WIND TUNNEL FACILITIES AT THE JET PROPULSION LABORATORY
Abstract
The wind tunnel failiies presently available at JP for NAA and miltary-service tesing purposes are debed. he wind tunnel failities include a 20-in. upersonic wind tunnel 9swt0 with a Mach-nuber range of 1.3 to 5.6 and a 21-in. hypersonc wind tunnel (HWT) wth a Mach-number range of 4.1 to 11.0. The geometric ze of the 20-in. SWT TEST SECTION IS !*-IN. WIDE BY <)-IN. HIGH, WHILE THE <!-IN. HWT hs a tet seion whch s 21 inches wide at the downsream end (the de walls each iverge t abot /2 deg) and 15 to 28-in. high (DJUSTABLE). Both wind unnels are of the coninuousflow, variable-density type and each utilizes a two-imensional flexle nozzle which can provide an infinite choce of test-section Mch numbers within a speified range. autho)AD-25527N! $+$ <)), >*%(, >)%, )!<, ><<$, !)<, >*%*, (*, !(>, !+$$, ><!%, *(*, ><!+, ><!>, >+ A-255 328Div. 27, 12, 26 (5 may 61) OTS pce 1.10 yon, Inc., Detroit, Mch. DEEP DRAWN PRE-PRODUION UNITS 2 T AGE POIS ROCKET MOTOR CHAMBERS AND A2 1ST STAGE POLRIS AFT CLOSURES, by Wayne A. Main. General rept. no. 6, 31 Jan28 Feb 61. 28 Feb 61, 7p. (Contrat NOw 60-0630) uncassified report DESCIPTOS: *Guided missiles, Forging, underwater to rface, SRFACE TO URFACE, *ocket cases, *ocket motors, Processing, Manufctuing methods, *MACHINE TOOLS, Dies, Hydraulic presses, Rocket motor nozles, *Booster rokets, *Gided missile boosters. Open-ended Terms: Polaris.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 18, 1961
- Accession Number
- AD0255327
Entities
People
- G.g. Goranson
- H.d. Strong
Organizations
- Jet Propulsion Laboratory