Add p01 and make filenames and dir names consistent

Makefile

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+all:
+	+$(MAKE) -C p01
+	+$(MAKE) -C p14

p01/Makefile

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+all:
+	make p01.out
+
+p01.out: p01.f
+	gfortran p01.f -o p01.out
+
+clean:
+	-rm *.out *.DAT

p01/p01.f

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+C     PROGRAM No. 1: GRID GENERATOR FOR 2-D AIRFOILS
+C     ----------------------------------------------
+
+C     THIS PROGRAM IS AN AUTOMATED COMPLEX AIRFOIL TRANSFORMATION OF THE
+C     TYPE PRESENTED BY VAN DE VOOREN AND DE JONG (1970). THE RESULTING
+C     AIRFOIL MAY HAVE A NON-ZERO TRAILING EDGE ANGLE. THIS FORMULATION
+C     IS FOR NON-CAMBERED AIRFOILS ONLY (PROGRAMMED BY STEVEN YON, 1989).
+      OPEN(8,FILE='AFOIL2.DAT',STATUS='NEW')
+      OPEN(10,FILE='CP.DAT',STATUS='NEW')
+      WRITE(6,*) 'READY TO START VAN DE VOOREN TRANSFORMATION'
+      WRITE(6,*) 'ENTER THICKNESS COEFF. E'
+      READ(5,*) E
+      WRITE(6,*) 'ENTER T.E. ANGLE COEFF. K'
+      READ(5,*) AK
+      TL=1.0
+      A=2*TL*(E+1)**(AK-1)/(2**AK)
+      WRITE(6,*) 'ENTER THE ANGLE OF ATTACK IN DEGREES'
+      READ(5,*) ALPHA
+      AL=ALPHA/57.2958
+      WRITE(6,*) 'ENTER NUMBER OF AIRFOIL PANELS, M'
+      WRITE(6,*) 'WITH WHICH TO MODEL THE AIRFOIL'
+      WRITE(6,*)
+     * '(NOTE THAT M SHOULD BE AN EVEN FACTOR OF 360)'
+      READ(5,*) M
+      ITHETA=360/M
+
+C     THE DO LOOP WILL RUN THROUGH THE CIRCLE PLANE WITH
+C     THE SPECIFIED ANGULAR INTERVAL AND TRANSFORM EACH
+C     POINT TO THE AIRFOIL PLANE
+      DO I=0,360,ITHETA
+        IF(I.EQ.0.OR.I.EQ.360) THEN
+          X=1
+          Y=0
+          CP=1
+          WRITE(8,*) X,' ,',Y
+          IF(AK.EQ.2.AND.I.EQ.0) GOTO 25
+          IF(AK.EQ.2.AND.I.EQ.360) GOTO 25
+          WRITE(10,*) X,' ,',CP
+25    CONTINUE
+          GOTO 100
+        ELSE
+          GOTO 50
+        END IF
+
+50    CONTINUE
+        TH=I/57.2958
+        R1=SQRT((A*(COS(TH)-1))**2+(A*SIN(TH))**2)
+        R2=SQRT((A*(COS(TH)-E))**2+(A*SIN(TH))**2)
+        IF(TH.EQ.0) THEN
+          TH1=1.5708
+        ELSE
+          TH1=(ATAN((A*SIN(TH))/(A*(COS(TH)-1))))+3.1415927
+        END IF
+        IF(COS(TH)-E.LT.0.AND.SIN(TH).GT.0) THEN
+          TH2=(ATAN((A*SIN(TH))/(A*(COS(TH)-E))))+3.1415927
+        ELSE IF(COS(TH)-E.LT.0.AND.SIN(TH).LT.0) THEN
+          TH2=(ATAN((A*SIN(TH))/(A*(COS(TH)-E))))+3.1415927
+        ELSE IF(COS(TH)-E.GT.0.AND.SIN(TH).LT.0) THEN
+          TH2=(ATAN((A*SIN(TH))/(A*(COS(TH)-E))))+2*3.1415927
+        ELSE
+          TH2=(ATAN((A*SIN(TH))/(A*(COS(TH)-E))))
+        END IF
+
+C       THIS PART COMPUTES THE TRANSFORMED POSITIONS
+        COM1=((R1**AK)/(R2**(AK-1)))/((COS((AK-1)
+     *    *TH2))**2+(SIN((AK-1)*TH2))**2)
+        X=COM1*(COS(AK*TH1)*COS((AK-1)*TH2)
+     *    +SIN(AK*TH1)*SIN((AK-1)*TH2))+TL
+        Y=COM1*(SIN(AK*TH1)*COS((AK-1)*TH2)
+     *    -COS(AK*TH1)*SIN((AK-1)*TH2))
+
+        WRITE(8,*) X,' ,',Y
+C       THIS PART COMPUTES THE TRANSFORMED PRESSURE
+C       DISTRIBUTION
+        A1=COS((AK-1)*TH1)*COS(AK*TH2)+SIN((AK-1)*TH1)*SIN(AK*TH2)
+        B1=SIN((AK-1)*TH1)*COS(AK*TH2)-COS((AK-1)*TH1)*SIN(AK*TH2)
+        C1=(COS(AK*TH2))**2+(SIN(AK*TH2))**2
+        P=A*(1-AK+AK*E)
+        D1=A1*(A*COS(TH)-P)-B1*A*SIN(TH)
+        D2=A1*A*SIN(TH)+B1*(A*COS(TH)-P)
+
+        TEMP=2*C1*(SIN(AL)-SIN(AL-TH))/(D1**2+D2**2)
+        COM2=TEMP*(R2**AK)/(R1**(AK-1))
+        VX=D1*SIN(TH)+D2*COS(TH)
+        VY=-(D1*COS(TH)-D2*SIN(TH))
+        CP=1-COM2**2*(VX**2+VY**2)
+        WRITE(10,*) X,' ,',CP
+
+100     CONTINUE
+      END DO
+      CLOSE(8)
+      CLOSE(10)
+      STOP
+      END

p14/Makefile

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+all:
+	make p14.out
+
+p14.out: p14.f surface.dat
+	gfortran p14.f -o p14.out
+
+clean:
+	rm *.out