5x5F (5x5F.dat) v2022-0915 Simulation Date: 09/22/2022 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE. THAT RESTS AGAINST THE LOWER SURFACE. SWEEP IS DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 1.3099 0.4603 5.0000 5.0000 4.6744 0.1354 0.1586 31.2787 0.0730 0.0222 -0.0102 -0.0494 -0.1050 1.3399 0.4551 5.0000 5.0000 4.6910 0.1332 0.1556 30.7056 0.0708 0.0214 -0.0153 -0.0504 -0.1075 1.3700 0.4495 5.0000 5.0000 4.7046 0.1309 0.1532 30.1512 0.0689 0.0206 -0.0205 -0.0516 -0.1103 1.4001 0.4435 5.0000 5.0000 4.7149 0.1284 0.1512 29.6121 0.0670 0.0199 -0.0257 -0.0526 -0.1134 1.4412 0.4347 5.0000 5.0000 4.7289 0.1248 0.1486 28.9061 0.0646 0.0190 -0.0329 -0.0542 -0.1180 1.4971 0.4219 5.0000 5.0000 4.7486 0.1195 0.1453 27.9932 0.0613 0.0179 -0.0429 -0.0563 -0.1247 1.5547 0.4077 5.0000 5.0000 4.7713 0.1137 0.1421 27.1054 0.0579 0.0168 -0.0534 -0.0584 -0.1321 1.6125 0.3926 5.0000 5.0000 4.7970 0.1074 0.1392 26.2672 0.0546 0.0157 -0.0640 -0.0602 -0.1396 1.6702 0.3767 5.0000 5.0000 4.8251 0.1008 0.1365 25.4758 0.0514 0.0145 -0.0748 -0.0619 -0.1472 1.7279 0.3602 5.0000 5.0000 4.8538 0.0939 0.1340 24.7279 0.0483 0.0133 -0.0859 -0.0633 -0.1545 1.7857 0.3433 5.0000 5.0000 4.8814 0.0866 0.1317 24.0200 0.0452 0.0120 -0.0970 -0.0644 -0.1617 1.8434 0.3262 5.0000 5.0000 4.9108 0.0791 0.1296 23.3493 0.0423 0.0108 -0.1084 -0.0653 -0.1686 1.9011 0.3088 5.0000 5.0000 4.9216 0.0714 0.1277 22.7132 0.0394 0.0096 -0.1199 -0.0662 -0.1758 1.9589 0.2915 5.0000 5.0000 4.9332 0.0635 0.1260 22.1091 0.0367 0.0084 -0.1317 -0.0672 -0.1833 2.0166 0.2743 5.0000 5.0000 4.9458 0.0554 0.1245 21.5348 0.0341 0.0074 -0.1436 -0.0683 -0.1913 2.0743 0.2574 5.0000 5.0000 4.9562 0.0472 0.1231 20.9882 0.0317 0.0065 -0.1558 -0.0696 -0.1998 2.1321 0.2409 5.0000 5.0000 4.9639 0.0388 0.1218 20.4676 0.0293 0.0057 -0.1682 -0.0711 -0.2088 2.1898 0.2250 5.0000 5.0000 4.9686 0.0304 0.1207 19.9711 0.0272 0.0049 -0.1809 -0.0729 -0.2184 2.2475 0.2098 5.0000 5.0000 4.9554 0.0220 0.1197 19.4972 0.0251 0.0043 -0.1939 -0.0750 -0.2286 2.3053 0.1955 5.0000 5.0000 4.8812 0.0136 0.1188 19.0445 0.0232 0.0037 -0.2070 -0.0774 -0.2392 2.3630 0.1822 5.0000 5.0000 4.7832 0.0052 0.1180 18.6116 0.0215 0.0032 -0.2204 -0.0801 -0.2503 2.4195 0.1633 5.0000 5.0000 4.6583 -0.0096 0.1173 18.2061 0.0192 0.0026 -0.2359 -0.0865 -0.2628 2.4593 0.1274 5.0000 5.0000 4.6663 -0.0422 0.1169 17.9305 0.0149 0.0016 -0.2547 -0.1028 -0.2758 2.4900 0.0472 5.0000 5.0000 5.5789 -0.1178 0.1166 17.7234 0.0055 0.0002 -0.2862 -0.1414 -0.2944 2.5000 0.0001 5.0000 5.0183 5.0162 -0.1626 0.1165 17.7174 0.0000 0.0000 -0.3016 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBTRA: 1.30 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.007210 TOTAL WEIGHT (Kg) = 0.003270 TOTAL VOLUME (IN**3) = 0.117460 TOTAL PROJECTED AREA (IN**2) = 1.0524 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000024 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003789 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 83.533 INNER LIMIT (NORMALIZED) = 0.378 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 115471.88 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.30, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.83, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412