Measurements of sonic booms generated by an airplane flying at Mach 3.5 and 4.8

Sonic booms generated by the X-15 airplane flying at Mach numbers of 3.5 and 4.8 were measured. The experimental results agreed within 12 percent with results obtained from theoretical methods. No unusual phenomena related to overpressure were encountered. Scaled data from the X-15 airplane for Mach 4.8 agreed with data for an SR-71 airplane operating at lower Mach numbers and similar altitudes. The simple technique used to scale the data on the basis of airplane lift was satisfactory for comparing X-15 and SR-71 sonic boom signatures

Letter from Edward K. Putnam to J. E. Calkins, 1907 Oct 23.

Estate of William Clement PutnamTRUSTEES HENRY ST. CLAIR PUTNAM GEORGE ROCKWELL PUTNAM EDWARD KIRBY PUTNAM BENJAMIN RISLEY PUTNAM ELIZABETH DUNCAN PUTNAM DAVENPORT. IOWA. Oct. 23rd, 1907. Mr. J. E. Calkins,Palo Alto, Gal. Dear Sir:-Thank you for your letter about the Hetch-Hetchy Valley. I will be glad to give what help I can in saving this valley.Hoping you are enjoying the sunshine in California and with beet wishes, I amYours very sincerely,[illegible] Dict. E.K.P.0623

Preliminary measurements of aircraft airframe noise with the NASA CV-990 aircraft

Flight tests were conducted in a CV-990 jet transport with engines at idle power to investigate aircraft airframe noise. Test results showed that airframe noise was measured for the aircraft in the landing configuration. The results agreed well with the expected variation with the fifth power of velocity. For the aircraft in the clean configuraton, it was concluded that airframe noise was measured only at higher airspeeds with engine idle noise present at lower speeds. The data show that landing gear and flaps make a significant contribution to airframe noise

The Administrative Climb with American Lung Association

The American Lung Association is a Nationwide non-profit organization. During times of COVID, many businesses and organizations have been struggling, especially nonprofits. Nonprofit organizations rely heavily on sponsors, donors and events to bring in the money they need to stay running. A major event for ALA is the Fight For Air Climb. The FFAC had to make changes due to Covid precautions and protocols. While in the midst of a pandemic, the nation is also in the middle of a vaping epidemic. ALA is dedicated in putting a stop to the vaping epidemic

Landing approach airframe noise measurements and analysis

Flyover measurements of the airframe noise produced by the AeroCommander, JetStar, CV-990, and B-747 airplanes are presented for various landing approach configurations. Empirical and semiempirical techniques are presented to correlate the measured airframe noise with airplane design and aerodynamic parameters. Airframe noise for the jet-powered airplanes in the clean configuration (flaps and gear retracted) was found to be adequately represented by a function of airplane weight and the fifth power of airspeed. Results show the airframe noise for all four aircraft in the landing configuration (flaps extended and gear down) also varied with the fifth power of airspeed, but this noise level could not be represented by the addition of a constant to the equation for clean-configuration airframe noise

Flight test evaluation of an RAF high altitude partial pressure protective assembly

A partial pressure suit was evaluated during tests in an F-104 and F-15 as a protective garment for emergency descents. The garment is an pressure jerkin and modified anti-g suit combined with an oronasal mask. The garment can be donned and doffed at the aircraft to minimize thermal buildup. The oronasal mask was favored by the pilots due to its immobility on the face during high g-loading. The garment was chosen to provide optimum dexterity for the pilot, which is not available in a full pressure suit, while protecting the pilot at altitudes up to 18,288 meters, during a cabin decompression, and subsequent aircraft descent. During cabin decompressions in the F-104 and F-15, cabin pressure altitude was measured at various aircraft angles of attack, Mach numbers, and altitudes to determine the effect of the aerodynamic slipstream on the cabin altitude