8.75x7.5N (875x75N.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 3.0472 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2200 0.0000 0.0000 0.1200 0.8615 3.5197 -0.4843 -1.0051 0.4452 0.0095 0.2204 -32.7118 0.1899 0.3762 0.2247 0.0133 -0.0339 0.2400 0.8214 3.9657 -0.3777 -1.4775 0.4424 0.0352 0.2262 -14.0627 0.1858 0.3641 0.2372 0.0316 -0.0283 0.3600 0.7864 4.3852 -0.0997 -1.7760 0.4414 0.0721 0.2313 -2.5245 0.1819 0.3426 0.2544 0.0525 -0.0176 0.4800 0.7631 4.7783 0.4158 -1.7572 0.4416 0.1161 0.2358 7.8491 0.1799 0.3133 0.2743 0.0744 -0.0031 0.6000 0.7560 5.1448 1.2102 -1.3188 0.4429 0.1629 0.2397 17.7975 0.1812 0.2806 0.2954 0.0961 0.0134 0.7200 0.7646 5.4848 2.2833 -0.4199 0.4447 0.2083 0.2430 26.7811 0.1858 0.2479 0.3160 0.1162 0.0301 0.8400 0.7838 5.7984 3.5702 0.8833 0.4467 0.2481 0.2457 34.0765 0.1925 0.2181 0.3340 0.1335 0.0453 0.9600 0.8050 6.0854 4.9200 2.3984 0.4487 0.2780 0.2477 39.2030 0.1994 0.1931 0.3470 0.1466 0.0576 1.0800 0.8194 6.3460 6.0893 3.7779 0.4501 0.2940 0.2492 41.9035 0.2042 0.1746 0.3521 0.1544 0.0655 1.2000 0.8193 6.5800 6.7699 4.5499 0.4507 0.2917 0.2500 41.9203 0.2049 0.1638 0.3461 0.1557 0.0673 1.3188 0.8085 6.7857 7.0088 4.7973 0.4506 0.2771 0.2503 40.2247 0.2023 0.1549 0.3312 0.1536 0.0649 1.4178 0.7986 6.9371 7.1842 5.0995 0.4503 0.2652 0.2500 38.8846 0.1997 0.1428 0.3169 0.1529 0.0627 1.5156 0.7882 7.0691 7.3393 5.4421 0.4499 0.2538 0.2493 37.6219 0.1965 0.1296 0.3024 0.1528 0.0607 1.6134 0.7772 7.1834 7.4764 5.7818 0.4493 0.2427 0.2483 36.4094 0.1929 0.1178 0.2888 0.1529 0.0593 1.7112 0.7655 7.2802 7.5953 6.0882 0.4485 0.2320 0.2468 35.2382 0.1889 0.1088 0.2770 0.1528 0.0587 1.8090 0.7532 7.3594 7.6959 6.3548 0.4475 0.2217 0.2449 34.1011 0.1845 0.1029 0.2673 0.1523 0.0591 1.9068 0.7402 7.4209 7.7781 6.5969 0.4463 0.2117 0.2426 32.9920 0.1796 0.0985 0.2592 0.1518 0.0602 2.0046 0.7266 7.4649 7.8417 6.8294 0.4448 0.2021 0.2399 31.9057 0.1743 0.0940 0.2514 0.1517 0.0613 2.1024 0.7124 7.4912 7.8866 7.0425 0.4430 0.1928 0.2368 30.8381 0.1687 0.0894 0.2436 0.1519 0.0623 2.2002 0.6976 7.5000 7.9126 7.2231 0.4409 0.1838 0.2333 29.7855 0.1627 0.0845 0.2357 0.1526 0.0630 2.2980 0.6820 7.5000 7.9286 7.3652 0.4384 0.1752 0.2294 28.7718 0.1565 0.0796 0.2275 0.1538 0.0631 2.3958 0.6659 7.5000 7.9430 7.4627 0.4357 0.1671 0.2251 27.8187 0.1499 0.0745 0.2189 0.1557 0.0626 2.4936 0.6491 7.5000 7.9558 7.5011 0.4325 0.1593 0.2203 26.9205 0.1430 0.0693 0.2097 0.1582 0.0613 2.5914 0.6317 7.5000 7.9669 7.5010 0.4290 0.1517 0.2154 26.0724 0.1361 0.0641 0.2002 0.1610 0.0594 2.6892 0.6136 7.5000 7.9763 7.5010 0.4250 0.1444 0.2104 25.2700 0.1291 0.0591 0.1907 0.1638 0.0575 2.7870 0.5948 7.5000 7.9838 7.5009 0.4206 0.1372 0.2055 24.5093 0.1222 0.0542 0.1814 0.1666 0.0555 2.8848 0.5754 7.5000 7.9894 7.5008 0.4157 0.1302 0.2005 23.7865 0.1154 0.0495 0.1722 0.1693 0.0534 2.9826 0.5554 7.5000 7.9928 7.5007 0.4104 0.1234 0.1956 23.0982 0.1086 0.0450 0.1630 0.1719 0.0512 3.0804 0.5347 7.5000 7.9939 7.5007 0.4046 0.1166 0.1906 22.4413 0.1019 0.0407 0.1539 0.1743 0.0489 3.1782 0.5134 7.5000 7.9924 7.5006 0.3982 0.1100 0.1857 21.8128 0.0953 0.0366 0.1450 0.1765 0.0466 3.2760 0.4915 7.5000 7.9881 7.5006 0.3913 0.1035 0.1807 21.2099 0.0888 0.0327 0.1361 0.1785 0.0442 3.3738 0.4689 7.5000 7.9805 7.5005 0.3838 0.0970 0.1757 20.6297 0.0824 0.0289 0.1273 0.1802 0.0417 3.4716 0.4456 7.5000 7.9693 7.5004 0.3758 0.0907 0.1708 20.0696 0.0761 0.0255 0.1187 0.1816 0.0392 3.5694 0.4217 7.5000 7.9539 7.5003 0.3671 0.0844 0.1658 19.5271 0.0699 0.0222 0.1101 0.1828 0.0367 3.6672 0.3972 7.5000 7.9336 7.5003 0.3578 0.0782 0.1609 18.9991 0.0639 0.0192 0.1016 0.1835 0.0340 3.7650 0.3720 7.5000 7.9074 7.5002 0.3479 0.0720 0.1559 18.4827 0.0580 0.0163 0.0932 0.1839 0.0313 3.8628 0.3461 7.5000 7.8741 7.5002 0.3372 0.0659 0.1510 17.9743 0.0523 0.0138 0.0849 0.1839 0.0286 3.9606 0.3196 7.5000 7.8319 7.5002 0.3259 0.0599 0.1460 17.4697 0.0467 0.0114 0.0767 0.1835 0.0258 4.0584 0.2924 7.4720 7.7504 7.4721 0.3139 0.0538 0.1411 16.9060 0.0413 0.0093 0.0686 0.1826 0.0231 4.1523 0.2658 7.3098 7.5234 7.3099 0.3016 0.0478 0.1363 16.0859 0.0362 0.0075 0.0609 0.1812 0.0208 4.1783 0.2582 7.2392 7.4320 7.2393 0.2981 0.0461 0.1350 15.8062 0.0349 0.0070 0.0587 0.1807 0.0202 4.2004 0.2518 7.1706 7.3446 7.1706 0.2951 0.0447 0.1339 15.5512 0.0337 0.0067 0.0570 0.1802 0.0198 4.2225 0.2454 7.0940 7.2480 7.0940 0.2920 0.0433 0.1327 15.2799 0.0326 0.0063 0.0552 0.1797 0.0193 4.2446 0.2368 7.0093 7.1424 7.0095 0.2868 0.0413 0.1316 14.9925 0.0312 0.0058 0.0527 0.1781 0.0184 4.2667 0.2245 6.9167 7.0276 6.9171 0.2781 0.0383 0.1305 14.6889 0.0293 0.0052 0.0491 0.1747 0.0170 4.2888 0.2078 6.8160 6.9033 6.8494 0.2651 0.0342 0.1294 14.3688 0.0269 0.0044 0.0442 0.1689 0.0148 4.3109 0.1851 6.7074 6.7693 6.8092 0.2463 0.0287 0.1283 14.0317 0.0237 0.0035 0.0376 0.1600 0.0116 4.3330 0.1524 6.5907 6.6254 6.8450 0.2177 0.0209 0.1271 13.6774 0.0194 0.0024 0.0281 0.1458 0.0069 4.3551 0.0892 6.4661 6.4714 7.3911 0.1595 0.0058 0.1260 13.3055 0.0112 0.0008 0.0101 0.1160 -0.0025 4.3750 0.0100 6.3470 6.3470 6.3470 0.0853 -0.0125 0.1250 13.0014 0.0013 0.0000 -0.0125 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) = 0.064862 TOTAL WEIGHT (Kg) = 0.029416 TOTAL VOLUME (IN**3) = 1.056688 TOTAL PROJECTED AREA (IN**2) = 4.7685 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000357 MOMENT OF INERTIA (Kg-M**2) = 0.000040 STATIC MOMENT, ONE SIDE (IN-LB) = 0.036153 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 = 75.354 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 43912.98 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.