8.75x7.75NN (875x775NN.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 3.1520 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2200 0.0000 0.0000 0.1200 0.8598 3.6399 -0.4857 -1.0057 0.4452 0.0071 0.2204 -32.7885 0.1895 0.3742 0.2221 0.0141 -0.0356 0.2400 0.8146 4.1005 -0.3882 -1.4847 0.4424 0.0260 0.2262 -14.4369 0.1842 0.3569 0.2275 0.0349 -0.0346 0.3600 0.7710 4.5337 -0.1306 -1.8055 0.4414 0.0532 0.2313 -3.3047 0.1783 0.3294 0.2344 0.0592 -0.0309 0.4800 0.7360 4.9395 0.3560 -1.8271 0.4416 0.0854 0.2358 6.7328 0.1735 0.2943 0.2419 0.0853 -0.0251 0.6000 0.7149 5.3180 1.1244 -1.4361 0.4429 0.1193 0.2397 16.6081 0.1714 0.2563 0.2493 0.1118 -0.0182 0.7200 0.7088 5.6691 2.1929 -0.5663 0.4447 0.1518 0.2430 25.8614 0.1722 0.2194 0.2560 0.1369 -0.0112 0.8400 0.7143 5.9929 3.5157 0.7566 0.4467 0.1797 0.2457 33.6684 0.1755 0.1866 0.2611 0.1590 -0.0051 0.9600 0.7241 6.2893 4.9467 2.3558 0.4487 0.1998 0.2477 39.3550 0.1794 0.1597 0.2632 0.1766 -0.0006 1.0800 0.7299 6.5583 6.2165 3.8560 0.4501 0.2089 0.2492 42.4926 0.1819 0.1401 0.2606 0.1880 0.0016 1.2000 0.7245 6.8000 6.9570 4.7051 0.4507 0.2038 0.2500 42.6977 0.1812 0.1289 0.2511 0.1918 0.0010 1.3188 0.7109 7.0124 7.2017 4.9608 0.4506 0.1892 0.2503 40.9935 0.1779 0.1205 0.2360 0.1911 -0.0019 1.4178 0.6995 7.1688 7.3810 5.2719 0.4503 0.1774 0.2500 39.6437 0.1749 0.1102 0.2219 0.1914 -0.0044 1.5156 0.6882 7.3050 7.5397 5.6246 0.4499 0.1662 0.2493 38.3705 0.1716 0.0994 0.2078 0.1919 -0.0067 1.6134 0.6767 7.4231 7.6799 5.9743 0.4493 0.1553 0.2483 37.1470 0.1680 0.0898 0.1946 0.1925 -0.0087 1.7112 0.6652 7.5230 7.8014 6.2900 0.4485 0.1449 0.2468 35.9643 0.1642 0.0826 0.1832 0.1926 -0.0099 1.8090 0.6535 7.6048 7.9043 6.5650 0.4475 0.1349 0.2449 34.8151 0.1601 0.0778 0.1736 0.1924 -0.0103 1.9068 0.6417 7.6683 7.9883 6.8151 0.4463 0.1253 0.2426 33.6935 0.1557 0.0744 0.1655 0.1919 -0.0101 2.0046 0.6296 7.7137 8.0533 7.0555 0.4448 0.1160 0.2399 32.5943 0.1511 0.0709 0.1578 0.1915 -0.0099 2.1024 0.6172 7.7410 8.0992 7.2759 0.4430 0.1072 0.2368 31.5132 0.1462 0.0674 0.1503 0.1913 -0.0097 2.2002 0.6046 7.7500 8.1259 7.4629 0.4409 0.0988 0.2333 30.4468 0.1411 0.0638 0.1428 0.1914 -0.0096 2.2980 0.5916 7.7500 8.1422 7.6102 0.4384 0.0908 0.2294 29.4191 0.1357 0.0602 0.1352 0.1918 -0.0100 2.3958 0.5782 7.7500 8.1572 7.7112 0.4357 0.0833 0.2251 28.4526 0.1301 0.0564 0.1274 0.1927 -0.0108 2.4936 0.5645 7.7500 8.1706 7.7511 0.4325 0.0762 0.2203 27.5415 0.1244 0.0526 0.1192 0.1941 -0.0122 2.5914 0.5502 7.7500 8.1824 7.7511 0.4290 0.0695 0.2154 26.6808 0.1185 0.0489 0.1109 0.1956 -0.0140 2.6892 0.5355 7.7500 8.1923 7.7510 0.4250 0.0631 0.2104 25.8660 0.1127 0.0452 0.1027 0.1971 -0.0157 2.7870 0.5202 7.7500 8.2003 7.7509 0.4206 0.0570 0.2055 25.0930 0.1069 0.0417 0.0948 0.1985 -0.0174 2.8848 0.5043 7.7500 8.2063 7.7508 0.4157 0.0511 0.2005 24.3580 0.1011 0.0382 0.0871 0.1997 -0.0190 2.9826 0.4879 7.7500 8.2099 7.7508 0.4104 0.0455 0.1956 23.6576 0.0954 0.0349 0.0796 0.2008 -0.0205 3.0804 0.4708 7.7500 8.2111 7.7507 0.4046 0.0401 0.1906 22.9885 0.0897 0.0317 0.0723 0.2017 -0.0219 3.1782 0.4530 7.7500 8.2095 7.7507 0.3982 0.0350 0.1857 22.3477 0.0841 0.0286 0.0652 0.2024 -0.0233 3.2760 0.4345 7.7500 8.2048 7.7506 0.3913 0.0301 0.1807 21.7322 0.0785 0.0256 0.0584 0.2030 -0.0245 3.3738 0.4152 7.7500 8.1965 7.7505 0.3838 0.0254 0.1757 21.1392 0.0730 0.0228 0.0517 0.2033 -0.0256 3.4716 0.3951 7.7500 8.1841 7.7504 0.3758 0.0210 0.1708 20.5658 0.0675 0.0201 0.0453 0.2034 -0.0266 3.5694 0.3742 7.7500 8.1670 7.7504 0.3671 0.0167 0.1658 20.0092 0.0621 0.0176 0.0391 0.2032 -0.0274 3.6672 0.3524 7.7500 8.1443 7.7503 0.3578 0.0127 0.1609 19.4661 0.0567 0.0152 0.0330 0.2028 -0.0282 3.7650 0.3297 7.7500 8.1146 7.7503 0.3479 0.0089 0.1559 18.9330 0.0514 0.0129 0.0272 0.2022 -0.0288 3.8628 0.3061 7.7500 8.0765 7.7502 0.3372 0.0052 0.1510 18.4055 0.0462 0.0108 0.0217 0.2012 -0.0292 3.9606 0.2814 7.7500 8.0274 7.7501 0.3259 0.0018 0.1460 17.8783 0.0411 0.0089 0.0163 0.2000 -0.0295 4.0584 0.2557 7.7210 7.9349 7.7211 0.3139 -0.0015 0.1411 17.2848 0.0361 0.0072 0.0111 0.1985 -0.0296 4.1523 0.2301 7.5534 7.6885 7.5534 0.3016 -0.0047 0.1363 16.4199 0.0314 0.0057 0.0064 0.1966 -0.0292 4.1783 0.2227 7.4804 7.5897 7.4804 0.2981 -0.0056 0.1350 16.1242 0.0301 0.0053 0.0051 0.1960 -0.0290 4.2004 0.2165 7.4095 7.4952 7.4095 0.2951 -0.0063 0.1339 15.8542 0.0290 0.0050 0.0040 0.1955 -0.0288 4.2225 0.2102 7.3302 7.3908 7.3303 0.2920 -0.0070 0.1327 15.5664 0.0279 0.0047 0.0030 0.1950 -0.0286 4.2446 0.2038 7.2427 7.2764 7.2428 0.2889 -0.0077 0.1316 15.2608 0.0268 0.0044 0.0019 0.1945 -0.0283 4.2667 0.1957 7.1470 7.1518 7.1470 0.2841 -0.0089 0.1305 14.9370 0.0255 0.0040 0.0003 0.1931 -0.0284 4.2888 0.1832 7.0429 7.0165 7.0479 0.2751 -0.0112 0.1294 14.5945 0.0237 0.0035 -0.0026 0.1895 -0.0292 4.3109 0.1650 6.9306 6.8704 6.9975 0.2606 -0.0149 0.1283 14.2328 0.0212 0.0028 -0.0072 0.1829 -0.0309 4.3330 0.1381 6.8100 6.7129 7.0225 0.2377 -0.0207 0.1271 13.8511 0.0176 0.0020 -0.0142 0.1719 -0.0339 4.3551 0.0876 6.6811 6.5434 7.4803 0.1919 -0.0321 0.1260 13.4484 0.0110 0.0008 -0.0279 0.1488 -0.0406 4.3750 0.0083 6.5581 6.5581 6.5581 0.1177 -0.0500 0.1250 13.4183 0.0010 0.0000 -0.0500 0.0000 0.0000 RADIUS: 4.38 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) = 0.056147 TOTAL WEIGHT (Kg) = 0.025464 TOTAL VOLUME (IN**3) = 0.914708 TOTAL PROJECTED AREA (IN**2) = 4.2852 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000278 MOMENT OF INERTIA (Kg-M**2) = 0.000031 STATIC MOMENT, ONE SIDE (IN-LB) = 0.028950 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 = 65.994 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 39030.30 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.