9x5F (9x5F.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) 1.7089 0.8746 5.0000 5.0000 4.5495 0.2687 0.1485 24.9698 0.1299 0.0688 0.3439 -0.0721 0.2059 1.7591 0.8762 5.0000 5.0000 4.5581 0.2684 0.1460 24.3409 0.1279 0.0678 0.3366 -0.0740 0.2015 1.8093 0.8770 5.0000 5.0000 4.5660 0.2679 0.1436 23.7410 0.1259 0.0669 0.3292 -0.0759 0.1969 1.8595 0.8767 5.0000 5.0000 4.5733 0.2670 0.1413 23.1684 0.1239 0.0659 0.3216 -0.0778 0.1920 1.9097 0.8755 5.0000 5.0000 4.5800 0.2658 0.1392 22.6214 0.1219 0.0650 0.3140 -0.0798 0.1868 1.9601 0.8735 5.0000 5.0000 4.5862 0.2644 0.1372 22.0968 0.1198 0.0641 0.3062 -0.0819 0.1814 2.0393 0.8684 5.0000 5.0000 4.5949 0.2616 0.1343 21.3170 0.1166 0.0627 0.2938 -0.0853 0.1725 2.1374 0.8594 5.0000 5.0000 4.6054 0.2572 0.1310 20.4212 0.1126 0.0609 0.2781 -0.0896 0.1608 2.2357 0.8475 5.0000 5.0000 4.6162 0.2518 0.1282 19.5926 0.1087 0.0591 0.2619 -0.0939 0.1485 2.3340 0.8329 5.0000 5.0000 4.6266 0.2454 0.1257 18.8264 0.1047 0.0572 0.2455 -0.0981 0.1357 2.4324 0.8158 5.0000 5.0000 4.6357 0.2383 0.1236 18.1159 0.1008 0.0551 0.2288 -0.1020 0.1226 2.5307 0.7964 5.0000 5.0000 4.6437 0.2303 0.1218 17.4554 0.0970 0.0529 0.2117 -0.1055 0.1093 2.6291 0.7751 5.0000 5.0000 4.6506 0.2215 0.1202 16.8400 0.0932 0.0505 0.1945 -0.1085 0.0958 2.7274 0.7519 5.0000 5.0000 4.6563 0.2120 0.1189 16.2655 0.0894 0.0479 0.1770 -0.1110 0.0822 2.8258 0.7272 5.0000 5.0000 4.6598 0.2018 0.1178 15.7279 0.0856 0.0451 0.1594 -0.1130 0.0686 2.9241 0.7011 5.0000 5.0000 4.6582 0.1910 0.1168 15.2238 0.0819 0.0421 0.1415 -0.1145 0.0550 3.0225 0.6739 5.0000 5.0000 4.6487 0.1797 0.1160 14.7504 0.0782 0.0391 0.1236 -0.1156 0.0415 3.1208 0.6458 5.0000 5.0000 4.6384 0.1678 0.1154 14.3049 0.0745 0.0360 0.1055 -0.1163 0.0279 3.2192 0.6169 5.0000 5.0000 4.6284 0.1554 0.1148 13.8851 0.0708 0.0328 0.0873 -0.1168 0.0144 3.3175 0.5877 5.0000 5.0000 4.6182 0.1426 0.1142 13.4887 0.0671 0.0297 0.0691 -0.1170 0.0009 3.4159 0.5581 5.0000 5.0000 4.6082 0.1295 0.1137 13.1140 0.0635 0.0267 0.0508 -0.1174 -0.0127 3.5142 0.5286 5.0000 5.0000 4.5982 0.1160 0.1132 12.7591 0.0598 0.0238 0.0325 -0.1180 -0.0266 3.6126 0.4993 5.0000 5.0000 4.5884 0.1023 0.1126 12.4227 0.0562 0.0212 0.0142 -0.1190 -0.0407 3.7109 0.4704 5.0000 5.0000 4.5787 0.0883 0.1119 12.1033 0.0527 0.0187 -0.0040 -0.1203 -0.0549 3.8093 0.4421 5.0000 5.0000 4.5692 0.0741 0.1112 11.7997 0.0492 0.0164 -0.0222 -0.1221 -0.0692 3.9076 0.4147 5.0000 5.0000 4.5601 0.0599 0.1103 11.5108 0.0457 0.0144 -0.0403 -0.1243 -0.0837 4.0060 0.3884 5.0000 5.0000 4.5513 0.0455 0.1092 11.2354 0.0424 0.0125 -0.0583 -0.1270 -0.0983 4.1043 0.3635 5.0000 5.0000 4.5261 0.0311 0.1079 10.9728 0.0392 0.0108 -0.0766 -0.1304 -0.1134 4.2026 0.3400 5.0000 5.0000 4.4680 0.0168 0.1064 10.7221 0.0362 0.0094 -0.0953 -0.1343 -0.1292 4.3010 0.3172 5.0000 5.0000 4.1909 0.0014 0.1046 10.4824 0.0332 0.0080 -0.1144 -0.1396 -0.1458 4.3922 0.2650 5.0000 5.0000 3.7671 -0.0450 0.1027 10.2694 0.0272 0.0055 -0.1392 -0.1629 -0.1654 4.4499 0.1880 5.0000 5.0000 3.4946 -0.1186 0.1013 10.1389 0.0191 0.0028 -0.1638 -0.2024 -0.1825 4.5000 0.0140 5.0000 5.0111 5.0111 -0.2886 0.1001 10.0503 0.0014 0.0000 -0.2054 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBTRA: 1.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.022408 TOTAL WEIGHT (Kg) = 0.010162 TOTAL VOLUME (IN**3) = 0.365051 TOTAL PROJECTED AREA (IN**2) = 4.0486 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000280 MOMENT OF INERTIA (Kg-M**2) = 0.000032 STATIC MOMENT, ONE SIDE (IN-LB) = 0.022561 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 = 85.956 INNER LIMIT (NORMALIZED) = 0.254 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 49218.42 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.70, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.29, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412