17 and 18: Supersonic parachute behavior
Page 19 and 20: Flow around a disk-gap disk gap-ban
Page 37 and 38: Wake effects M Forebody Shock 1 Sho
Page 39 and 40: Ribbon flutter modified pressure di
Page 41 and 42: Conical Ribbon Parachute
Page 43 and 44: Hemisflo Parachute More refined sha
Page 45 and 46: Supersonic-X Supersonic X parachute
Page 47 and 48: Disk-Gap Disk Gap-Band Band tested
Page 49 and 50: Hermes Testing Test decelerators: s
Page 51 and 52: Ribbon parachute drag coefficient
Page 53 and 54: Drag coefficient vs M
Page 55 and 56: Huygens DGB main ogive wake Cd 0.75
Page 57 and 58: Galileo testing - transonic drag lo
Page 59 and 60: Drag summary Conical ribbon - effec
Page 61: Stability vs M
Page 65 and 66: Aerodynamic Heating stagnation temp
Page 67 and 68: Aerodynamic Heating high temperatur
Page 69 and 70: Design guide 2 sometimes a multi-st
Page 71 and 72: Design guide 4 if aerodynamic heati
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