Dryden Technical Report Server
From the NTRS FAQ: Where do I go for a hardcopy of the report?
- DETERMINATION OF STABILITY DERIVATIVES FROM FLIGHT DATA USING A NEWTON-RAPHSON MINIMIZATION TECHNIQUE , Technical Note
Authors: K. W. Iliff and L. W. Taylor, Jr.
Report Number: NASA-TN-D-6579
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A modified Newton-Raphson or quasilinearization minimization technique for determining stability derivatives from flight data was developed and compared with simple-equations, analog-matching, least-squares, and Shinbrot methods of analysis. For the data analyzed, the solutions computed by using the estimates obtained from the Newton-Raphson technique fit the data and determined coefficients adequately. A further modification to include a priori information was found to be useful. A model statistically similar to the flight data was analyzed using the same methods (excluding analog matching), and the Newton-Raphson technique was found to yield superior estimates. An approximate Cramer-Rao bound was compared with the error covariance matrix of the model and was found to provide information about the reliability of the individual estimates obtained. The technique was successfully applied to data obtained from a light airplane, a large supersonic
airplane, and a lifting body vehicle. It was shown that the reliability of the estimates of a given coefficient obtained from these vehicles depends upon the data analyzed.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 59
Availability:
Format(s) on-line:
PDF (2,208 KBytes)
Report Date: March 1972
No. Pages: 59
Keywords: Aircraft control; Aircraft stability; Flight tests; Newton-Raphson method; Mathematical models; Matrices (mathematics); Optimization; Regression analysis
- ANALYSIS OF AN ELECTROHYDRAULIC AIRCRAFT CONTROL SURFACE SERVO AND COMPARISON WITH TEST RESULTS , Technical Note
Authors: J. W. Edwards
Report Number: NASA-TN-D-6928
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An analysis of an electrohydraulic aircraft control-surface system is made in which the system is modeled as a lumped, two-mass, spring-coupled system controlled by a servo valve. Both linear and nonlinear models are developed, and the effects of hinge-moment loading are included. Transfer functions of the system and approximate literal factors of the transfer functions for several cases are presented. The damping action of dynamic pressure feedback is analyzed. Comparisons of the model responses with results from tests made on a highly resonant rudder control-surface servo indicate the adequacy of the model. The effects of variations in hinge-moment loading are illustrated.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (2,480 KBytes)
Report Date: August 1972
No. Pages: 74
Keywords: Aerodynamic configurations; Aircraft control; Control surfaces; Flight control; Hydraulic equipment; Linear systems; Nonlinear systems; Systems analysis
- LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF LIGHT, TWIN-ENGINE, PROPELLER-DRIVEN AIRPLANES , Technical Note
Authors: C. H. Wolowicz and R. B. Yancey
Report Number: NASA-TN-D-6800
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Representative state-of-the-art analytical procedures and design data for predicting the longitudinal static and dynamic stability and control characteristics of light, propeller-driven airplanes are presented. Procedures for predicting drag characteristics are also included. The procedures are applied to a twin-engine, propeller-driven airplane in the clean configuration from zero lift to stall conditions. The calculated characteristics are compared with wind-tunnel and flight data. Included in the comparisons are level-flight trim characteristics, period and damping of the short-period oscillatory mode, and windup-turn characteristics. All calculations are documented.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (12,838 KBytes)
Report Date: June 1972
No. Pages: 371
Keywords: Aircraft configurations; Aircraft control; Aircraft stability; Fixed wings; Aerodynamic characteristics; Aircraft performance; Performance prediciton
- FLIGHT-DETERMINED CHARACTERISTICS OF AN AIR INTAKE SYSTEM ON AN F-111A AIRPLANE , Technical Note
Authors: D. L. Hughes, J. k. Holzman and H. J. Johnson
Report Number: NASA-TN-D-6679
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flow phenomena of the F-111A air intake system were investigated over a large range of Mach number, altitude, and angle of attack. Boundary-layer variations are shown for the fuselage splitter plate and inlet entrance stations. Inlet performance is shown in terms of pressure recovery, airflow, mass-flow ratio, turbulence factor, distortion factor, and power spectral density. The fuselage boundary layer was found to be not completely removed from the upper portion of the splitter plate at all Mach numbers investigated. Inlet boundary-layer ingestion started at approximately Mach 1.6 near the translating spike and cone. Pressure-recovery distribution at the compressor face showed increasing distortion with increasing angle of attack and increasing Mach number. The time-averaged distortion-factor value approached 1300, which is near the distortion tolerance of the engine at Mach numbers above 2.1.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (2,638 KBytes)
Report Date: March 1972
No. Pages: 66
Keywords: Aerodynamic characteristics; F-111 aircraft; Flight tests; Inlet flow; Supersonic speed
- STATISTICAL SURVEY OF XB-70 AIRPLANE RESPONSES AND CONTROL USAGE WITH AN ILLUSTRATION OFTHE APPLICATION TO HANDLING QUALITIES CRITERIA , Technical Note
Authors: B. G. Powers
Report Number: NASA-TN-D-6872
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The magnitude and frequency of occurrence of aircraft responses and control inputs during 27 flights of the XB-70 airplane were measured. Exceedance curves are presented for the airplane responses and control usage. A technique is presented which makes use of these exceedance curves to establish or verify handling qualities criteria. This technique can provide a means of incorporating current operational experience in handling qualities requirements for future aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,211 KBytes)
Report Date: July 1972
No. Pages: 42
Keywords: Aircraft control; B-70 aircraft; Controllability; Statistical analysis; Delta wings; Flight characteristics; Operations research
- FLIGHT CALIBRATION OF COMPENSATED AND UNCOMPENSATED PITOT-STATIC AIRSPEED PROBES AND APPLICATION OF THE PROBES TO SUPERSONIC CRUISE VEHICLES , Technical Note
Authors: L. D. Webb and H. P. Washington
Report Number: NASA-TN-D-6827
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Static pressure position error calibrations for a compensated and an uncompensated XB-70 nose boom pitot static probe were obtained in flight. The methods (Pacer, acceleration-deceleration, and total temperature) used to obtain the position errors over a Mach number range from 0.5 to 3.0 and an altitude range from 25,000 feet to 70,000 feet are discussed. The error calibrations are compared with the position error determined from wind tunnel tests, theoretical analysis, and a standard NACA pitot static probe. Factors which influence position errors, such as angle of attack, Reynolds number, probe tip geometry, static orifice location, and probe shape, are discussed. Also included are examples showing how the uncertainties caused by position errors can affect the inlet controls and vertical altitude separation of a supersonic transport.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (2,578 KBytes)
Report Date: May 1972
No. Pages: 43
Keywords: B-70 aircraft; Pitot tubes; Position errors; Static pressure; Angle of attack; Calibrating; Reynolds number
- FLIGHT MEASUREMENTS O BUFFET CHARACTERISTICS OF THE F-104 AIRPLANE FOR SELECTED WING-FLAP DEFLECTIONS , Technical Note
Authors: E. L. Friend and W. J. Sefic
Report Number: NASA-TN-D-6943
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight program was conducted on the F-104 airplane to investigate the effects of moderate deflections of wing leading- and trailing-edge flaps on the buffet characteristics at subsonic and transonic Mach numbers. Selected deflections of the wing leading and trailing-edge flaps, individually and in combination, were used to assess buffet onset, intensity, and frequency; lift curves; and wing-rock characteristics for each configuration. Increased deflection of the trailing-edge flap delayed the buffet onset and buffet intensity rise to a significantly higher airplane normal-force coefficient. Deflection of the leading-edge flap produced some delay in buffet onset and the resulting intensity rise at low subsonic speeds. Increased deflection of the trailing-edge flap provided appreciable lift increments in the angle-of-attack range covered, whereas the leading-edge flap provided lift increments only at high angles-of-attack. The pilots appreciated the
increased maneuvering envelope provided by the flaps because of the improved turn capability.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,374 KBytes)
Report Date: August 1972
No. Pages: 49
Keywords: Aerodynamic characteristics; Buffeting; F-104 aircraft; Subsonic speed; Transonic speed
- FLIGHT-TEST RESULTS FROM TWO TOTAL TEMPERATURE PROBES FOR AIR-DATA MEASUREMENTS UP TO 2014 K (3625R) , Technical Note
Authors: J. Nugent, G. M. Sakamoto and L. D. Webb
Report Number: NASA-TN-D-6748
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An experimental temperature probe package containing a fluidic oscillator temperature probe and a shielded thermocouple temperature probe was tested during several X-15 flights. The X-15 flights provided greatly varying test conditions, including a wide range of rapidly changing total temperatures and Mach numbers which extended from subsonic to hypersonic speeds. Within restricted ranges of free-stream Mach number, free-stream unit weight flow, and local stagnation pressure, both probes yielded ramp outputs of temperature parallel to ramp inputs of free-stream total temperature. Within these ranges both probes were used to determine total temperature in the Mach 6 temperature environment. Because ambient temperature was known, both probes were used to estimate velocity and Mach number.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 35
Availability:
Currently this document is not available on-line.
From the NTRS FAQ: Where do I go for a hardcopy of the report?
Report Date: March 1972
No. Pages: 53
Keywords: Temperature measuring instruments; Thermocouples; X-15 aircraft; Aircraft equipment; Flight tests; Temperature probes
- EXPLORATORY FLIGHT INVESTIGATION OF AIRCRAFT RESPONSE TO THE WING VORTEX WAKE GENERATED BY JET TRANSPORT AIRCRAFT , Technical Note
Authors: W. H. Andrews, G. H. Robinson and R. R. Larson
Report Number: NASA-TN-D-6655
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The effect of intercepting wing tip vortices generated by large jet transports, including jumbo jets, over separation distances from 1 nautical mile to 15 nautical miles is evaluated on the basis of the response of a vortex probe airplane in the roil mode. The vortex probe test aircraft included a representative general aviation airplane, an executive jet, a fighter, and light and medium weight jet transports. The test conditions and airplane configurations were comparable to those normally used during takeoff, landing, or holding pattern operations. For flight safety the tests were performed at altitudes from 9500 feet to 12,500 feet. In addition to an evaluation of the probe airplane response, a flight test technique is suggested for determining minimum separation distance, using as variable the ratio of vortex-induced roll acceleration to maximum lateral control acceleration and the gross weight of the generating aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,234 KBytes)
Report Date: March 1972
No. Pages: 33
Keywords: Aircraft wakes; General aviation aircraft; Transport aircraft; Turbulent wakes; Vortices
- LOW-LIFT-TO-DRAG-RATIO APPROACH AND LANDING STUDIES USING A CV-990 AIRPLANE , Technical Note
Authors: B. M. Kock, F. L. Fulton and F. J. Drinkwater, III
Report Number: NASA-TN-D-6732
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The results are presented of a flight-test program utilizing a CV-990 airplane, flow in low-lift-to-drag-ratio (L/D) configurations, to simulate terminal area operation, approach, and landing of large unpowered vehicles. The results indicate that unpowered approaches and landings are practical with vehicles of the size and performance characteristics of the proposed shuttle vehicle. Low L/D landings provided touchdown dispersion patterns acceptable for operation on runways of reasonable length. The dispersion pattern was reduced when guidance was used during the final approach. High levels of pilot proficiency were not required for acceptable performance.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
Format(s) on-line:
PDF (1,761 KBytes)
Report Date: March 1972
No. Pages: 47
Keywords: Approach; CV-990 aircraft; Landing; Lift drag ratio; Space shuttles
- EXPERIMENTAL INVESTIGATION OF MACH 3 CRUISE HEATING SIMULATIONS ON A REPRESENTATIVE WING STRUCTURE FOR FLIGHT LOADS MEASUREMENT , Technical Note
Authors: R. A. Fields, F. V. Olinger and R. C. Momaghan
Report Number: NASA-TN-D-6749
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Radiant heating experiments were performed in the laboratory on an instrumented multispar wing structure to investigate: (1) how accurately the structural temperatures of a Mach 3 cruise-flight profile could be simulated, (2) what the effects of the heating and heating inaccuracies would be on the responses of strain-gage bridges installed on the structure, and (3) how these responses would affect flight loads measurements. Test temperatures throughout the structure agreed well with temperatures calculated for a Mach 3 profile. In addition, temperatures produced by two identical tests were repeatable to less than + or -6 K deg. Thermally induced strain-gage-bridge responses were large enough to be detrimental to a high-speed flight loads program with a goal of establishing aerodynamic loads (exclusive of thermal loads). It was shown that heating simulation can be used effectively for thermal calibration (that is, to provide corrections for a
high-temperature environment), and that thermal calibration may not be needed if the simulation data are used to carefully select bridges and load equations.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 39
Availability:
Format(s) on-line:
PDF (1,755 KBytes)
Report Date: March 1972
No. Pages: 42
Keywords: Aerodynamic heating; Flight load recorders; Wing planforms; X-15 aircraft
- IN-FLIGHT PILOT EVALUATIONS OF THE FLYING QUALITIES OF A FOUR-ENGINE JET TRANSPORT , Technical Note
Authors: E. C. Holleman and G. B. Gilyard
Report Number: NASA-TN-D-6811
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The flying qualities of the CV-990 jet transport were evaluated over the normal operating flight envelope and in smooth air to provide baseline data for transport airplanes. Pilot ratings of airplane handling characteristics for specific test conditions and configurations from approach to normal cruise were compared with various flying qualities criteria. In general, the CV-990 flying qualities were evaluated as satisfactory, and the evaluations supported transport flying qualities criteria. The Dutch roll damping was rated more satisfactory than was predicted by the flying qualities criteria. The pilots found rudder coordination for the yaw generated during high roll rates very difficult. They preferred to control with roll and pitch controls and to use the yaw damper to provide the required rudder coordination.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Currently this document is not available on-line.
From the NTRS FAQ: Where do I go for a hardcopy of the report?
Report Date: May 1972
No. Pages: 54
Keywords: Aircraft performance; CV-990 aircraft; Flight tests; Transport aircraft; Aerodynamic characteristics; Aircraft control; Flight envelopes; Roll; Yaw
- GROUND AND FLIGHT TEST METHODS FOR DETERMINING LIMIT CYCLE AND STRUCTURAL RESONANCECHARACTERISTICS OF AIRCRAFT STABILITY AUGMENTATION SYSTEMS , Technical Note
Authors: W. D. Painter and G. J. Sitterle
Report Number: NASA-TN-D-6867
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Performance criteria and test techniques are applied to stability augmentation systems (SAS) during ground testing to predict objectionable limit cycles and preclude structural resonance during flight. Factors that give rise to these problems, means of suppressing their effects, trade-offs to be considered, and ground test methods that have been developed are discussed. SAS performance predicted on the basis of these tests is compared with flight data obtained from three lifting body vehicles and the X-15 research airplane. Limit cycle and structural resonance test criteria, based upon ground and flight experience and data, were successfully applied to these vehicles. The criteria used were: The limit cycle amplitude (SAS gain multiplied by peak-to-peak angular rate) shall not exceed 0.5 deg for the highest product of control power and SAS gain that will be used in flight; the maximum in-flight SAS gain should never exceed 50 percent of the value at
which a structural resonance can be sustained during ground test.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (954 KBytes)
Report Date: June 1972
No. Pages: 22
Keywords: Aircraft stability; Feedback control; Stability derivatives; Stabilization
- STATISTICAL ANALYSIS OF LANDING CONTACT CONDITIONS FOR THREE LIFTING BODY RESEARCH VEHICLES , Technical Note
Authors: R. R. Larson
Report Number: NASA-TN-D-6708
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The landing contact conditions for the HL-10, M2-F2/F3, and the X-24A lifting body vehicles are analyzed statistically for 81 landings. The landing contact parameters analyzed are true airspeed, peak normal acceleration at the center of gravity, roll angle, and roll velocity. Ground measurement parameters analyzed are lateral and longitudinal distance from intended touchdown, lateral distance from touchdown to full stop, and rollout distance. The results are presented in the form of histograms for frequency distributions and cumulative frequency distribution probability curves with a Pearson Type 3 curve fit for extrapolation purposes.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 15
Availability:
Format(s) on-line:
PDF (2,091 KBytes)
Report Date: March 1972
No. Pages: 33
Keywords: Landing loads; Lifting reentry vehicles; Statistical analysis
- FLIGHT-DETERMINED DERIVATIVES AND DYNAMIC CHARACTERISTICS OF THE CV-990 AIRPLANE , Technical Note
Authors: G. B. Gilyard
Report Number: NASA-TN-D-6777
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight-determined longitudinal and lateral-directional stability and control derivatives are presented for the CV-990 airplane for various combinations of Mach number, altitude, and flap setting throughout the flight envelope up to a Mach number of 0.87. Also presented are the dynamic characteristics of the aircraft calculated from the flight-obtained derivatives and the measured phugoid characteristics. The derivative characteristics were obtained from flight records of longitudinal and lateral-directional transient oscillation maneuvers by using a modified Newton-Raphson digital derivative determination technique. Generally the derivatives exhibited consistent variation with lift coefficient in the low-speed data and with Mach number and altitude in the high-speed data. Many also varied with flap deflection, notably spoiler effectiveness and directional stability.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (2,219 KBytes)
Report Date: May 1972
No. Pages: 67
Keywords: Aerodynamic configurations; Flight envelopes; Stability derivatives; Subsonic speed
- LATERAL-DIRECTIONAL AERODYNAMIC CHARACTERISTICS OF LIGHT, TWIN-ENGINE, PROPELLER-DRIVEN AIRPLANES , Technical Note
Authors: C. H. Wolowicz and R. B. Yancey
Report Number: NASA-TN-D-6946
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Analytical procedures and design data for predicting the lateral-directional static and dynamic stability and control characteristics of light, twin engine, propeller driven airplanes for propeller-off and power-on conditions are reported. Although the consideration of power effects is limited to twin engine airplanes, the propeller-off considerations are applicable to single engine airplanes as well. The procedures are applied to a twin engine, propeller driven, semi-low-wing airplane in the clean configuration through the linear lift range. The calculated derivative characteristics are compared with wind tunnel and flight data. Included in the calculated characteristics are the spiral mode, roll mode, and Dutch roll mode over the speed range of the airplane.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (9,129 KBytes)
Report Date: October 1972
No. Pages: 293
Keywords: Aerodynamic characteristics; Lateral stability; Light aircraft; Performance prediction
- WIND TUNNEL MEASUREMENTS OF SURFACE PRESSURE FLUCTUATIONS AT MACH NUMBERS OF 1.6, 2.0,AND 2.5 USING 12 DIFFERENT TRANSDUCERS , Technical Note
Authors: T. L. Lewis and J. B. Dods, Jr.
Report Number: NASA-TN-D-7087
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The turbulent boundary layer on the wall of a 9 by 7 foot wind tunnel was measured with 12 different transducers at Mach numbers of 1.6, 2.0, and 2.5. The results indicated that the wall surface-pressure-fluctuation field was more homogeneous at a Mach number of 2.5 than at Mach numbers of 1.6 or 2.0. A comparison of power-spectral-density data at Mach 2.5 with a summary of similar data (Mach 0.1 to 3.45) showed good agreement. The measurement uncertainty was greatest when frequencies were low and the surface-pressure-fluctuation field was homogeneous. The uncertainty at higher frequencies increased as the surface-pressure-fluctuation field became more inhomogeneous. Since transducer mounting effects and system noise levels were determined not to have contributed appreciably to measurement uncertainties, the result was attributed to an interaction between the surface-pressure-fluctuation field and the transducers. Corcos' correction for size effects
improved the comparison between transducers at the high frequencies, but did not eliminate an apparent size effect at the lower frequencies.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 35
Availability:
Format(s) on-line:
PDF (1,664 KBytes)
Report Date: October 1972
No. Pages: 51
Keywords: Pressure pulses; Supersonic boundary layers; Transducers; Wind tunnel walls; Aerodynamic noise; Dynamic response
- FLIGHT-DETERMINED DERIVATIVES AND DYNAMIC CHARACTERISTICS FOR THE HL-10 LIFTING BODY VEHICLE ATSUBSONIC AND TRANSONIC MACH NUMBERS , Technical Note
Authors: L. W. Strutz
Report Number: NASA-TN-D-6934
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The HL-10 lifting body stability and control derivatives were determined by using an analog-matching technique and compared with derivatives obtained from wind-tunnel results. The flight derivatives were determined as a function of angle of attack for a subsonic configuration at Mach 0.7 and for a transonic configuration at Mach 0.7, 0.9, and 1.2. At an angle of attack of 14 deg, data were obtained for a Mach number range from 0.6 to 1.4. The flight and wind-tunnel derivatives were in general agreement, with the possible exception of the longitudinal and lateral damping derivatives. Some differences were noted between the vehicle dynamic response characteristics calculated from flight-determined derivatives and those predicted by the wind-tunnel results. However, the only difference the pilots noted between the response of the vehicle in flight and the response of a simulator programed with wind-tunnel-predicted data was that the damping generally
was higher in the flight vehicle.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 15
Availability:
Currently this document is not available on-line.
From the NTRS FAQ: Where do I go for a hardcopy of the report?
Report Date: September 1972
No. Pages: 78
Keywords: Aerodynamic characteristics; HL-10 reentry vehicel; Wind tunnel stability tests; Aircraft control; Correlation; Data acquisition; Stability derivatives
- FLIGHT INVESTIGATION OF THE ROLL REQUIREMENTS FOR TRANSPORT AIRPLANES IN THE LANDING APPROACH , Technical Note
Authors: E. C. Holleman and B. G. Powers
Report Number: NASA-TN-D-7062
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An in-flight evaluation of transport roll characteristics in the landing approach was made with a general purpose airborne simulator. The evaluation task consisted of an instrument approach with a visual correction for a (200-foot) lateral offset. Pilot evaluations and ratings were obtained for approaches made at 140 knots and 180 knots indicated airspeed with variations of wheel characteristics, maximum roll rate, and roll time constant.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Format(s) on-line:
PDF (1,663 KBytes)
Report Date: October 1972
No. Pages: 50
Keywords: Aircraft landing; Aircraft stability; Lateral oscillation; Transport aircraft; Aircraft control; Aircraft performance; Flight simulators; Lateral control
- A FLIGHT EVALUATION OF METHODS FOR PREDICTING VORTEX WAKE EFFECTS ON TRAILING AIRCRAFT , Technical Note
Authors: G. H. Robinson and R. R. Larson
Report Number: NASA-TN-D-6904
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The results of four current analytical methods for predicting wing vortex strength and decay rate are compared with the results of a flight investigation of the wake characteristics of several large jet transport aircraft. An empirical expression defining the strength and decay rate of wake vortices is developed that best represents most of the flight-test data. However, the expression is not applicable to small aircraft that would be immersed in the vortex wake of large aircraft.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
Currently this document is not available on-line.
From the NTRS FAQ: Where do I go for a hardcopy of the report?
Report Date: November 1972
No. Pages: 60
Keywords: Aircraft wakes; Vortices; Wing tips; Aerodynamic charactertistics; Flight tests; Jet aircraft; Mathematical models; Transport aircraft
|
