11x5.5R-RH (11x55R-RH.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 0.7800 2.2424 0.0000 0.0000 0.3900 0.0000 0.0797 0.0000 0.0622 0.0000 0.1150 0.0000 0.0000 0.1000 0.7693 2.5150 0.0187 -0.1788 0.3845 0.0115 0.0798 1.7070 0.0614 0.1440 0.1234 0.0117 -0.0002 0.2000 0.7783 2.7735 0.1375 -0.3264 0.3870 0.0424 0.0799 6.2432 0.0622 0.1693 0.1459 0.0119 -0.0009 0.3000 0.8104 3.0177 0.4148 -0.3513 0.3960 0.0872 0.0799 12.4097 0.0648 0.1933 0.1684 0.0121 -0.0010 0.4000 0.8661 3.2479 0.8610 -0.1359 0.4099 0.1404 0.0800 18.9112 0.0693 0.2017 0.1895 0.0120 -0.0002 0.5000 0.9409 3.4639 1.4496 0.3324 0.4273 0.1970 0.0800 24.7692 0.0753 0.1970 0.2215 0.0115 0.0010 0.6000 1.0264 3.6657 2.1287 1.0051 0.4468 0.2520 0.0800 29.4520 0.0821 0.1819 0.2634 0.0104 0.0022 0.7000 1.1117 3.8534 2.8331 1.7932 0.4669 0.3004 0.0800 32.7872 0.0890 0.1597 0.3070 0.0083 0.0027 0.8000 1.1857 4.0270 3.4894 2.5823 0.4862 0.3372 0.0800 34.7685 0.0949 0.1350 0.3424 0.0049 0.0020 0.9000 1.2381 4.1864 4.0183 3.2390 0.5031 0.3573 0.0800 35.3970 0.0991 0.1137 0.3622 0.0003 -0.0001 1.0000 1.2599 4.3316 4.3301 3.6084 0.5163 0.3557 0.0800 34.5726 0.1008 0.1028 0.3608 -0.0040 -0.0021 1.1022 1.2595 4.4655 4.4655 3.7212 0.5261 0.3389 0.0799 32.8140 0.1007 0.1014 0.3441 -0.0061 -0.0030 1.2422 1.2547 4.6249 4.6249 3.8296 0.5366 0.3165 0.0798 30.6481 0.1002 0.1002 0.3219 -0.0065 -0.0040 1.3845 1.2453 4.7583 4.7583 3.9078 0.5438 0.2946 0.0797 28.6787 0.0993 0.0985 0.3001 -0.0060 -0.0049 1.5267 1.2313 4.8632 4.8632 3.9575 0.5476 0.2734 0.0796 26.8836 0.0980 0.0962 0.2791 -0.0052 -0.0057 1.6690 1.2126 4.9394 4.9394 3.9788 0.5478 0.2529 0.0794 25.2220 0.0963 0.0932 0.2587 -0.0044 -0.0061 1.8112 1.1894 4.9871 4.9871 3.9723 0.5445 0.2331 0.0792 23.6642 0.0942 0.0895 0.2390 -0.0039 -0.0063 1.9534 1.1615 5.0100 5.0100 3.9420 0.5378 0.2141 0.0790 22.2044 0.0918 0.0852 0.2201 -0.0036 -0.0060 2.0957 1.1312 5.0296 5.0296 3.9080 0.5276 0.1966 0.0788 20.9053 0.0891 0.0806 0.2028 -0.0045 -0.0058 2.2379 1.1008 5.0493 5.0493 3.8731 0.5158 0.1806 0.0786 19.7527 0.0865 0.0762 0.1868 -0.0059 -0.0060 2.3802 1.0704 5.0689 5.0689 3.8378 0.5038 0.1660 0.0783 18.7238 0.0839 0.0719 0.1722 -0.0069 -0.0064 2.5224 1.0400 5.0886 5.0886 3.8019 0.4915 0.1526 0.0781 17.8004 0.0813 0.0678 0.1589 -0.0074 -0.0069 2.6647 1.0096 5.1083 5.1083 3.7658 0.4791 0.1405 0.0779 16.9673 0.0787 0.0638 0.1468 -0.0076 -0.0074 2.8069 0.9792 5.1279 5.1279 3.7296 0.4664 0.1294 0.0777 16.2123 0.0761 0.0599 0.1358 -0.0075 -0.0078 2.9491 0.9488 5.1476 5.1476 3.6932 0.4535 0.1194 0.0775 15.5251 0.0736 0.0561 0.1258 -0.0074 -0.0081 3.0914 0.9184 5.1672 5.1672 3.6569 0.4403 0.1104 0.0773 14.8972 0.0710 0.0525 0.1168 -0.0072 -0.0082 3.2336 0.8880 5.1869 5.1869 3.6205 0.4270 0.1022 0.0772 14.3213 0.0685 0.0490 0.1086 -0.0069 -0.0081 3.3759 0.8576 5.2065 5.2065 3.5843 0.4135 0.0949 0.0770 13.7913 0.0660 0.0456 0.1012 -0.0066 -0.0079 3.5181 0.8272 5.2262 5.2262 3.5482 0.3998 0.0882 0.0768 13.3020 0.0635 0.0424 0.0945 -0.0063 -0.0074 3.6603 0.7968 5.2459 5.2459 3.5123 0.3860 0.0822 0.0766 12.8490 0.0611 0.0393 0.0884 -0.0061 -0.0069 3.8026 0.7664 5.2655 5.2655 3.4766 0.3719 0.0768 0.0765 12.4285 0.0586 0.0363 0.0829 -0.0059 -0.0062 3.9448 0.7360 5.2852 5.2852 3.4410 0.3577 0.0718 0.0763 12.0370 0.0562 0.0334 0.0778 -0.0058 -0.0055 4.0871 0.7056 5.3048 5.3048 3.4061 0.3433 0.0671 0.0762 11.6718 0.0538 0.0307 0.0730 -0.0057 -0.0047 4.2293 0.6752 5.3245 5.3245 3.3714 0.3287 0.0628 0.0760 11.3302 0.0513 0.0281 0.0686 -0.0057 -0.0040 4.3716 0.6448 5.3441 5.3441 3.3371 0.3140 0.0587 0.0759 11.0102 0.0489 0.0256 0.0643 -0.0058 -0.0033 4.5138 0.6144 5.3638 5.3638 3.3032 0.2991 0.0547 0.0758 10.7096 0.0466 0.0232 0.0602 -0.0060 -0.0028 4.6560 0.5840 5.3835 5.3835 3.2702 0.2841 0.0508 0.0756 10.4269 0.0442 0.0209 0.0561 -0.0062 -0.0025 4.7983 0.5536 5.4031 5.4031 3.2378 0.2690 0.0468 0.0755 10.1605 0.0418 0.0188 0.0520 -0.0066 -0.0024 4.9405 0.5232 5.4228 5.4228 3.2063 0.2537 0.0427 0.0754 9.9090 0.0395 0.0168 0.0477 -0.0070 -0.0026 5.0828 0.4928 5.4424 5.4424 3.1729 0.2383 0.0385 0.0753 9.6713 0.0371 0.0149 0.0432 -0.0075 -0.0033 5.2190 0.4637 5.4613 5.4613 3.1263 0.2234 0.0341 0.0752 9.4554 0.0349 0.0131 0.0386 -0.0077 -0.0043 5.2528 0.4565 5.4659 5.4659 3.1118 0.2197 0.0330 0.0752 9.4036 0.0343 0.0127 0.0375 -0.0077 -0.0046 5.2806 0.4505 5.4698 5.4698 3.0990 0.2166 0.0320 0.0751 9.3615 0.0339 0.0124 0.0365 -0.0077 -0.0048 5.3083 0.4446 5.4736 5.4736 3.0851 0.2136 0.0311 0.0751 9.3198 0.0334 0.0120 0.0355 -0.0077 -0.0051 5.3361 0.4387 5.4775 5.4775 3.0705 0.2105 0.0301 0.0751 9.2785 0.0329 0.0117 0.0344 -0.0076 -0.0054 5.3639 0.4327 5.4813 5.4813 3.0541 0.2074 0.0291 0.0751 9.2376 0.0325 0.0114 0.0334 -0.0076 -0.0058 5.3917 0.4262 5.4851 5.4852 3.0371 0.2041 0.0280 0.0751 9.1973 0.0320 0.0110 0.0323 -0.0075 -0.0061 5.4194 0.4131 5.4890 5.4898 3.0198 0.1975 0.0264 0.0751 9.1586 0.0310 0.0103 0.0306 -0.0074 -0.0065 5.4472 0.3876 5.4928 5.4961 3.0032 0.1847 0.0239 0.0750 9.1228 0.0291 0.0091 0.0278 -0.0073 -0.0069 5.4750 0.3377 5.4966 5.5064 2.9890 0.1599 0.0194 0.0750 9.0940 0.0253 0.0069 0.0228 -0.0072 -0.0073 5.5000 0.1976 5.5001 5.5371 5.5371 0.0909 0.0080 0.0750 9.1031 0.0148 0.0000 0.0079 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.39 HUB RADIUS (IN) HUBTRA: 1.00 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.048836 TOTAL WEIGHT (Kg) = 0.022148 TOTAL VOLUME (IN**3) = 0.795601 TOTAL PROJECTED AREA (IN**2) = 9.1561 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000587 MOMENT OF INERTIA (Kg-M**2) = 0.000066 STATIC MOMENT, ONE SIDE (IN-LB) = 0.041370 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 = 90.656 INNER LIMIT (NORMALIZED BY RADIUS) = 0.071 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9208.42 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.50, APC16009R (Transition Start, Airfoil 1) AIRFOIL2: 5.00, APC16009R (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.