Static and wind tunnel near-field/far-field jet noise measurements from model scale single-flow baseline and suppressor nozzles. Volume 1: Noise source locations and extrapolation of static free-field jet noise data

A test was conducted in the Boeing Large Anechoic Chamber to determine static jet noise source locations of six baseline and suppressor nozzle models, and establish a technique for extrapolating near field data into the far field. The test covered nozzle pressure ratios from 1.44 to 2.25 and jet velocities from 412 to 594 m/s at a total temperature of 844 K

Analysis of pressure and heat transfer tests on surface roughness elements with laminar and turbulent boundary layers Final report

Data analysis from pressure and heat transfer tests on surface roughness elements with laminar and turbulent boundary layer

Static and wind tunnel near-field/far-field jet noise measurements from model scale single-flow base line and suppressor nozzles. Summary report

A test program was conducted in the Boeing large anechoic test chamber and the NASA-Ames 40- by 80-foot wind tunnel to study the near- and far-field jet noise characteristics of six baseline and suppressor nozzles. Static and wind-on noise source locations were determined. A technique for extrapolating near field jet noise measurements into the far field was established. It was determined if flight effects measured in the near field are the same as those in the far field. The flight effects on the jet noise levels of the baseline and suppressor nozzles were determined. Test models included a 15.24-cm round convergent nozzle, an annular nozzle with and without ejector, a 20-lobe nozzle with and without ejector, and a 57-tube nozzle with lined ejector. The static free-field test in the anechoic chamber covered nozzle pressure ratios from 1.44 to 2.25 and jet velocities from 412 to 594 m/s at a total temperature of 844 K. The wind tunnel flight effects test repeated these nozzle test conditions with ambient velocities of 0 to 92 m/s

Static and wind tunnel near-field/far field jet noise measurements from model scale single-flow baseline and suppressor nozzles. Volume 2: Forward speed effects

A model scale flight effects test was conducted in the 40 by 80 foot wind tunnel to investigate the effect of aircraft forward speed on single flow jet noise characteristics. The models tested included a 15.24 cm baseline round convergent nozzle, a 20-lobe and annular nozzle with and without lined ejector shroud, and a 57-tube nozzle with a lined ejector shroud. Nozzle operating conditions covered jet velocities from 412 to 640 m/s at a total temperature of 844 K. Wind tunnel speeds were varied from near zero to 91.5 m/s. Measurements were analyzed to (1) determine apparent jet noise source location including effects of ambient velocity; (2) verify a technique for extrapolating near field jet noise measurements into the far field; (3) determine flight effects in the near and far field for baseline and suppressor nozzles; and (4) establish the wind tunnel as a means of accurately defining flight effects for model nozzles and full scale engines

Thermal-structural combined loads design criteria study

A study was conducted to determine methodology for combining thermal structural loads and assessing the effects of the combined loads on the design of a thermal protection system and a hot structure of a high cross range delta wing space shuttle orbiter vehicle. The study presents guidelines for establishing a basis for predicting thermal and pressure environments and for determining limit and ultimate design loads on the vehicle during reentry. Limit trajectories were determined by using dispersions on a representative nominal mission and system parameters expected during the life of the vehicle. Nine chosen locations on the vehicle surface having TPS or hot structures were examined, and weight sensitivity analyses were performed for each location

Transpiration cooling system development for reentry vehicles

Transpiration cooling system for reentry vehicle

Guidelines for the use of flow cytometry and cell sorting in immunological studies (third edition)

The third edition of Flow Cytometry Guidelines provides the key aspects to consider when performing flow cytometry experiments and includes comprehensive sections describing phenotypes and functional assays of all major human and murine immune cell subsets. Notably, the Guidelines contain helpful tables highlighting phenotypes and key differences between human and murine cells. Another useful feature of this edition is the flow cytometry analysis of clinical samples with examples of flow cytometry applications in the context of autoimmune diseases, cancers as well as acute and chronic infectious diseases. Furthermore, there are sections detailing tips, tricks and pitfalls to avoid. All sections are written and peer-reviewed by leading flow cytometry experts and immunologists, making this edition an essential and state-of-the-art handbook for basic and clinical researchers

Metastatic recurrence after complete resection of colorectal liver metastases: impact of surgery and chemotherapy on survival

PURPOSE: Surgery is the standard of care for resectable colorectal liver metastases (CRC-LM). Unfortunately, 60 % of patients develop secondary metastatic recurrence (SMR) after R0-resection of CRC-LM. We investigated the impact of surgical re-intervention and chemotherapy (Ctx) on survival in a consecutive series of patients with SMR. METHODS: From 01/2001 to 11/2011, 104 out of 178 consecutive patients with R0-resection of CRC-LM developed SMR and were evaluated. The impact of surgical and Ctx re-interventions on recurrence free (RFS) and cancer-specific survival (CSS) was analyzed. Median follow-up was 28.0 (95 %CI: 19.4–37.4) months. RESULTS: SMR occurred in 81 patients at a single site (49× liver, 18× lung, 14× other) and in 23 patients at multiple sites. Forty-two patients were scheduled for primary surgery. Fifty-three patients were classified as non-resectable and treated with median 5.0 [IQR, 3.0–10.0] cycles of Ctx, combined with an EGFR/VEGF-antibody in 27 patients. Nine patients received best supportive care only. R0/R1 resection could be achieved in 35 patients primarily and even in 8 patients secondarily after Ctx. Surgical morbidity and mortality were 16 and 0 %, respectively. The 5-year RFS rates for patients with R0 versus R1-resection were 22 and 24 % (p = 0.948). The 5-year CSS rate for R0/R1-resected patients was 38 % versus 10 % for those patients treated by Ctx alone (p < 0.001). CONCLUSION: In SMR, surgical re-intervention is feasible and safe in a remarkable number of patients and offers significantly longer CSS compared to patients without resection