Analysis and test evaluation of the dynamic response and stability of three advanced turboprop models at low forward speed / by Arthur F. Smith.
"Results of wind tunnel tests at low forward speed for blade dynamic response and stability of three 62.2 cm (24.5 in) diameter models of the Prop-Fan, advanced turboprop, are presented. Measurements of dynamic response were made with the rotors mounted on an isolated nacelle, with varying tilt for...
| Uniform Title: | NASA contractor report ;
NASA CR-175026. |
|---|---|
| Main Author: | |
| Corporate Authors: | |
| Language: | English |
| Published: |
Windsor Locks, Conn. : Cleveland, Ohio : [Springfield, Va.] :
United Technologies Corporation, Hamilton Standard Division ; National Aeronautics and Space Administration, Lewis Research Center ; [For sale by the National Technical Information Service],
1985.
|
| Series: | NASA contractor report ;
NASA CR-175026. |
| Subjects: | |
| Physical Description: | x, 101/102 pages : illustrations. Distributed to depository libraries in microfiche; also available online. |
| Format: | Government Document Microfilm Book |
MARC
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| 086 | 0 | |a NAS 1.26:175026 | |
| 088 | |a HSER-11055 | ||
| 099 | |a NAS 1.26:175026 | ||
| 100 | 1 | |a Smith, Arthur F. | |
| 245 | 1 | 0 | |a Analysis and test evaluation of the dynamic response and stability of three advanced turboprop models at low forward speed / |c by Arthur F. Smith. |
| 260 | |a Windsor Locks, Conn. : |b United Technologies Corporation, Hamilton Standard Division ; |a Cleveland, Ohio : |b National Aeronautics and Space Administration, Lewis Research Center ; |a [Springfield, Va.] : |b [For sale by the National Technical Information Service], |c 1985. | ||
| 300 | |a x, 101/102 pages : |b illustrations. | ||
| 336 | |a text |b txt |2 rdacontent | ||
| 337 | |a microform |b h |2 rdamedia | ||
| 338 | |a microfiche |b he |2 rdacarrier | ||
| 490 | 1 | |a NASA-CR ; |v 175026 | |
| 500 | |a "December, 1985." | ||
| 500 | |a Microform. | ||
| 504 | |a Includes bibliographical references (page 29/30). | ||
| 513 | |a Final report. | ||
| 530 | |a Distributed to depository libraries in microfiche; also available online. | ||
| 520 | 3 | |a "Results of wind tunnel tests at low forward speed for blade dynamic response and stability of three 62.2 cm (24.5 in) diameter models of the Prop-Fan, advanced turboprop, are presented. Measurements of dynamic response were made with the rotors mounted on an isolated nacelle, with varying tilt for nonuniform inflow. Low speed stall flutter tests were conducted at Mach numbers from 0.0 to 0.35. Measurements are compared to Eigen-solution flutter boundaries. Calculated 1P stress response agrees favorably with experiment. Predicted stall flutter boundaries correlate well with measured high stress regions. Stall flutter is significantly reduced by increased blade sweep. Susceptibility to stall flutter decreases rapidly with forward speed."--NTIS abstract. | |
| 533 | |a Microfiche. |b [Washington, D.C.] : |c National Aeronautics and Space Administration, |d 1988. |e 2 microfiches : negative. | ||
| 650 | 0 | |a Airplanes |x Turbine-propeller engines |x Blades |x Testing. |0 http://id.loc.gov/authorities/subjects/sh85002907 | |
| 650 | 0 | |a Airplanes |x Turbojet engines |x Blades |x Testing. |0 http://id.loc.gov/authorities/subjects/sh85002911 | |
| 650 | 0 | |a Turbines |x Blades |x Testing. |0 http://id.loc.gov/authorities/subjects/sh85138720 | |
| 650 | 0 | |a Propellers |x Aerodynamics |x Testing. |0 http://id.loc.gov/authorities/subjects/sh85107486 | |
| 650 | 7 | |a Aerodynamic stability. |2 nasat | |
| 650 | 7 | |a Dynamic response. |2 nasat | |
| 650 | 7 | |a Dynamic structural analysis. |2 nasat | |
| 650 | 7 | |a Evaluation. |2 nasat | |
| 650 | 7 | |a Prop-fan technology. |2 nasat | |
| 650 | 7 | |a Turboprop engines. |2 nasat | |
| 650 | 7 | |a Propeller fans. |2 nasat | |
| 653 | |a Prop-fan technology; Turboprop engines; Nacelles; Rotors; Aerodynamic stability; Dynamic response; Dynamic structural analysis; Aerodynamic stalling; Flutter analysis; Installing; Mach number; Wind tunnel models; Wind tunnel tests; Evaluation; Finite element method. | ||
| 710 | 2 | |a Lewis Research Center. |0 http://id.loc.gov/authorities/names/n80126316 | |
| 710 | 2 | |a United Technologies Corporation. |b Hamilton Standard Division. |0 http://id.loc.gov/authorities/names/n79004513 | |
| 776 | 0 | 8 | |i Print version: |a Smith, Arthur F. |t Analysis and test evaluation of the dynamic response and stability of three advanced turboprop models at low forward speed. |w (OCoLC)804877164. |
| 776 | 0 | 8 | |i Online version: |a Smith, Arthur F. |t Analysis and test evaluation of the dynamic response and stability of three advanced turboprop models at low forward speed. |w (OCoLC)804877134. |
| 830 | 0 | |a NASA contractor report ; |v NASA CR-175026. |0 http://id.loc.gov/authorities/names/n83825229 | |
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| 952 | f | f | |p Non-Circulating |a Michigan State University-Library of Michigan |b Michigan State University |c MSU Government Documents |d MSU Government Documents - U.S. Fiche, 2 West |t 0 |e NAS 1.26:175026 |h Other scheme |i Microform (Microfilm/Microfiche) |n 1 |