13x10F (13x10F.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 10.0000 10.0000 9.1204 0.3633 0.1691 42.9780 0.1929 0.1294 0.4034 -0.0060 0.1214 1.7783 1.1596 10.0000 10.0000 9.1953 0.3679 0.1611 41.8275 0.1869 0.1278 0.3966 -0.0130 0.1172 1.8486 1.1771 10.0000 10.0000 9.2624 0.3721 0.1540 40.7264 0.1812 0.1263 0.3896 -0.0199 0.1129 1.9189 1.1928 10.0000 10.0000 9.3217 0.3757 0.1476 39.6723 0.1760 0.1249 0.3825 -0.0267 0.1087 1.9892 1.2069 10.0000 10.0000 9.3731 0.3788 0.1420 38.6630 0.1714 0.1236 0.3752 -0.0333 0.1044 2.0595 1.2193 10.0000 10.0000 9.4165 0.3815 0.1373 37.6963 0.1674 0.1226 0.3677 -0.0398 0.1000 2.1298 1.2302 10.0000 10.0000 9.4520 0.3837 0.1333 36.7700 0.1640 0.1219 0.3600 -0.0462 0.0955 2.2206 1.2419 10.0000 10.0000 9.4862 0.3858 0.1293 35.6304 0.1606 0.1215 0.3499 -0.0542 0.0895 2.3591 1.2549 10.0000 10.0000 9.5304 0.3877 0.1242 34.0050 0.1559 0.1208 0.3340 -0.0660 0.0799 2.4984 1.2623 10.0000 10.0000 9.5705 0.3878 0.1196 32.4978 0.1510 0.1195 0.3174 -0.0773 0.0699 2.6378 1.2644 10.0000 10.0000 9.6059 0.3863 0.1155 31.1056 0.1460 0.1178 0.3002 -0.0880 0.0593 2.7771 1.2615 10.0000 10.0000 9.6364 0.3833 0.1119 29.8172 0.1411 0.1158 0.2826 -0.0981 0.0484 2.9164 1.2539 10.0000 10.0000 9.6614 0.3787 0.1087 28.6224 0.1363 0.1133 0.2645 -0.1075 0.0371 3.0557 1.2418 10.0000 10.0000 9.6798 0.3728 0.1060 27.5125 0.1316 0.1106 0.2459 -0.1161 0.0255 3.1950 1.2256 10.0000 10.0000 9.6901 0.3654 0.1036 26.4794 0.1270 0.1075 0.2270 -0.1240 0.0137 3.3343 1.2056 10.0000 10.0000 9.6890 0.3568 0.1016 25.5161 0.1225 0.1041 0.2077 -0.1311 0.0017 3.4737 1.1821 10.0000 10.0000 9.6827 0.3470 0.0999 24.6161 0.1181 0.1004 0.1881 -0.1373 -0.0104 3.6130 1.1554 10.0000 10.0000 9.6735 0.3359 0.0986 23.7739 0.1139 0.0963 0.1683 -0.1428 -0.0227 3.7523 1.1258 10.0000 10.0000 9.6624 0.3238 0.0975 22.9844 0.1098 0.0920 0.1481 -0.1474 -0.0349 3.8916 1.0936 10.0000 10.0000 9.6500 0.3107 0.0967 22.2431 0.1057 0.0874 0.1278 -0.1514 -0.0472 4.0309 1.0591 10.0000 10.0000 9.6372 0.2966 0.0961 21.5458 0.1018 0.0826 0.1073 -0.1546 -0.0595 4.1702 1.0226 10.0000 10.0000 9.6245 0.2817 0.0957 20.8891 0.0978 0.0775 0.0867 -0.1572 -0.0717 4.3096 0.9845 10.0000 10.0000 9.6128 0.2659 0.0954 20.2695 0.0939 0.0723 0.0659 -0.1594 -0.0840 4.4489 0.9450 10.0000 10.0000 9.6024 0.2493 0.0953 19.6842 0.0900 0.0670 0.0451 -0.1611 -0.0962 4.5882 0.9044 10.0000 10.0000 9.5935 0.2321 0.0953 19.1306 0.0862 0.0616 0.0242 -0.1625 -0.1085 4.7275 0.8630 10.0000 10.0000 9.5839 0.2143 0.0953 18.6062 0.0823 0.0563 0.0033 -0.1636 -0.1208 4.8668 0.8212 10.0000 10.0000 9.5758 0.1959 0.0954 18.1088 0.0784 0.0511 -0.0176 -0.1648 -0.1333 5.0061 0.7793 10.0000 10.0000 9.5685 0.1770 0.0956 17.6365 0.0745 0.0461 -0.0384 -0.1662 -0.1460 5.1455 0.7375 10.0000 10.0000 9.5622 0.1577 0.0957 17.1874 0.0706 0.0414 -0.0591 -0.1680 -0.1591 5.2848 0.6961 10.0000 10.0000 9.5571 0.1381 0.0957 16.7600 0.0667 0.0369 -0.0797 -0.1702 -0.1723 5.4241 0.6555 10.0000 10.0000 9.5535 0.1182 0.0958 16.3528 0.0628 0.0328 -0.1002 -0.1730 -0.1859 5.5634 0.6160 10.0000 10.0000 9.5518 0.0981 0.0957 15.9645 0.0589 0.0290 -0.1204 -0.1764 -0.1996 5.7027 0.5779 10.0000 10.0000 9.5521 0.0778 0.0955 15.5936 0.0552 0.0255 -0.1404 -0.1804 -0.2135 5.8420 0.5414 10.0000 10.0000 9.5549 0.0575 0.0951 15.2393 0.0515 0.0224 -0.1601 -0.1852 -0.2275 5.9814 0.5070 10.0000 10.0000 9.5603 0.0371 0.0945 14.9003 0.0479 0.0196 -0.1795 -0.1908 -0.2417 6.1207 0.4748 10.0000 10.0000 9.5386 0.0168 0.0938 14.5757 0.0445 0.0171 -0.1991 -0.1973 -0.2567 6.2548 0.4385 10.0000 10.0000 9.4329 -0.0101 0.0928 14.2760 0.0407 0.0145 -0.2210 -0.2085 -0.2742 6.3300 0.3932 10.0000 10.0000 9.3114 -0.0504 0.0922 14.1133 0.0362 0.0116 -0.2405 -0.2283 -0.2885 6.4000 0.3190 10.0000 10.0000 8.7938 -0.1198 0.0915 13.9650 0.0292 0.0076 -0.2672 -0.2638 -0.3064 6.4700 0.1359 10.0000 10.0000 8.5532 -0.2958 0.0907 13.8197 0.0123 0.0014 -0.3219 -0.3575 -0.3390 6.5000 0.0201 10.0000 10.0154 10.0154 -0.4078 0.0904 13.7788 0.0018 0.0000 -0.3542 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) = 0.056585 TOTAL WEIGHT (Kg) = 0.025662 TOTAL VOLUME (IN**3) = 0.921844 TOTAL PROJECTED AREA (IN**2) = 8.8407 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001502 MOMENT OF INERTIA (Kg-M**2) = 0.000170 STATIC MOMENT, ONE SIDE (IN-LB) = 0.082338 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) = 25949.71 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