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 (A).

AH 79-K-132/20 to AH 93-K-131/15

Page 3 of 5 1 2 3 4 5 Next

(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah79k135-il) AH 79-K-135/20 B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-135/20 airfoil for use with flaps (K) Max thickness 13.5% at 40.2% chord Max camber 3.1% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah79k143-il) AH 79-K-143/18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-143/18 airfoil for use with flaps (K) Max thickness 14.3% at 40.2% chord Max camber 2.9% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah80129-il) AH 80-129		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord Max camber 4.1% at 43.5% chord Source UIUC Airfoil Coordinates Database
(ah80136-il) AH 80-136		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord Max camber 3.4% at 33.9% chord Source UIUC Airfoil Coordinates Database

(ah80140-il) AH 80-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord Source UIUC Airfoil Coordinates Database
(ah81131-il) AH 81-131		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord Max camber 2.8% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah81k144-il) AH 81-K-144/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-K-144/17 airfoil for use with flaps (K) Max thickness 14.5% at 40.2% chord Max camber 4.2% at 46.7% chord Source UIUC Airfoil Coordinates Database
(ah81k144wfklappe-il) AH 81-K-144 W-F KLAPPE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-K-144 W-F KLAPPE airfoil for use with flaps (K) Max thickness 22% at 17% chord Max camber 1.1% at 56.5% chord Source UIUC Airfoil Coordinates Database
(ah82150a-il) AH 82-150 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Source UIUC Airfoil Coordinates Database
(ah82150f-il) AH 82-150 F		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 F airfoil Max thickness 15% at 43.5% chord Max camber 3.6% at 46.7% chord Source UIUC Airfoil Coordinates Database
(ah83150q-il) AH 83-150 Q		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-150 Q airfoil Max thickness 15% at 40.2% chord Max camber 4.1% at 37.1% chord Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Source UIUC Airfoil Coordinates Database

(ah85l120-il) AH 85-L-120/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(ah88k130-il) AH 88-K-130/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Source UIUC Airfoil Coordinates Database
(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Source UIUC Airfoil Coordinates Database
(ah93156-il) AH 93-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord Source UIUC Airfoil Coordinates Database
(ah93157-il) AH 93-157		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-157 airfoil Max thickness 15.7% at 39.6% chord Max camber 3.5% at 41.7% chord Source UIUC Airfoil Coordinates Database
(ah93k130-il) AH 93-K-130/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-130/15 airfoil for use with flaps (K) Max thickness 13.1% at 42% chord Max camber 3.5% at 42% chord Source UIUC Airfoil Coordinates Database
(ah93k131-il) AH 93-K-131/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord Source UIUC Airfoil Coordinates Database