8.8x9.75 (88x975.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 0.9000 6.4418 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2100 0.0000 0.0000 0.1200 0.8601 6.2213 -0.4857 -1.0223 0.4452 0.0070 0.2204 -32.7875 0.1896 0.3742 0.2124 0.0137 -0.0444 0.2400 0.8158 6.0662 -0.3883 -1.5158 0.4424 0.0259 0.2262 -14.4382 0.1845 0.3574 0.2185 0.0340 -0.0427 0.3600 0.7735 5.9715 -0.1317 -1.8468 0.4414 0.0530 0.2313 -3.3311 0.1789 0.3305 0.2265 0.0577 -0.0381 0.4800 0.7399 5.9327 0.3509 -1.8740 0.4416 0.0850 0.2358 6.6371 0.1745 0.2958 0.2353 0.0833 -0.0312 0.6000 0.7200 5.9447 1.1088 -1.4862 0.4429 0.1188 0.2397 16.3902 0.1726 0.2582 0.2442 0.1091 -0.0231 0.7200 0.7147 6.0029 2.1563 -0.6219 0.4447 0.1512 0.2430 25.4850 0.1737 0.2215 0.2524 0.1336 -0.0148 0.8400 0.7203 6.1024 3.4449 0.6878 0.4467 0.1790 0.2457 33.1327 0.1770 0.1887 0.2589 0.1552 -0.0073 0.9600 0.7297 6.2385 4.8305 2.2636 0.4487 0.1989 0.2477 38.6888 0.1808 0.1616 0.2621 0.1725 -0.0014 1.0800 0.7346 6.4064 6.0535 3.7359 0.4501 0.2079 0.2492 41.7357 0.1831 0.1417 0.2602 0.1839 0.0021 1.2000 0.7280 6.6012 6.7620 4.5640 0.4507 0.2028 0.2500 41.8869 0.1820 0.1299 0.2511 0.1880 0.0023 1.3188 0.7129 6.8160 7.0083 4.8193 0.4506 0.1883 0.2503 40.2231 0.1784 0.1210 0.2359 0.1881 -0.0001 1.4175 0.7002 7.0075 7.2216 5.1512 0.4503 0.1767 0.2500 39.0366 0.1751 0.1103 0.2218 0.1894 -0.0027 1.5149 0.6876 7.2057 7.4408 5.5463 0.4499 0.1659 0.2493 38.0150 0.1715 0.0992 0.2078 0.1912 -0.0054 1.6124 0.6749 7.4102 7.6661 5.9623 0.4493 0.1555 0.2483 37.1141 0.1676 0.0893 0.1947 0.1931 -0.0080 1.7099 0.6621 7.6185 7.8947 6.3683 0.4486 0.1457 0.2468 36.3093 0.1634 0.0819 0.1834 0.1947 -0.0100 1.8074 0.6493 7.8280 8.1240 6.7562 0.4475 0.1363 0.2449 35.5796 0.1590 0.0768 0.1740 0.1959 -0.0113 1.9048 0.6364 8.0361 8.3515 7.1399 0.4463 0.1273 0.2427 34.9070 0.1544 0.0732 0.1660 0.1968 -0.0122 2.0023 0.6235 8.2402 8.5745 7.5342 0.4448 0.1187 0.2400 34.2762 0.1496 0.0696 0.1583 0.1976 -0.0130 2.0998 0.6105 8.4378 8.7903 7.9271 0.4430 0.1106 0.2369 33.6742 0.1446 0.0660 0.1507 0.1985 -0.0140 2.1973 0.5974 8.6263 8.9963 8.3023 0.4409 0.1027 0.2334 33.0894 0.1394 0.0624 0.1432 0.1995 -0.0152 2.2947 0.5843 8.8032 9.1897 8.6401 0.4385 0.0953 0.2295 32.5120 0.1341 0.0588 0.1356 0.2005 -0.0166 2.3922 0.5711 8.9659 9.3679 8.9181 0.4358 0.0881 0.2252 31.9332 0.1286 0.0552 0.1278 0.2017 -0.0184 2.4897 0.5578 9.1117 9.5281 9.1128 0.4326 0.0813 0.2205 31.3453 0.1230 0.0515 0.1196 0.2030 -0.0207 2.5872 0.5445 9.2382 9.6676 9.2396 0.4291 0.0747 0.2156 30.7410 0.1174 0.0480 0.1113 0.2044 -0.0232 2.6846 0.5310 9.3427 9.7836 9.3441 0.4252 0.0683 0.2107 30.1140 0.1119 0.0446 0.1031 0.2053 -0.0255 2.7821 0.5175 9.4228 9.8733 9.4241 0.4208 0.0620 0.2057 29.4585 0.1065 0.0413 0.0952 0.2059 -0.0277 2.8796 0.5038 9.4758 9.9340 9.4769 0.4160 0.0559 0.2008 28.7691 0.1012 0.0382 0.0875 0.2060 -0.0296 2.9771 0.4901 9.4991 9.9629 9.5002 0.4107 0.0500 0.1959 28.0408 0.0960 0.0353 0.0800 0.2057 -0.0314 3.0745 0.4762 9.5000 9.9673 9.5010 0.4049 0.0442 0.1909 27.2920 0.0909 0.0325 0.0728 0.2049 -0.0330 3.1720 0.4622 9.5000 9.9683 9.5009 0.3986 0.0386 0.1860 26.5724 0.0860 0.0298 0.0657 0.2037 -0.0346 3.2695 0.4481 9.5000 9.9669 9.5008 0.3918 0.0332 0.1810 25.8816 0.0811 0.0273 0.0588 0.2021 -0.0362 3.3670 0.4339 9.5000 9.9627 9.5007 0.3844 0.0281 0.1761 25.2173 0.0764 0.0249 0.0522 0.2001 -0.0378 3.4644 0.4195 9.5000 9.9555 9.5006 0.3764 0.0231 0.1712 24.5771 0.0718 0.0227 0.0458 0.1976 -0.0393 3.5619 0.4050 9.5000 9.9450 9.5005 0.3678 0.0184 0.1662 23.9589 0.0673 0.0206 0.0395 0.1945 -0.0407 3.6594 0.3903 9.5000 9.9310 9.5004 0.3586 0.0138 0.1613 23.3605 0.0629 0.0186 0.0335 0.1909 -0.0422 3.7569 0.3755 9.5000 9.9129 9.5003 0.3487 0.0094 0.1563 22.7800 0.0587 0.0167 0.0277 0.1868 -0.0435 3.8543 0.3605 9.5000 9.8904 9.5002 0.3382 0.0052 0.1514 22.2151 0.0546 0.0150 0.0221 0.1820 -0.0448 3.9518 0.3454 9.5000 9.8628 9.5002 0.3270 0.0012 0.1465 21.6637 0.0506 0.0133 0.0168 0.1766 -0.0461 4.0493 0.3301 9.4754 9.8049 9.4755 0.3150 -0.0027 0.1415 21.0756 0.0467 0.0118 0.0116 0.1705 -0.0472 4.1428 0.3153 9.2934 9.5850 9.2935 0.3029 -0.0064 0.1368 20.2151 0.0431 0.0105 0.0069 0.1638 -0.0476 4.1688 0.3104 9.2114 9.4914 9.2116 0.2987 -0.0077 0.1355 19.9186 0.0421 0.0101 0.0053 0.1615 -0.0477 4.1908 0.3037 9.1311 9.4013 9.1317 0.2928 -0.0097 0.1344 19.6482 0.0408 0.0096 0.0030 0.1582 -0.0484 4.2129 0.2942 9.0409 9.3012 9.0422 0.2841 -0.0126 0.1332 19.3605 0.0392 0.0089 -0.0004 0.1534 -0.0496 4.2349 0.2816 8.9409 9.1910 8.9479 0.2725 -0.0165 0.1321 19.0554 0.0372 0.0081 -0.0049 0.1471 -0.0515 4.2570 0.2652 8.8310 9.0706 8.8673 0.2572 -0.0216 0.1310 18.7328 0.0347 0.0072 -0.0107 0.1386 -0.0541 4.2790 0.2438 8.7113 8.9399 8.7941 0.2371 -0.0282 0.1299 18.3926 0.0317 0.0060 -0.0182 0.1276 -0.0577 4.3011 0.2150 8.5818 8.7989 8.7449 0.2100 -0.0370 0.1288 18.0348 0.0277 0.0047 -0.0281 0.1127 -0.0627 4.3231 0.1715 8.4424 8.6478 8.7842 0.1688 -0.0501 0.1276 17.6597 0.0219 0.0030 -0.0430 0.0903 -0.0705 4.3452 0.0915 8.2932 8.4875 9.4240 0.0926 -0.0741 0.1265 17.2695 0.0116 0.0009 -0.0703 0.0491 -0.0853 4.3650 0.0139 8.1504 8.1504 8.1504 0.0186 -0.0968 0.1255 16.5508 0.0018 0.0000 -0.0968 0.0000 0.0000 RADIUS: 4.36 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.056628 TOTAL WEIGHT (Kg) = 0.025682 TOTAL VOLUME (IN**3) = 0.922543 TOTAL PROJECTED AREA (IN**2) = 4.3206 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000293 MOMENT OF INERTIA (Kg-M**2) = 0.000033 STATIC MOMENT, ONE SIDE (IN-LB) = 0.029697 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 = 73.855 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 35730.48 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.