-
1
-
-
0012314391
-
Experimental surface pressure data obtained on 65° delta wing across Reynolds number and Mach number ranges
-
Chu J, Luckring JM (1996) Experimental surface pressure data obtained on 65° delta wing across Reynolds number and Mach number ranges, NASA TM 4645
-
(1996)
NASA TM
, vol.4645
-
-
Chu, J.1
Luckring, J.M.2
-
3
-
-
33845423357
-
Effects of boundary layer formation on the vortical flow above Slender Delta Wings
-
RTO specialists' meeting on enhancement of NATO military flight vehicle performance by management of interacting boundary layer transition and separation, Prague, Czech Republic, 4-7 October 2004
-
Hummel D (2004) Effects of boundary layer formation on the vortical flow above Slender Delta Wings, RTO specialists' meeting on enhancement of NATO military flight vehicle performance by management of interacting boundary layer transition and separation, Prague, Czech Republic, 4-7 October 2004, Meeting Proceedings RTO-MP-AVT-111, pp 30-1 to 30-22
-
(2004)
Meeting Proceedings RTO-MP-AVT-111
-
-
Hummel, D.1
-
5
-
-
33845403580
-
A new vortex flow experiment for computer code validation
-
RTO AVT symposium on vortex flow and high angle of attack aerodynamics, Loen, 7-11 May 2001 SYA 8-1 to 8-31
-
Hummel D, Redeker G (2003) A new vortex flow experiment for computer code validation, RTO AVT symposium on vortex flow and high angle of attack aerodynamics, Loen, 7-11 May 2001, Meeting Proceedings RTO-MP-069 (I), SYA 8-1 to 8-31
-
(2003)
Meeting Proceedings RTO-MP-069 (I)
-
-
Hummel, D.1
Redeker, G.2
-
6
-
-
24144448605
-
Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel
-
Klein C, Engler RH, Henne U, Sachs W (2005) Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel. Exp Fluids 39:475-483
-
(2005)
Exp Fluids
, vol.39
, pp. 475-483
-
-
Klein, C.1
Engler, R.H.2
Henne, U.3
Sachs, W.4
-
7
-
-
33845444295
-
Development of PSP technique for application on the VFE-2 65° delta wing configuration in sub- and transonic flow
-
Klein C, Sachs W, Henne U, Engler RH, Wiedemann A, Konrath R (2006) Development of PSP technique for application on the VFE-2 65° delta wing configuration in sub- and transonic flow, AIAA-Paper 2006-0059
-
(2006)
AIAA-Paper 2006-0059
-
-
Klein, C.1
Sachs, W.2
Henne, U.3
Engler, R.H.4
Wiedemann, A.5
Konrath, R.6
-
8
-
-
34250759802
-
Analysis of PSP results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speed
-
Konrath R, Klein C, Engler RH, Otter D (2006a) Analysis of PSP results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speed, AIAA-Paper 2006-0060
-
(2006)
AIAA-Paper 2006-0060
-
-
Konrath, R.1
Klein, C.2
Engler, R.H.3
Otter, D.4
-
9
-
-
33845428022
-
Analysis of PIV results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speeds
-
Konrath R, Schröder A, Kompenhans J (2006b) Analysis of PIV results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speeds, AIAA-Paper 2006-3003
-
(2006)
AIAA-Paper 2006-3003
-
-
Konrath, R.1
Schröder, A.2
Kompenhans, J.3
-
10
-
-
2942715250
-
Compressibility and leading-edge bluntness effects for a 65° delta-wing
-
Luckring JM (2004a) Compressibility and leading-edge bluntness effects for a 65° delta-wing. AIAA Paper 2004-0765
-
(2004)
AIAA Paper 2004-0765
-
-
Luckring, J.M.1
-
11
-
-
78149428493
-
Reynolds number, compressibility, and leading-edge bluntness effects on delta-wing aerodynamics
-
Paper 4.1.4
-
Luckring JM (2004b) Reynolds number, compressibility, and leading-edge bluntness effects on delta-wing aerodynamics, ICAS Proceedings, Paper 4.1.4
-
(2004)
ICAS Proceedings
-
-
Luckring, J.M.1
-
12
-
-
1642438233
-
Vortex investigations over a rolling delta wing model in transonic flow by stereo PIV measurements
-
Göttingen, 25-29 August, ISBN 03CH37501
-
Sammler B, Schröder A, Arnott A, Otter D, Agocs J, Kompenhans J (2003) Vortex investigations over a rolling delta wing model in transonic flow by stereo PIV measurements. In: 20th international congress on instrumentation in aerospace simulation facilities (ICIASF'03), Göttingen, 25-29 August, ISBN 03CH37501, pp 268-277
-
(2003)
20th International Congress on Instrumentation in Aerospace Simulation Facilities (ICIASF'03)
, pp. 268-277
-
-
Sammler, B.1
Schröder, A.2
Arnott, A.3
Otter, D.4
Agocs, J.5
Kompenhans, J.6
-
13
-
-
0036144446
-
Iterative image deformation methods in PIV
-
Scarano F (2002) Iterative image deformation methods in PIV. Meas Sci Technol 13:R1-R19
-
(2002)
Meas Sci Technol
, vol.13
-
-
Scarano, F.1
-
15
-
-
33845416121
-
Application of stereo PIV to the VFE-2 65 delta wing configuration at sub- and transonic speeds
-
Schröder A, Agocs J, Frahnert H, Otter D, Mattner H, Kompenhans J, Konrath R (2006) Application of stereo PIV to the VFE-2 65 delta wing configuration at sub- and transonic speeds, AIAA-Paper 2006-3486
-
(2006)
AIAA-Paper 2006-3486
-
-
Schröder, A.1
Agocs, J.2
Frahnert, H.3
Otter, D.4
Mattner, H.5
Kompenhans, J.6
Konrath, R.7
-
17
-
-
0031354164
-
Stereoscopic digital particle image velocimetry for application in wind tunnel flows
-
Willert C (1997) Stereoscopic digital particle image velocimetry for application in wind tunnel flows. Meas Sci Technol 8:1465-1479
-
(1997)
Meas Sci Technol
, vol.8
, pp. 1465-1479
-
-
Willert, C.1
|