Accession Number:

AD0255327

Title:

WIND TUNNEL FACILITIES AT THE JET PROPULSION LABORATORY

Descriptive Note:

Corporate Author:

JET PROPULSION LAB PASADENA CALIF

Personal Author(s):

• GORANSON,G.G.
• STRONG,H.D.

Report Date:

1961-04-18

Pagination or Media Count:

1.0

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. authoAD-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.

Descriptors:

• *HYPERSONIC WIND TUNNELS
• *SUPERSONIC WIND TUNNELS
• *TEST FACILITIES
• *WIND TUNNELS
• AERODYNAMIC CHARACTERISTICS
• CALIBRATION
• DIGITAL COMPUTERS
• INSTRUMENTATION
• LABORATORIES
• MODEL TESTS
• TEST EQUIPMENT
• TEST METHODS
• WIND TUNNEL NOZZLES

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE