13x5.5E (13x55E.dat) v2025-1001 Simulation Date: 02/24/2026 ----- 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 & RAKE ARE 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(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.8000 -0.8225 0.0000 0.0000 0.4000 0.0000 0.4375 0.0000 0.3500 0.0000 0.0800 0.0000 0.0000 0.1050 0.7665 0.0317 0.0107 -0.4470 0.3957 0.0048 0.4353 0.9271 0.3337 0.2255 0.0830 0.0089 -0.0844 0.2100 0.7319 0.8239 0.0836 -0.8671 0.3933 0.0181 0.4288 3.6262 0.3138 0.2197 0.0912 0.0246 -0.0816 0.3150 0.7014 1.5541 0.2761 -1.1518 0.3929 0.0377 0.4179 7.9428 0.2931 0.2091 0.1034 0.0431 -0.0758 0.4200 0.6808 2.2224 0.6357 -1.1609 0.3944 0.0620 0.4026 13.5436 0.2741 0.1920 0.1184 0.0635 -0.0667 0.5250 0.6746 2.8287 1.1893 -0.8003 0.3979 0.0889 0.3830 19.8260 0.2584 0.1720 0.1354 0.0840 -0.0547 0.6300 0.6846 3.3731 1.9293 -0.0386 0.4033 0.1166 0.3591 25.9848 0.2458 0.1522 0.1536 0.1035 -0.0404 0.7350 0.7097 3.8555 2.7992 1.0609 0.4105 0.1434 0.3315 31.2215 0.2353 0.1346 0.1720 0.1207 -0.0242 0.8400 0.7463 4.2760 3.6885 2.2900 0.4196 0.1674 0.3054 34.9485 0.2279 0.1208 0.1896 0.1343 -0.0073 0.9450 0.7903 4.6344 4.4487 3.3152 0.4306 0.1867 0.2816 36.8420 0.2226 0.1123 0.2050 0.1427 0.0084 1.0500 0.8385 4.9310 4.9293 3.9468 0.4433 0.1996 0.2600 36.7657 0.2180 0.1109 0.2170 0.1432 0.0194 1.1585 0.8886 5.1723 5.1723 4.2537 0.4569 0.2070 0.2398 35.3964 0.2131 0.1143 0.2257 0.1368 0.0258 1.3273 0.9584 5.4162 5.4162 4.6036 0.4752 0.2134 0.2126 33.0019 0.2038 0.1175 0.2342 0.1237 0.0342 1.4996 1.0198 5.5000 5.5000 4.8013 0.4904 0.2127 0.1896 30.2736 0.1933 0.1186 0.2364 0.1087 0.0410 1.6719 1.0716 5.5000 5.5000 4.9038 0.5021 0.2053 0.1708 27.6357 0.1830 0.1185 0.2322 0.0931 0.0436 1.8441 1.1138 5.5000 5.5000 4.9866 0.5105 0.1918 0.1558 25.3922 0.1735 0.1179 0.2216 0.0781 0.0397 2.0164 1.1469 5.5000 5.5000 5.0490 0.5157 0.1750 0.1441 23.4662 0.1653 0.1174 0.2075 0.0635 0.0321 2.1887 1.1711 5.5000 5.5000 5.0952 0.5180 0.1589 0.1352 21.7985 0.1584 0.1169 0.1940 0.0494 0.0246 2.3610 1.1872 5.5000 5.5000 5.1290 0.5175 0.1434 0.1286 20.3426 0.1527 0.1165 0.1810 0.0357 0.0174 2.5333 1.1955 5.5000 5.5000 5.1509 0.5143 0.1285 0.1238 19.0622 0.1480 0.1159 0.1686 0.0229 0.0105 2.7056 1.1965 5.5000 5.5000 5.1622 0.5085 0.1142 0.1203 17.9284 0.1439 0.1150 0.1567 0.0111 0.0040 2.8778 1.1907 5.5000 5.5000 5.1675 0.5004 0.1008 0.1176 16.9182 0.1400 0.1134 0.1453 0.0000 -0.0021 3.0501 1.1787 5.5000 5.5000 5.1710 0.4901 0.0884 0.1151 16.0129 0.1357 0.1109 0.1343 -0.0103 -0.0075 3.2224 1.1608 5.5000 5.5000 5.1723 0.4777 0.0768 0.1129 15.1974 0.1310 0.1074 0.1237 -0.0197 -0.0124 3.3947 1.1377 5.5000 5.5000 5.1678 0.4634 0.0661 0.1108 14.4592 0.1260 0.1031 0.1136 -0.0283 -0.0166 3.5670 1.1097 5.5000 5.5000 5.1541 0.4474 0.0563 0.1088 13.7881 0.1207 0.0980 0.1039 -0.0361 -0.0203 3.7393 1.0773 5.5000 5.5000 5.1388 0.4297 0.0472 0.1070 13.1755 0.1153 0.0923 0.0946 -0.0430 -0.0235 3.9116 1.0411 5.5000 5.5000 5.1229 0.4106 0.0388 0.1054 12.6142 0.1097 0.0861 0.0857 -0.0492 -0.0262 4.0838 1.0015 5.5000 5.5000 5.1076 0.3901 0.0310 0.1039 12.0980 0.1041 0.0796 0.0770 -0.0546 -0.0284 4.2561 0.9591 5.5000 5.5000 5.0930 0.3686 0.0238 0.1026 11.6219 0.0984 0.0729 0.0687 -0.0594 -0.0303 4.4284 0.9142 5.5000 5.5000 5.0807 0.3460 0.0172 0.1014 11.1814 0.0927 0.0661 0.0607 -0.0637 -0.0318 4.6007 0.8675 5.5000 5.5000 5.0709 0.3226 0.0110 0.1004 10.7726 0.0871 0.0593 0.0529 -0.0675 -0.0331 4.7730 0.8193 5.5000 5.5000 5.0646 0.2985 0.0052 0.0996 10.3924 0.0816 0.0527 0.0454 -0.0710 -0.0342 4.9453 0.7702 5.5000 5.5000 5.0606 0.2738 -0.0002 0.0989 10.0379 0.0762 0.0465 0.0381 -0.0743 -0.0353 5.1175 0.7206 5.5000 5.5000 5.0579 0.2488 -0.0053 0.0984 9.7065 0.0709 0.0406 0.0310 -0.0778 -0.0365 5.2898 0.6711 5.5000 5.5000 5.0563 0.2235 -0.0102 0.0980 9.3961 0.0658 0.0352 0.0241 -0.0815 -0.0377 5.4621 0.6221 5.5000 5.5000 5.0566 0.1982 -0.0149 0.0978 9.1047 0.0609 0.0303 0.0174 -0.0853 -0.0391 5.6344 0.5742 5.5000 5.5000 5.0590 0.1729 -0.0195 0.0978 8.8308 0.0561 0.0259 0.0108 -0.0895 -0.0407 5.8067 0.5277 5.5000 5.5000 5.0587 0.1478 -0.0239 0.0979 8.5727 0.0517 0.0220 0.0041 -0.0941 -0.0426 5.9790 0.4832 5.5000 5.5000 5.0195 0.1232 -0.0283 0.0982 8.3292 0.0474 0.0185 -0.0032 -0.0991 -0.0456 6.1440 0.4429 5.5000 5.5000 4.9281 0.1000 -0.0325 0.0986 8.1086 0.0437 0.0157 -0.0109 -0.1044 -0.0495 6.1840 0.4335 5.5000 5.5000 4.8960 0.0945 -0.0336 0.0987 8.0568 0.0428 0.0151 -0.0128 -0.1057 -0.0506 6.2167 0.4238 5.5000 5.5000 4.8663 0.0878 -0.0347 0.0988 8.0150 0.0419 0.0144 -0.0148 -0.1080 -0.0517 6.2494 0.4101 5.5000 5.5000 4.8214 0.0771 -0.0365 0.0989 7.9736 0.0406 0.0135 -0.0176 -0.1125 -0.0533 6.2821 0.3920 5.5000 5.5000 4.7178 0.0620 -0.0388 0.0991 7.9326 0.0388 0.0124 -0.0212 -0.1195 -0.0553 6.3148 0.3687 5.5000 5.5000 4.6218 0.0416 -0.0418 0.0992 7.8920 0.0366 0.0110 -0.0257 -0.1293 -0.0578 6.3475 0.3386 5.5000 5.5000 4.5422 0.0145 -0.0458 0.0993 7.8519 0.0336 0.0093 -0.0313 -0.1429 -0.0609 6.3802 0.2988 5.5000 5.5000 4.5027 -0.0224 -0.0511 0.0995 7.8122 0.0297 0.0073 -0.0387 -0.1618 -0.0648 6.4129 0.2407 5.5000 5.5000 4.5877 -0.0775 -0.0589 0.0996 7.7728 0.0240 0.0048 -0.0491 -0.1906 -0.0703 6.4456 0.1314 5.5000 5.5000 5.4134 -0.1836 -0.0734 0.0997 7.7338 0.0131 0.0015 -0.0683 -0.2469 -0.0801 6.4750 0.0185 5.5000 5.5028 5.5028 -0.2934 -0.0884 0.0999 7.7029 0.0019 0.0000 -0.0884 0.0000 0.0000 RADIUS: 6.47 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.05 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.074075 TOTAL WEIGHT (Kg) = 0.033594 TOTAL VOLUME (IN**3) = 1.206769 TOTAL PROJECTED AREA (IN**2) = 10.7720 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001469 MOMENT OF INERTIA (Kg-M**2) = 0.000166 STATIC MOMENT, ONE SIDE (IN-LB) = 0.083729 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 = 82.897 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9977.00 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.05, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412