Normal view MARC view ISBD view

PRELIMINARY ANALYSIS OF THE EFFECT OF FLOW SEPARATION DUE TO ROCKET JET PLUMING ON AIRCRAFT DYNAMIC STABILITY DURING ATMOSPHERIC EXIT

Material type: materialTypeLabel

BookPublisher: Nasa, Washington, D.C. 1959Description: 35.DDC classification: NASA | MEMO 4-22-59E -

average rating: 0.0 (0 votes)

Item type	Current location	Collection	Call number	Status	Date due	Barcode	Item holds
Technical Report	PK Kelkar Library, IIT Kanpur	General Stacks	NASA MEMO 4-22-59E - (Browse shelf)	Not for loan		TR7711

Total holds: 0

Previous								Next
Previous	NASA MEMO 4-20-59L TRANSONIC AERODYNAMIC CHARACTURISTICS OF A 45DEGREE SWEPT-WING-FUSELAGE MODEL WITH A FINNED AND UNFINNED BODY PYLON-MOUNTED BENEATH THE FUSELAGE OR WING, INCLUDING MEASUREMENTS OF BODY LOADS	NASA MEMO 4-21-59E - ANALYSIS OF FLOW-SYSTEM STARTING DYNAMICS OF TURBOPUMP-FED LIQUID-PROPELLANT ROCKET	NASA MEMO 4-21-59L INVESIGATION OF THE CHAACTERISTICS OF AN ACCELERATION-TYPE TAKE-OFF INDICATOR IN A LARGE JET AIRPLANE	NASA MEMO 4-22-59E - PRELIMINARY ANALYSIS OF THE EFFECT OF FLOW SEPARATION DUE TO ROCKET JET PLUMING ON AIRCRAFT DYNAMIC STABILITY DURING ATMOSPHERIC EXIT	NASA MEMO 4-22-59L LOW-SPEED LONGITUDINAL CHARACTERISTICS OF AN AIRPLANE CONFIGURATION INCLUDING EFFECTS OF CANARD AND WING TRAILING-EDGE FLAP CONTROLS IN COMBINATION	NASA MEMO 4-23-59L ANALYTICAL INVESTIGATION OF A FLIKER-TYPE ROLL CONTROL FOR A MACH NUMBER 6 MISSILE WITH AERODYNAMIC CONTROLS OVER AN ALTITUDE RANGE OF 82,000 TO 282,000 FEET	NASA MEMO 4-2-59L - STABILITY CHARACTERISTICS FROM MACH NUMBER 1.0 TO 3.2 OF A MISSILE OF FINENESS RATIO 11.5 WITH A 10(DEGREE) FLARED-SKIRT AFTERBODY	Next

Bound With Nasa Memo 4-6-59e-4-30-59e

There are no comments for this item.

PKK Library