5.1x5.0E-3 (51x50E-3.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) 0.1245 0.4313 1.9676 0.0000 -0.3933 0.2156 0.0000 0.1790 0.0000 0.0772 0.0000 0.1100 0.0000 0.0000 0.1720 0.3934 2.2447 0.0320 -0.5822 0.1966 0.0067 0.1732 1.6947 0.0682 0.0716 0.1136 0.0051 0.0007 0.2196 0.3855 2.5080 0.1555 -0.7045 0.1915 0.0247 0.1676 6.4307 0.0646 0.0738 0.1234 0.0054 0.0026 0.2671 0.3924 2.7576 0.3935 -0.6469 0.1924 0.0511 0.1621 13.1921 0.0636 0.0745 0.1354 0.0070 0.0076 0.3147 0.4069 2.9934 0.7589 -0.3510 0.1942 0.0828 0.1568 20.9967 0.0638 0.0703 0.1483 0.0100 0.0160 0.3623 0.4300 3.2155 1.2497 0.2099 0.1963 0.1172 0.1516 28.7698 0.0652 0.0629 0.1627 0.0137 0.0266 0.4098 0.4597 3.4239 1.8476 1.0101 0.1984 0.1513 0.1466 35.6614 0.0674 0.0536 0.1791 0.0175 0.0384 0.4574 0.4920 3.6185 2.5156 1.9591 0.1997 0.1824 0.1418 41.1997 0.0698 0.0441 0.1968 0.0201 0.0492 0.5049 0.5216 3.7994 3.1964 2.8882 0.1998 0.2078 0.1372 45.2158 0.0716 0.0354 0.2139 0.0219 0.0587 0.5525 0.5451 3.9665 3.7771 3.6578 0.2007 0.2247 0.1328 47.4169 0.0724 0.0286 0.2274 0.0237 0.0667 0.6000 0.5594 4.1198 4.1181 4.0910 0.2046 0.2302 0.1286 47.5274 0.0719 0.0256 0.2322 0.0250 0.0703 0.6483 0.5665 4.2614 4.2614 4.2424 0.2103 0.2276 0.1246 46.2941 0.0706 0.0255 0.2297 0.0249 0.0696 0.7088 0.5740 4.4189 4.4189 4.4093 0.2164 0.2238 0.1199 44.7784 0.0688 0.0253 0.2262 0.0243 0.0687 0.7700 0.5800 4.5556 4.5556 4.5549 0.2215 0.2196 0.1156 43.2793 0.0670 0.0250 0.2222 0.0232 0.0677 0.8312 0.5845 4.6695 4.6695 4.6767 0.2255 0.2149 0.1117 41.8013 0.0653 0.0247 0.2177 0.0216 0.0667 0.8924 0.5876 4.7607 4.7607 4.7741 0.2285 0.2098 0.1084 40.3337 0.0637 0.0244 0.2130 0.0194 0.0657 0.9536 0.5893 4.8291 4.8291 4.8467 0.2304 0.2044 0.1055 38.8683 0.0622 0.0241 0.2079 0.0167 0.0647 1.0148 0.5896 4.8747 4.8747 4.8941 0.2315 0.1985 0.1032 37.3988 0.0608 0.0238 0.2025 0.0136 0.0637 1.0760 0.5886 4.8975 4.8975 4.9160 0.2316 0.1923 0.1014 35.9200 0.0597 0.0236 0.1968 0.0102 0.0628 1.1372 0.5863 4.9029 4.9029 4.9180 0.2308 0.1857 0.1002 34.4574 0.0588 0.0234 0.1908 0.0065 0.0617 1.1984 0.5827 4.9073 4.9073 4.9170 0.2291 0.1788 0.0995 33.0931 0.0580 0.0232 0.1846 0.0028 0.0602 1.2596 0.5780 4.9116 4.9116 4.9157 0.2267 0.1716 0.0988 31.8239 0.0571 0.0229 0.1782 -0.0011 0.0583 1.3208 0.5721 4.9160 4.9160 4.9142 0.2234 0.1642 0.0982 30.6412 0.0562 0.0225 0.1716 -0.0050 0.0561 1.3820 0.5651 4.9204 4.9204 4.9126 0.2194 0.1568 0.0975 29.5375 0.0551 0.0221 0.1648 -0.0090 0.0535 1.4432 0.5570 4.9247 4.9247 4.9109 0.2146 0.1492 0.0968 28.5058 0.0539 0.0216 0.1579 -0.0131 0.0507 1.5044 0.5479 4.9291 4.9291 4.9091 0.2092 0.1416 0.0961 27.5399 0.0527 0.0211 0.1509 -0.0173 0.0478 1.5656 0.5378 4.9334 4.9334 4.9073 0.2032 0.1339 0.0954 26.6343 0.0513 0.0204 0.1438 -0.0215 0.0446 1.6268 0.5268 4.9378 4.9378 4.9055 0.1965 0.1263 0.0947 25.7837 0.0499 0.0197 0.1367 -0.0257 0.0414 1.6880 0.5148 4.9421 4.9421 4.9040 0.1892 0.1187 0.0941 24.9838 0.0484 0.0190 0.1295 -0.0300 0.0380 1.7492 0.5020 4.9465 4.9465 4.9026 0.1814 0.1111 0.0934 24.2305 0.0469 0.0182 0.1223 -0.0342 0.0346 1.8104 0.4884 4.9508 4.9508 4.9017 0.1731 0.1037 0.0927 23.5199 0.0453 0.0173 0.1152 -0.0385 0.0312 1.8717 0.4740 4.9552 4.9552 4.9015 0.1643 0.0963 0.0920 22.8488 0.0436 0.0164 0.1081 -0.0427 0.0278 1.9329 0.4589 4.9596 4.9596 4.9021 0.1551 0.0891 0.0913 22.2141 0.0419 0.0155 0.1010 -0.0468 0.0245 1.9941 0.4431 4.9639 4.9639 4.9036 0.1455 0.0821 0.0906 21.6131 0.0402 0.0145 0.0941 -0.0509 0.0213 2.0553 0.4266 4.9683 4.9683 4.9061 0.1355 0.0753 0.0900 21.0433 0.0384 0.0135 0.0873 -0.0549 0.0181 2.1165 0.4096 4.9726 4.9726 4.9100 0.1252 0.0687 0.0893 20.5024 0.0366 0.0125 0.0806 -0.0588 0.0151 2.1777 0.3918 4.9770 4.9770 4.9156 0.1144 0.0623 0.0886 19.9884 0.0347 0.0114 0.0740 -0.0627 0.0123 2.2389 0.3707 4.9813 4.9813 4.9232 0.1007 0.0553 0.0879 19.4994 0.0326 0.0103 0.0666 -0.0679 0.0090 2.3001 0.3441 4.9857 4.9857 4.9294 0.0820 0.0469 0.0872 19.0337 0.0300 0.0088 0.0576 -0.0754 0.0048 2.3613 0.3104 4.9901 4.9901 4.9323 0.0567 0.0369 0.0865 18.5897 0.0269 0.0072 0.0463 -0.0862 -0.0009 2.4200 0.2695 4.9942 4.9942 4.9429 0.0248 0.0252 0.0859 18.1831 0.0231 0.0054 0.0331 -0.1004 -0.0079 2.4354 0.2564 4.9953 4.9953 4.9481 0.0144 0.0217 0.0857 18.0793 0.0220 0.0049 0.0290 -0.1049 -0.0100 2.4483 0.2445 4.9962 4.9962 4.9539 0.0046 0.0183 0.0856 17.9934 0.0209 0.0045 0.0252 -0.1095 -0.0120 2.4611 0.2322 4.9972 4.9972 4.9612 -0.0066 0.0146 0.0854 17.9084 0.0198 0.0041 0.0210 -0.1152 -0.0143 2.4740 0.2195 4.9981 4.9981 4.9700 -0.0192 0.0105 0.0853 17.8241 0.0187 0.0036 0.0164 -0.1222 -0.0171 2.4869 0.2064 4.9990 4.9990 4.9809 -0.0338 0.0058 0.0851 17.7407 0.0176 0.0032 0.0112 -0.1310 -0.0204 2.4998 0.1930 4.9999 4.9999 4.9945 -0.0507 0.0004 0.0850 17.6580 0.0164 0.0028 0.0053 -0.1418 -0.0243 2.5127 0.1786 5.0008 5.0008 5.0137 -0.0707 -0.0060 0.0849 17.5761 0.0152 0.0024 -0.0015 -0.1555 -0.0290 2.5255 0.1548 5.0017 5.0017 5.0665 -0.0958 -0.0138 0.0847 17.4949 0.0131 0.0018 -0.0100 -0.1698 -0.0341 2.5384 0.1140 5.0027 5.0027 5.2319 -0.1302 -0.0246 0.0846 17.4146 0.0096 0.0010 -0.0218 -0.1857 -0.0399 2.5500 0.0083 5.0035 5.0059 5.0059 -0.2093 -0.0491 0.0844 17.3508 0.0007 0.0000 -0.0491 0.0000 0.0000 RADIUS: 2.55 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.60 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.011389 TOTAL WEIGHT (Kg) = 0.005165 TOTAL VOLUME (IN**3) = 0.185543 TOTAL PROJECTED AREA (IN**2) = 2.9758 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000037 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003499 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 = 126.897 INNER LIMIT (NORMALIZED BY RADIUS) = 0.098 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 26536.83 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.66, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.45, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412