Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database list (G).

GOE 177 AIRFOIL to GOE 228 (MVA H.38) AIRFOIL

Page 4 of 21 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Next

(goe177-il) GOE 177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database
(goe178-il) GOE 178 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 178 airfoil Max thickness 8.5% at 30% chord Max camber 4.4% at 30% chord Source UIUC Airfoil Coordinates Database
(goe180-il) GOE 180 (MVA H.26) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 180 (MVA H.26) airfoil Max thickness 8.7% at 30% chord Max camber 4.4% at 40% chord Source UIUC Airfoil Coordinates Database
(goe182-il) GOE 182 (MVA H.27) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 182 (MVA H.27) airfoil Max thickness 9.5% at 19.9% chord Max camber 5.3% at 39.9% chord Source UIUC Airfoil Coordinates Database
(goe184-il) GOE 184 (MVA H.29) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 184 (MVA H.29) airfoil Max thickness 8.3% at 19.9% chord Max camber 5.3% at 39.9% chord Source UIUC Airfoil Coordinates Database

(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 187 (Schatte-Lanz 2U10) airfoil Max thickness 8.3% at 30% chord Max camber 4.8% at 30% chord Source UIUC Airfoil Coordinates Database
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord Source UIUC Airfoil Coordinates Database
(goe190-il) GOE 190 (MVA MK.18) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord Source UIUC Airfoil Coordinates Database
(goe195-il) GOE 195 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 195 airfoil Max thickness 8.6% at 20% chord Max camber 5.1% at 50% chord Source UIUC Airfoil Coordinates Database
(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 198 (L.F.G. 5294) airfoil Max thickness 7.8% at 19.9% chord Max camber 6.5% at 39.9% chord Source UIUC Airfoil Coordinates Database
(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord Max camber 5.2% at 30% chord Source UIUC Airfoil Coordinates Database
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 207 (AVIATIK V8) airfoil Max thickness 8.8% at 19.9% chord Max camber 6.6% at 29.9% chord Source UIUC Airfoil Coordinates Database
(goe210-il) GOE 210 (DAIMLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% at 30% chord Max camber 4.3% at 40% chord Source UIUC Airfoil Coordinates Database

(goe217-il) GOE 217 (MVA MK.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord Source UIUC Airfoil Coordinates Database
(goe222-il) GOE 222 (MVA H.33) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord Max camber 7.2% at 49.2% chord Source UIUC Airfoil Coordinates Database
(goe223-il) GOE 223 (MVA H.34) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord Max camber 5.7% at 49.1% chord Source UIUC Airfoil Coordinates Database
(goe225-il) GOE 225 (MVA H.35) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 225 (MVA H.35) airfoil Max thickness 12.8% at 19.7% chord Max camber 7.6% at 49.7% chord Source UIUC Airfoil Coordinates Database
(goe226-il) GOE 226 (MVA H.36) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord Source UIUC Airfoil Coordinates Database
(goe227-il) GOE 227 (MVA H.37) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord Source UIUC Airfoil Coordinates Database
(goe228-il) GOE 228 (MVA H.38) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord Source UIUC Airfoil Coordinates Database