![]() | TECHLAND RESEARCH INC |
28895 LORAIN RD STE-201 NORTH OLMSTED OH 44070-4042 UNITED STATES Telephone: 4407169077 |
TECHLAND RESEARCH INC is an Active Commercial Supplier with the Cage Code 1D2J5 and is tracked by Dun & Bradstreet under DUNS Number 967185414.
SIC Code 1: | 8731 |
Status: | A |
Type: | F |
Size: | A |
Primary Business: | N |
Type of Business: | N |
Woman Owned: | Y |
CAO: | S3605A |
ADP CNT CT: | HQ0337 |
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION CHECKOUT AND PLANNING: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE 3C EXTENSION AND PHASE 3D PLANNING EXTENSION
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::OT::IGF AERODYNAMIC TEST SUPPORT
1720: AIRCRAFT LAUNCHING EQUIPMENT
D: DEFINITIVE CONTRACT
IGF::OT::IGF INNOVATIVE METHOD FOR PARAMETRIC BLEED PATTERN VARIATION IN WIND TUNNEL MODELS
AC13: R&D- DEFENSE SYSTEM: AIRCRAFT (ADVANCED DEVELOPMENT)
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE 3C.
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE 3C.
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE 3C.
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE IIIB.
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::OT::IGF "INNOVATIVE METHODS FOR PARAMETRIC BLEED PATTERN VARIATION"
AC11: R&D- DEFENSE SYSTEM: AIRCRAFT (BASIC RESEARCH)
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE IIIB.
1720: AIRCRAFT LAUNCHING EQUIPMENT
B: PURCHASE ORDER
IGF::CL::IGF ENGINE INTEGRATION STRATEGIES: MODE TRANSITION IN A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM, PHASE IIIB.
1720: AIRCRAFT LAUNCHING EQUIPMENT
PO Purchase Order
IGF::OT::IGF AERODYNAMIC TEST SUPPORT
1720: AIRCRAFT LAUNCHING EQUIPMENT
PO Purchase Order
IGF::OT::IGF - LIQUIFIED BLEED SEEDLING FUND PROJ
AS12: R&D- MODAL TRANSPORTATION: AIR (APPLIED RESEARCH/EXPLORATORY DEVELOPMENT)
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D- OTHER RESEARCH AND DEVELOPMENT (BASIC RESEARCH)
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D- OTHER RESEARCH AND DEVELOPMENT (BASIC RESEARCH)
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D- SPACE: AERONAUTICS/SPACE TECHNOLOGY (ADVANCED DEVELOPMENT)
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D- SPACE: AERONAUTICS/SPACE TECHNOLOGY (ADVANCED DEVELOPMENT)
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D- SPACE: AERONAUTICS/SPACE TECHNOLOGY (ADVANCED DEVELOPMENT)
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D- OTHER RESEARCH AND DEVELOPMENT (BASIC RESEARCH)
DCA Definitive Contract
SBIR PHASE I TOPIC N121-028
AC61: R&D- DEFENSE SYSTEM: ELECTRONICS/COMMUNICATION EQUIPMENT (BASIC RESEARCH)
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D- OTHER RESEARCH AND DEVELOPMENT (BASIC RESEARCH)
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D- SPACE: AERONAUTICS/SPACE TECHNOLOGY (ADVANCED DEVELOPMENT)
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D-OTHER R & D-B RES
B: PURCHASE ORDER
NASA GLENN RESEARCH CENTER HAS AN INTEREST IN THE DEVELOPMENT OF NEW PROPULSION SYSTEM TECHNOLOGIES FOR APPLICATION TO FUTURE SUPERSONIC CRUISE CIVIL AIRCRAFT. IN ORDER TO BE ECONOMICALLY VIABLE, SUCH AIRCRAFT NEED TO ACHIEVE UNPRECEDENTED LEVELS OF CRUISE EFFICIENCY, WHILE ALSO MEETING STRINGENT AIRPORT NOISE REQUIREMENTS AT TAKEOFF AND LANDING AND MINIMIZING THE AIRCRAFT S SONIC BOOM SIGNATURE. THE PROPULSION SYSTEM MUST BE DESIGNED AS AN INTEGRATED SYSTEM AND INSTALLED IN AN OPTIMAL WAY ON THE AIRFRAME. THE SUPERSONIC INLET IS A CRITICAL COMPONENT OF AN EFFICIENT SUPERSONIC CRUISE PROPULSION SYSTEM. THE INLET DESIGNER MUST CONSIDER THE ENTIRE PROPULSION SYSTEM AND AIRCRAFT INTEGRATION STRATEGY TO DEVELOP AN INLET THAT NOT ONLY ACHIEVES HIGH PERFORMANCE AT CRUISE CONDITIONS, BUT ALSO MAINTAINS STABILITY AND OPERABILITY THROUGHOUT THE ENTIRE FLIGHT ENVELOPE, FROM TAKEOFF TO CRUISE TO LANDING. INLET PERFORMANCE METRICS INCLUDE TOTAL PRESSURE RECOVERY AND AMOUNT AND DISTORTION LEVELS OF MASS-FLOW DELIVERED TO THE ENGINE. OPERABILITY CONSIDERATIONS INCLUDE TERMINAL SHOCK STABILITY (FOR MIXED-COMPRESSION INLETS), BUZZ RESISTANCE, AND TOLERANCE TO CHANGES IN ANGLE-OF-ATTACK AND MACH NUMBER. SATISFYING EACH OF THESE REQUIREMENTS NECESSITATES THE INTEGRATION OF VARIABLE GEOMETRY, STABILITY BLEED, OVERBOARD BYPASS, AND INLET CONTROL SYSTEMS. IN ADDITION, THE FINAL CONFIGURATION MUST INTEGRATE WITH THE AIRFRAME IN SUCH A WAY AS TO MINIMIZE THE SONIC BOOM SIGNATURE OF THE OVERALL AIRCRAFT. NEW TECHNOLOGIES ARE EMERGING THAT MAY HAVE SIGNIFICANT IMPACTS ON THE DESIGN OF FUTURE SUPERSONIC INLETS. TECHLAND RESEARCH, INC. HAS BEEN CENTRAL TO THE DEVELOPMENT OF SOME OF THESE. NASA GRC HAS AN INTEREST IN FUNDING TECHLAND TO HELP GUIDE THE DEVELOPMENT OF TWO OF THESE TECHNOLOGIES THROUGH TEST DEMONSTRATION. BACKGROUND TECHLAND RESEARCH, INC. AERODYNAMICALLY DESIGNED, ANALYZED, AND FABRICATED RESEARCH HARDWARE FOR A PATENTED AXISYMMETRIC INLET CONCEPT UNDER PHASE I AND PHASE II SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) CONTRACTS (NAS3-98041, NAS4-00011, AND NAS4-01031). THE FIRST SBIR CONTRACT (WITH NASA GLENN RESEARCH CENTER) WAS A DESIGN AND FEASIBILITY STUDY THAT DEMONSTRATED THE POTENTIAL ADVANTAGES OF A UNIQUE AXISYMMETRIC INLET CONCEPT OVER STATE-OF-THE-ART INLET CONFIGURATIONS TYPICALLY IDENTIFIED FOR SUPERSONIC TRANSPORT AIRCRAFT APPLICATIONS. THE MIXED-COMPRESSION INLET CONCEPT WAS UNIQUE IN ITS UTILIZATION OF AN INNOVATIVE VARIABLE GEOMETRY SYSTEM TO FACILITATE ENGINE AIRFLOW MATCHING AT OFF-DESIGN FLIGHT CONDITIONS. THE TRANSLATING CHANNELED CENTERBODY (TCCB) CONCEPT PROVIDES FOR THE OPENING OF LONGITUDINAL CHANNELS IN THE CENTERBODY WITH CENTERBODY TRANSLATION. THE VARIABLE GEOMETRY IS RELATIVELY SIMPLE TO EFFECT, REQUIRING NO ADDITIONAL ACTUATION SYSTEMS, AND OFFERS EQUIVALENT LEVELS OF INLET STABILITY AND OPERABILITY AS CONCEPTS WITH SIGNIFICANTLY MORE COMPLEX VARIABLE GEOMETRY SCHEMES, SUCH AS THE VARIABLE DIAMETER CENTERBODY (VDC). THE NASA DFRC PHASE I AND PHASE II SBIR EFFORTS FOCUSED ON THE DEVELOPMENT OF AN AERODYNAMIC DESIGN THAT, WHEN OPERATED AT OFF-DESIGN (MACH 1.5) CONDITIONS, WOULD SUPPLY AIRFLOW TO A DFRC-DESIGNED DUCTED ROCKET ENGINE IN SUPPORT OF ROCKET-BASED COMBINED CYCLE (RBCC) RESEARCH. THE INLET AND ENGINE HARDWARE WERE TO BE TESTED ON THE F-15B PROPULSION FLIGHT TEST FACILITY (PFTF). TWO INLET CONFIGURATIONS WERE DESIGNED: ONE WHICH REPRESENTED THE CHANNELED CENTERBODY CONFIGURATION TO PROVIDE INCREASED AIRFLOW AT LOW-SUPERSONIC MACH NUMBER CONDITIONS, AND A SMOOTH CENTERBODY CONFIGURATION WITH AN EQUIVALENT AREA DISTRIBUTION TO THAT OF THE CHANNELED CONFIGURATION. THE EFFORT INCLUDED 3-DIMENSIONAL COMPUTATIONAL FLUID DYNAMICS (CFD) ANALYSES OF BOTH THE SMOOTH AND CHANNELED CENTERBODY CONFIGURATIONS AT FREESTREAM MACH NUMBERS OF 1.5 AND 1.7, AND AT SEVERAL INLET BACKPRESSURES (REPRESENTING SEVERAL ENGINE AIRFLOW CONDITIONS). TECHLAND FABRICATED INLET MODEL HARDWARE PER ME
AB91: R&D-OTHER SVC & DEVELOP-B RES
DCA Definitive Contract
MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D-AERO & SPACE TECH-ADV DEV
B: PURCHASE ORDER
NASA GLENN RESEARCH CENTER HAS AN INTEREST IN THE DEVELOPMENT OF NEW PROPULSION SYSTEM TECHNOLOGIES FOR APPLICATION TO FUTURE SUPERSONIC CRUISE CIVIL AIRCRAFT. IN ORDER TO BE ECONOMICALLY VIABLE, SUCH AIRCRAFT NEED TO ACHIEVE UNPRECEDENTED LEVELS OF CRUISE EFFICIENCY, WHILE ALSO MEETING STRINGENT AIRPORT NOISE REQUIREMENTS AT TAKEOFF AND LANDING AND MINIMIZING THE AIRCRAFT S SONIC BOOM SIGNATURE. THE PROPULSION SYSTEM MUST BE DESIGNED AS AN INTEGRATED SYSTEM AND INSTALLED IN AN OPTIMAL WAY ON THE AIRFRAME. THE SUPERSONIC INLET IS A CRITICAL COMPONENT OF AN EFFICIENT SUPERSONIC CRUISE PROPULSION SYSTEM. THE INLET DESIGNER MUST CONSIDER THE ENTIRE PROPULSION SYSTEM AND AIRCRAFT INTEGRATION STRATEGY TO DEVELOP AN INLET THAT NOT ONLY ACHIEVES HIGH PERFORMANCE AT CRUISE CONDITIONS, BUT ALSO MAINTAINS STABILITY AND OPERABILITY THROUGHOUT THE ENTIRE FLIGHT ENVELOPE, FROM TAKEOFF TO CRUISE TO LANDING. INLET PERFORMANCE METRICS INCLUDE TOTAL PRESSURE RECOVERY AND AMOUNT AND DISTORTION LEVELS OF MASS-FLOW DELIVERED TO THE ENGINE. OPERABILITY CONSIDERATIONS INCLUDE TERMINAL SHOCK STABILITY (FOR MIXED-COMPRESSION INLETS), BUZZ RESISTANCE, AND TOLERANCE TO CHANGES IN ANGLE-OF-ATTACK AND MACH NUMBER. SATISFYING EACH OF THESE REQUIREMENTS NECESSITATES THE INTEGRATION OF VARIABLE GEOMETRY, STABILITY BLEED, OVERBOARD BYPASS, AND INLET CONTROL SYSTEMS. IN ADDITION, THE FINAL CONFIGURATION MUST INTEGRATE WITH THE AIRFRAME IN SUCH A WAY AS TO MINIMIZE THE SONIC BOOM SIGNATURE OF THE OVERALL AIRCRAFT. NEW TECHNOLOGIES ARE EMERGING THAT MAY HAVE SIGNIFICANT IMPACTS ON THE DESIGN OF FUTURE SUPERSONIC INLETS. TECHLAND RESEARCH, INC. HAS BEEN CENTRAL TO THE DEVELOPMENT OF SOME OF THESE. NASA GRC HAS AN INTEREST IN FUNDING TECHLAND TO HELP GUIDE THE DEVELOPMENT OF TWO OF THESE TECHNOLOGIES THROUGH TEST DEMONSTRATION. BACKGROUND TECHLAND RESEARCH, INC. AERODYNAMICALLY DESIGNED, ANALYZED, AND FABRICATED RESEARCH HARDWARE FOR A PATENTED AXISYMMETRIC INLET CONCEPT UNDER PHASE I AND PHASE II SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) CONTRACTS (NAS3-98041, NAS4-00011, AND NAS4-01031). THE FIRST SBIR CONTRACT (WITH NASA GLENN RESEARCH CENTER) WAS A DESIGN AND FEASIBILITY STUDY THAT DEMONSTRATED THE POTENTIAL ADVANTAGES OF A UNIQUE AXISYMMETRIC INLET CONCEPT OVER STATE-OF-THE-ART INLET CONFIGURATIONS TYPICALLY IDENTIFIED FOR SUPERSONIC TRANSPORT AIRCRAFT APPLICATIONS. THE MIXED-COMPRESSION INLET CONCEPT WAS UNIQUE IN ITS UTILIZATION OF AN INNOVATIVE VARIABLE GEOMETRY SYSTEM TO FACILITATE ENGINE AIRFLOW MATCHING AT OFF-DESIGN FLIGHT CONDITIONS. THE TRANSLATING CHANNELED CENTERBODY (TCCB) CONCEPT PROVIDES FOR THE OPENING OF LONGITUDINAL CHANNELS IN THE CENTERBODY WITH CENTERBODY TRANSLATION. THE VARIABLE GEOMETRY IS RELATIVELY SIMPLE TO EFFECT, REQUIRING NO ADDITIONAL ACTUATION SYSTEMS, AND OFFERS EQUIVALENT LEVELS OF INLET STABILITY AND OPERABILITY AS CONCEPTS WITH SIGNIFICANTLY MORE COMPLEX VARIABLE GEOMETRY SCHEMES, SUCH AS THE VARIABLE DIAMETER CENTERBODY (VDC). THE NASA DFRC PHASE I AND PHASE II SBIR EFFORTS FOCUSED ON THE DEVELOPMENT OF AN AERODYNAMIC DESIGN THAT, WHEN OPERATED AT OFF-DESIGN (MACH 1.5) CONDITIONS, WOULD SUPPLY AIRFLOW TO A DFRC-DESIGNED DUCTED ROCKET ENGINE IN SUPPORT OF ROCKET-BASED COMBINED CYCLE (RBCC) RESEARCH. THE INLET AND ENGINE HARDWARE WERE TO BE TESTED ON THE F-15B PROPULSION FLIGHT TEST FACILITY (PFTF). TWO INLET CONFIGURATIONS WERE DESIGNED: ONE WHICH REPRESENTED THE CHANNELED CENTERBODY CONFIGURATION TO PROVIDE INCREASED AIRFLOW AT LOW-SUPERSONIC MACH NUMBER CONDITIONS, AND A SMOOTH CENTERBODY CONFIGURATION WITH AN EQUIVALENT AREA DISTRIBUTION TO THAT OF THE CHANNELED CONFIGURATION. THE EFFORT INCLUDED 3-DIMENSIONAL COMPUTATIONAL FLUID DYNAMICS (CFD) ANALYSES OF BOTH THE SMOOTH AND CHANNELED CENTERBODY CONFIGURATIONS AT FREESTREAM MACH NUMBERS OF 1.5 AND 1.7, AND AT SEVERAL INLET BACKPRESSURES (REPRESENTING SEVERAL ENGINE AIRFLOW CONDITIONS). TECHLAND FABRICATED INLET MODEL HARDWARE PER ME
AB91: R&D-OTHER SVC & DEVELOP-B RES
DCA Definitive Contract
ADVANCED FLOW CONTROL TECHNOLOGY DEMONSTRATION IN THE NASA GRC 40-60 MIXED-COMPRESSION INLET
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
OPTION 2 TO EXTEND THE RESEARCH FOR MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
MOD 7 - MODIFY OPTION #4 WORK TO CHANGE SPECS
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
MOD 6 - EXERCISE OPTION #4 & EXTEND PERIOD OF PERFORMANCE THRU 3/1/10
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200228676
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
MOD 5 - CORRECTS FUNDING ERROR ON MOD 4, AND ADDS FUNDS TO FULLY FUND THE CONTRACT THROUGH 11/09
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200222353
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200222353
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200222353
AR13: R&D-AERO & SPACE TECH-ADV DEV
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200228676 MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM: THE PRIMARY OBJECTIVE OF THE WORK EFFORT IS TO INVESTIGATE AND DEVELOP METHODS OF MODE TRANSITIONING FOR A DUAL MODE HYPERSONIC AIRBREATHING PROPULSION SYSTEM. WIND TUNNEL TESTING WILL BE CONDUCTED OF A TBCC PROPULSION SYSTEM WITH A SINGLE INTEGRATED INLET SUPPLYING BOTH A TURBINE-BASED LOW SPEED ENGINE AND A DUAL-MODE SCRAMJET HIGH-SPEED ENGINE. THIS WILL BE ACCOMPLISHED THROUGH A SERIES OF EXPERIMENTAL TESTING EFFORTS ON A LARGE-SCALE RESEARCH MODEL. THE TEST SERIES INCLUDES INLET DEVELOPMENT TESTING; CONTROLS DEVELOPMENT TESTING AND MODE TRANSITIONING WITH AN INTEGRATED PROPULSION SYSTEM INCLUDING ENGINES. THE RESEARCH MODEL IS TO BE TESTED IN THE GRC 10X10 SUPERSONIC WIND TUNNEL
AZ11: R&D-OTHER R & D-B RES
IDC Indefinite Delivery Contract
AERONAUTIC RESEARCH
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200222353
AR13: R&D-AERO & SPACE TECH-ADV DEV
DO Delivery Order
DESIGN & FABRICATION 15X15CM HARDWARE
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200228676 MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM: THE PRIMARY OBJECTIVE OF THE WORK EFFORT IS TO INVESTIGATE AND DEVELOP METHODS OF MODE TRANSITIONING FOR A DUAL MODE HYPERSONIC AIRBREATHING PROPULSION SYSTEM. WIND TUNNEL TESTING WILL BE CONDUCTED OF A TBCC PROPULSION SYSTEM WITH A SINGLE INTEGRATED INLET SUPPLYING BOTH A TURBINE-BASED LOW SPEED ENGINE AND A DUAL-MODE SCRAMJET HIGH-SPEED ENGINE. THIS WILL BE ACCOMPLISHED THROUGH A SERIES OF EXPERIMENTAL TESTING EFFORTS ON A LARGE-SCALE RESEARCH MODEL. THE TEST SERIES INCLUDES INLET DEVELOPMENT TESTING; CONTROLS DEVELOPMENT TESTING AND MODE TRANSITIONING WITH AN INTEGRATED PROPULSION SYSTEM INCLUDING ENGINES. THE RESEARCH MODEL IS TO BE TESTED IN THE GRC 10X10 SUPERSONIC WIND TUNNEL
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200228676 MODE TRANSITIONING FOR A DUAL-FLOW TURBINE-BASED COMBINED CYCLE HYPERSONIC PROPULSION SYSTEM: THE PRIMARY OBJECTIVE OF THE WORK EFFORT IS TO INVESTIGATE AND DEVELOP METHODS OF MODE TRANSITIONING FOR A DUAL MODE HYPERSONIC AIRBREATHING PROPULSION SYSTEM. WIND TUNNEL TESTING WILL BE CONDUCTED OF A TBCC PROPULSION SYSTEM WITH A SINGLE INTEGRATED INLET SUPPLYING BOTH A TURBINE-BASED LOW SPEED ENGINE AND A DUAL-MODE SCRAMJET HIGH-SPEED ENGINE. THIS WILL BE ACCOMPLISHED THROUGH A SERIES OF EXPERIMENTAL TESTING EFFORTS ON A LARGE-SCALE RESEARCH MODEL. THE TEST SERIES INCLUDES INLET DEVELOPMENT TESTING; CONTROLS DEVELOPMENT TESTING AND MODE TRANSITIONING WITH AN INTEGRATED PROPULSION SYSTEM INCLUDING ENGINES. THE RESEARCH MODEL IS TO BE TESTED IN THE GRC 10X10 SUPERSONIC WIND TUNNEL
AZ11: R&D-OTHER R & D-B RES
DCA Definitive Contract
SAP PURCHASE REQUISITION: 4200222353
AR13: R&D-AERO & SPACE TECH-ADV DEV
IDC Indefinite Delivery Contract
AERONAUTIC RESEARCH
DO Delivery Order
DESIGN & FABRICATION 15X15CM HARDWARE
AR11: R&D-AERO & SPACE TECH-B RES
DO Delivery Order
ORDER AGAINST OUTLINE AGREEMENT NAS3-03110
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DO Delivery Order
ORDER AGAINST OUTLINE AGREEMENT NAS3-03110
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DCA Definitive Contract
TURBINE RESEARCH
AR26: R&D-SPACE SCIENCE & APPL-MGMT SUP
DCA Definitive Contract
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
PO Purchase Order
ENGINERRING SUPPORT FOR TURBINE ACCELERATOR INLET ANALYSIS
AR26: R&D-SPACE SCIENCE & APPL-MGMT SUP
DCA Definitive Contract
TURBINE RESEARCH
AR26: R&D-SPACE SCIENCE & APPL-MGMT SUP
PO Purchase Order
ENGINERRING SUPPORT FOR TURBINE ACCELERATOR INLET ANALYSIS
AR26: R&D-SPACE SCIENCE & APPL-MGMT SUP
DCA Definitive Contract
SBIR PHASE I - MODE TRANSITION VARIABLE GEOMETRY FOR HIGH SPEED INLETS FOR HYPERSONIC AIRCRAFT
AS11: AIR TRANSPORTATION (BASIC)
DCA Definitive Contract
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DCA Definitive Contract
AC16: R&D-AIRCRAFT-MGMT SUP
PO Purchase Order
INLT SYSTEMS DESIGN
AR21: R&D-SPACE SCIENCE & APPL-B RES
PO Purchase Order
TO 4 AGANIST OUTLINE AGREEMENT NAS3-03110
AR21: R&D-SPACE SCIENCE & APPL-B RES
DCA Definitive Contract
SBIR 99-1 PHASE 11 FLIGHT TESTING OF A NEW DESIGN CONCEPT FOR AXISYMMETRIZ INLETS
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DCA Definitive Contract
AC16: R&D-AIRCRAFT-MGMT SUP
PO Purchase Order
TECHNICAL CONTRACTOR REPORT ON THE RESULTS OF AN E XPERIMENTAL PROGRAM ON A LARGE SCALE MACH 5, INLE
AR21: R&D-SPACE SCIENCE & APPL-B RES
PO Purchase Order
INLT SYSTEMS DESIGN
AR21: R&D-SPACE SCIENCE & APPL-B RES
IDC Indefinite Delivery Contract
AERONAUTIC RESEARCH
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
PO Purchase Order
AC16: R&D-AIRCRAFT-MGMT SUP
PO Purchase Order
AR23: R&D-SPACE SCIENCE & APPL-ADV DEV
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
PO Purchase Order
AR23: R&D-SPACE SCIENCE & APPL-ADV DEV
DCA Definitive Contract
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
PO Purchase Order
AR23: R&D-SPACE SCIENCE & APPL-ADV DEV
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR12: R&D-AERO & SPACE TECH-A RES/EXPL DE
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
PO Purchase Order
AR11: R&D-AERO & SPACE TECH-B RES
PO Purchase Order
AR31: SPACE FLIGHT (BASIC)
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES
DCA Definitive Contract
AR11: R&D-AERO & SPACE TECH-B RES