13x7F (13x7F.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) 1.7080 1.1403 7.0000 7.0000 6.2912 0.3633 0.1691 33.1147 0.1929 0.1294 0.3675 -0.0477 0.1427 1.7783 1.1596 7.0000 7.0000 6.3447 0.3679 0.1611 32.0662 0.1869 0.1279 0.3610 -0.0537 0.1396 1.8486 1.1771 7.0000 7.0000 6.3927 0.3721 0.1540 31.0755 0.1812 0.1263 0.3544 -0.0595 0.1364 1.9189 1.1928 7.0000 7.0000 6.4358 0.3757 0.1476 30.1386 0.1760 0.1249 0.3476 -0.0652 0.1331 1.9892 1.2069 7.0000 7.0000 6.4732 0.3788 0.1420 29.2516 0.1714 0.1236 0.3407 -0.0707 0.1295 2.0595 1.2193 7.0000 7.0000 6.5051 0.3815 0.1373 28.4111 0.1674 0.1226 0.3336 -0.0760 0.1258 2.1298 1.2302 7.0000 7.0000 6.5310 0.3837 0.1333 27.6139 0.1640 0.1219 0.3264 -0.0813 0.1218 2.2206 1.2419 7.0000 7.0000 6.5555 0.3858 0.1293 26.6435 0.1606 0.1215 0.3169 -0.0878 0.1162 2.3591 1.2549 7.0000 7.0000 6.5875 0.3877 0.1242 25.2788 0.1559 0.1207 0.3020 -0.0975 0.1070 2.4984 1.2623 7.0000 7.0000 6.6177 0.3878 0.1196 24.0327 0.1510 0.1195 0.2865 -0.1067 0.0972 2.6378 1.2644 7.0000 7.0000 6.6451 0.3863 0.1155 22.8973 0.1460 0.1178 0.2706 -0.1155 0.0869 2.7771 1.2615 7.0000 7.0000 6.6692 0.3833 0.1119 21.8593 0.1411 0.1157 0.2543 -0.1237 0.0760 2.9164 1.2539 7.0000 7.0000 6.6893 0.3787 0.1087 20.9073 0.1363 0.1133 0.2376 -0.1314 0.0646 3.0557 1.2418 7.0000 7.0000 6.7039 0.3728 0.1060 20.0314 0.1316 0.1106 0.2205 -0.1384 0.0529 3.1950 1.2256 7.0000 7.0000 6.7117 0.3654 0.1036 19.2233 0.1270 0.1075 0.2031 -0.1447 0.0409 3.3343 1.2056 7.0000 7.0000 6.7077 0.3568 0.1016 18.4757 0.1225 0.1041 0.1854 -0.1503 0.0286 3.4737 1.1821 7.0000 7.0000 6.6988 0.3470 0.0999 17.7823 0.1181 0.1004 0.1674 -0.1551 0.0161 3.6130 1.1554 7.0000 7.0000 6.6867 0.3359 0.0986 17.1375 0.1139 0.0963 0.1491 -0.1591 0.0035 3.7523 1.1258 7.0000 7.0000 6.6724 0.3238 0.0975 16.5366 0.1098 0.0920 0.1307 -0.1624 -0.0092 3.8916 1.0936 7.0000 7.0000 6.6568 0.3107 0.0967 15.9753 0.1057 0.0874 0.1120 -0.1650 -0.0220 4.0309 1.0591 7.0000 7.0000 6.6406 0.2966 0.0961 15.4500 0.1018 0.0826 0.0931 -0.1670 -0.0348 4.1702 1.0226 7.0000 7.0000 6.6246 0.2817 0.0957 14.9573 0.0978 0.0775 0.0741 -0.1684 -0.0476 4.3096 0.9845 7.0000 7.0000 6.6090 0.2659 0.0954 14.4945 0.0939 0.0723 0.0550 -0.1695 -0.0604 4.4489 0.9450 7.0000 7.0000 6.5946 0.2493 0.0953 14.0588 0.0900 0.0670 0.0358 -0.1701 -0.0732 4.5882 0.9044 7.0000 7.0000 6.5820 0.2321 0.0953 13.6482 0.0862 0.0616 0.0166 -0.1706 -0.0861 4.7275 0.8630 7.0000 7.0000 6.5714 0.2143 0.0953 13.2604 0.0823 0.0563 -0.0027 -0.1709 -0.0990 4.8668 0.8212 7.0000 7.0000 6.5624 0.1959 0.0954 12.8936 0.0784 0.0511 -0.0220 -0.1713 -0.1120 5.0061 0.7793 7.0000 7.0000 6.5543 0.1770 0.0956 12.5463 0.0745 0.0461 -0.0413 -0.1720 -0.1252 5.1455 0.7375 7.0000 7.0000 6.5472 0.1577 0.0957 12.2170 0.0706 0.0414 -0.0605 -0.1732 -0.1387 5.2848 0.6961 7.0000 7.0000 6.5414 0.1381 0.0957 11.9042 0.0667 0.0369 -0.0797 -0.1749 -0.1523 5.4241 0.6555 7.0000 7.0000 6.5371 0.1182 0.0958 11.6069 0.0628 0.0328 -0.0987 -0.1771 -0.1662 5.5634 0.6160 7.0000 7.0000 6.5347 0.0981 0.0957 11.3238 0.0589 0.0290 -0.1176 -0.1800 -0.1801 5.7027 0.5779 7.0000 7.0000 6.5343 0.0778 0.0955 11.0541 0.0552 0.0255 -0.1364 -0.1836 -0.1943 5.8420 0.5414 7.0000 7.0000 6.5360 0.0575 0.0951 10.7967 0.0515 0.0224 -0.1550 -0.1881 -0.2085 5.9814 0.5070 7.0000 7.0000 6.5402 0.0371 0.0945 10.5510 0.0479 0.0196 -0.1733 -0.1933 -0.2228 6.1207 0.4748 7.0000 7.0000 6.5182 0.0168 0.0938 10.3160 0.0445 0.0171 -0.1921 -0.1996 -0.2379 6.2548 0.4377 7.0000 7.0000 6.4133 -0.0110 0.0928 10.0994 0.0406 0.0145 -0.2132 -0.2110 -0.2553 6.3300 0.3918 7.0000 7.0000 6.2999 -0.0524 0.0922 9.9819 0.0361 0.0115 -0.2308 -0.2315 -0.2685 6.4000 0.3173 7.0000 7.0000 5.8232 -0.1230 0.0915 9.8749 0.0290 0.0075 -0.2536 -0.2677 -0.2842 6.4700 0.1343 7.0000 7.0000 5.5894 -0.3012 0.0907 9.7701 0.0122 0.0013 -0.2973 -0.3628 -0.3105 6.5000 0.0201 7.0000 7.0107 7.0107 -0.4132 0.0904 9.7405 0.0018 0.0000 -0.3222 0.0000 0.0000 RADIUS: 6.50 PROPELLER RADIUS (IN) HUBTRA: 1.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.056654 TOTAL WEIGHT (Kg) = 0.025693 TOTAL VOLUME (IN**3) = 0.922968 TOTAL PROJECTED AREA (IN**2) = 9.3403 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001502 MOMENT OF INERTIA (Kg-M**2) = 0.000170 STATIC MOMENT, ONE SIDE (IN-LB) = 0.082386 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 = 85.779 INNER LIMIT (NORMALIZED) = 0.175 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 25975.79 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.70, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.75, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412