PL422991A1 - Device for testing aerodynamic forces - Google Patents
Device for testing aerodynamic forcesInfo
- Publication number
- PL422991A1 PL422991A1 PL422991A PL42299117A PL422991A1 PL 422991 A1 PL422991 A1 PL 422991A1 PL 422991 A PL422991 A PL 422991A PL 42299117 A PL42299117 A PL 42299117A PL 422991 A1 PL422991 A1 PL 422991A1
- Authority
- PL
- Poland
- Prior art keywords
- crank
- axial part
- sleeve
- screw
- cylindrical cap
- Prior art date
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Toys (AREA)
Abstract
Przedmiotem wynalazku jest przyrząd do badania sił aerodynamicznych przeznaczony do zastosowań w laboratoriach fizycznych i do celów edukacyjnych. Przyrząd zawiera korbę z częścią osiową (1), przechodzącą przez tulejkę (2), której końce stykają się ze sprężystymi pierścieniami (3, 4), korzystnie typu Segera, wciśniętymi w rowki osadcze, znajdujące się na osiowej części korby (1). Górny koniec osiowej części korby (1), zaopatrzony jest we współosiową, walcową nasadkę (5) z otworem, przez który przechodzi sprężysta rurka (6), prostopadła do osiowej części korby (1) i zamocowana śrubą (7), wkręconą w walcową nasadkę (5), przy czym odcinki sprężystej rurki (6) po obu stronach walcowej nasadki (5) mają różne długości. Na końcu dłuższego odcinka sprężystej rurki (6) umieszczane są wymienne, lekkie kształtki (8) o profilu, np. tarczy kołowej, kropli lub fragmentu płata skrzydła samolotu, wykonane korzystnie jako zamknięte powłoki i zaopatrzone w przelotowy otwór oraz tulejkę z prostopadłą do niej śrubą. Na krótszym odcinku sprężystej rurki (6) umieszczony jest obciążnik (11), zaopatrzony w przelotowy otwór i prostopadłą do niego śrubę. Odsadzona część korby (13) przechodzi również przez tulejkę (14), której końce stykają się ze sprężystymi pierścieniami (15, 16), wciśniętymi w rowki osadcze znajdujące się na odsadzonej części korby (13).The present invention relates to an aerodynamic force testing device intended for use in physical laboratories and for educational purposes. The device comprises a crank with an axial part (1) passing through the sleeve (2), the ends of which are in contact with elastic rings (3, 4), preferably of the Seger type, pressed into the slots located on the axial part of the crank (1). The upper end of the axial part of the crank (1) is provided with a coaxial cylindrical cap (5) with an opening through which the elastic tube (6) passes, perpendicular to the axial part of the crank (1) and fixed with a screw (7) screwed into the cylindrical cap (5), the sections of the elastic tube (6) on both sides of the cylindrical cap (5) having different lengths. At the end of the longer section of the flexible tube (6), replaceable, lightweight fittings (8) with a profile, e.g. a circular disk, droplet or fragment of the plane's wing, are placed, preferably made as closed shells and equipped with a through hole and a sleeve with a perpendicular screw . On the shorter section of the elastic tube (6) there is a weight (11) fitted with a through hole and a screw perpendicular to it. The offset portion of the crank (13) also passes through the sleeve (14), the ends of which come into contact with the spring rings (15, 16) pressed into the receiving grooves located on the offset portion of the crank (13).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL422991A PL233132B1 (en) | 2017-09-28 | 2017-09-28 | Device for testing aerodynamic forces |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL422991A PL233132B1 (en) | 2017-09-28 | 2017-09-28 | Device for testing aerodynamic forces |
Publications (2)
Publication Number | Publication Date |
---|---|
PL422991A1 true PL422991A1 (en) | 2019-04-08 |
PL233132B1 PL233132B1 (en) | 2019-09-30 |
Family
ID=65992042
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PL422991A PL233132B1 (en) | 2017-09-28 | 2017-09-28 | Device for testing aerodynamic forces |
Country Status (1)
Country | Link |
---|---|
PL (1) | PL233132B1 (en) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20020092348A1 (en) * | 1999-11-26 | 2002-07-18 | Richard J. Ulman | Apparatus and method for measuring forces and moments acting on models tested in aerodynamic wind tunnels |
DE10228482A1 (en) * | 2002-06-26 | 2004-01-15 | Hill, Bernd, Prof. Dr. | Lifting force and flow resistance measurement device for measuring such force and resistance in aerodynamic models has a moving base plate to support a vertical floor-mounted column with a lever |
CN103065527A (en) * | 2012-12-21 | 2013-04-24 | 中国航空工业空气动力研究院 | Aerodynamic lift demonstration device |
-
2017
- 2017-09-28 PL PL422991A patent/PL233132B1/en unknown
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20020092348A1 (en) * | 1999-11-26 | 2002-07-18 | Richard J. Ulman | Apparatus and method for measuring forces and moments acting on models tested in aerodynamic wind tunnels |
DE10228482A1 (en) * | 2002-06-26 | 2004-01-15 | Hill, Bernd, Prof. Dr. | Lifting force and flow resistance measurement device for measuring such force and resistance in aerodynamic models has a moving base plate to support a vertical floor-mounted column with a lever |
CN103065527A (en) * | 2012-12-21 | 2013-04-24 | 中国航空工业空气动力研究院 | Aerodynamic lift demonstration device |
Also Published As
Publication number | Publication date |
---|---|
PL233132B1 (en) | 2019-09-30 |
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