Dryden Technical Report Server
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- IN-FLIGHT TRANSITION MEASUREMENT ON A 10 DEG CONE AT MACH NUMBERS FROM 0.5 TO 2.0 , Technical Paper
Authors: D. F. Fisher and N. S. Dougherty, Jr.
Report Number: NASA-TP-1971
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Boundary layer transition measurements were made in flight on a 10 deg transition cone tested previously in 23 wind tunnels. The cone was mounted on the nose of an F-15 aircraft and flown at Mach numbers room 0.5 to 2.0 and altitudes from 1500 meters (5000 feet) to 15,000 meters (50,000 feet), overlapping the Mach number/Reynolds number envelope of the wind tunnel tests. Transition was detected using a traversing pitot probe in contact with the surface. Data were obtained near zero cone incidence and adiabatic wall temperature. Transition Reynolds number was found to be a function of Mach number and of the ratio of wall temperature to adiabatic all temperature. Microphones mounted flush with the cone surface measured free-stream disturbances imposed on the laminar boundary layer and identified Tollmien-Schlichting waves as the probable cause of transition. Transition Reynolds number also correlated with the disturbance levels as measured by the cone
surface microphones under a laminar boundary layer as well as the free-stream impact.
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Subject Category: 02
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PDF (6,043 KBytes)
Report Date: June 1982
No. Pages: 143
Keywords: Boundary layer transition; F-15 aircraft; Flow measurement; In-flight monitoring; Mach number.
- A GENERAL SOLUTION TO THE HIDDEN-LINE PROBLEM , Reference Publication
Authors: D. R. Hedgley, Jr.
Report Number: NASA-RP-1085
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The requirements for computer-generated perspective projections of three dimensional objects has escalated. A general solution was developed. The theoretical solution to this problem is presented. The method is very efficient as it minimizes the selection of points and comparison of line segments and hence avoids the devastation of square-law growth.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 59
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PDF (619 KBytes)
Report Date: March 1982
No. Pages: 17
Keywords: Computer aided design; Computer graphics; Computerized simulation; Lines (geometry); Plotting.
- KC-135 WINGLET PROGRAM REVIEW , Conference Publication
Authors: Various
Report Number: NASA-CP-2211
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The results of a joint NASA/USAF program to develop flight test winglets on a KC-135 aircraft are reviewed. The winglet development from concept through wind tunnel and flight tests is discussed. Predicted, wind tunnel, and flight test results are compared for the performance, loads and flutter characteristics of the winglets. The flight test winglets had a variable winglet cant and incidence angle capability which enabled a limited evaluation of the effects of these geometry changes.
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Subject Category: 02
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From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1982
No. Pages: 193
Keywords: Aerodynamic characteristics; Aerodynamic loads; Aircraft performance; C-135 aircraft; Conferences.
Notes: Symp. held in Edwards, Calif., 16 Sep. 1981.
- USER'S GUIDE FOR SKETCH , Technical Memorandum
Authors: D. R. Hedgley, Jr.
Report Number: NASA-TM-81369
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A user's guide for the computer program SKETCH is presented. The removal of hidden lines from images of solid objects is a problem in computer graphics which is solved by SKETCH.
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Subject Category: 59
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PDF (327 KBytes)
Report Date: February 1982
No. Pages: 13
Keywords: Computer graphics; Error detection codes; FORTRAN; Lines (geometry); User manuals (computer programs);
- A FLIGHT TEST MANEUVER AUTOPILOT FOR A HIGHLY MANUEVERABLE AIRCRAFT , Technical Memorandum
Authors: R. B. Roncoli
Report Number: NASA-TM-81372
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight test maneuver autopilot (FTMAP) is currently being flown to increase the quality and quantity of the data obtained in the flight testing of the highly maneuverable aircraft technology (HiMAT) remotely piloted research vehicle (RPRV). The FTMAP resides in a ground-based digital computer and was designed to perform certain prescribed maneuvers precisely, while maintaining critical flight parameters within close tolerances. The FTMAP operates as a non-flight-critical outer loop controller and augments the vehicle primary flight control system. The inputs to the FTMAP consist of telemetry-downlinked aircraft sensor data. During FTMAP operation, the FTMAP computer replaces normal pilot inputs to the aircraft stick and throttle positions. The FTMAP maneuvers include straight-and-level flight, level accelerations and decelerations, pushover pullups, and windup turns. The pushover pullups can be executed holding throttle or Mach number fixed. The
windup turns can be commanded by either normal acceleration or angle of attack. The operational procedures, control mode configuration, and initial simulation results are discussed.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 08
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PDF (1,587 KBytes)
Report Date: November 1982
No. Pages: 27
Keywords: Aircraft maneuvers; Automatic flight control; Automatic pilots; Flight tests; Remotely piloted vehicles.
Notes: Presented at the AIAA region 6 32nd Ann. Student Conf., Irvine, Calif., 28 Apr. - 1 May 1982.
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