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Administration AERONAUTICS AND SPACE aircraft angle Apollo approach approximately bearing Block boattail Center changes chi-square CM CM CM CM CO CO CM CO CO CO conducted configuration considered Continued corrected cowl crack determined deviations diameter difference dimensions discussed distance distribution effect equation etched failure fibers Figure flight friction function heat increase indicated initial input load maximum mean measured metal meter NASA normal Note nozzle observed obtained oo oo operating parameter percent performance plate position presented pressure probability problem range ratio reference rH CM rH rH Runs sample selected separation shown shows square star Statistics strength stress surface TABLE TECHNICAL temperature thermal units values variation vortex wedge wind zero
Page iii - As an aid to the reader, where necessary the original units of measure have been converted to the equivalent value in the Systeme International d
Page x - Type I and Type II errors. A Type I error is the rejection of a...
Page 8 - Fatigue Crack Propagation in Unnotched and Notched Aluminum Alloy Specimens," NLR-TR-M2128, National Aerospace Laboratories, Amsterdam, Netherlands, May 1964.
Page 63 - Classif. (of this report! 20. Security Classif. (of this pagel 21. No. of Pages 22. Price...