8.75x7.0N (875x70N.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 2.8473 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2200 0.0000 0.0000 0.1200 0.8621 3.2879 -0.4847 -1.0045 0.4452 0.0095 0.2204 -32.7343 0.1900 0.3762 0.2247 0.0130 -0.0337 0.2400 0.8234 3.7039 -0.3812 -1.4747 0.4424 0.0350 0.2262 -14.1879 0.1862 0.3641 0.2372 0.0306 -0.0275 0.3600 0.7900 4.0952 -0.1124 -1.7710 0.4414 0.0717 0.2313 -2.8458 0.1827 0.3427 0.2543 0.0505 -0.0163 0.4800 0.7682 4.4617 0.3829 -1.7545 0.4416 0.1155 0.2358 7.2363 0.1811 0.3136 0.2743 0.0713 -0.0011 0.6000 0.7616 4.8035 1.1407 -1.3306 0.4429 0.1620 0.2397 16.8342 0.1826 0.2810 0.2954 0.0919 0.0161 0.7200 0.7698 5.1206 2.1556 -0.4662 0.4447 0.2071 0.2430 25.4778 0.1871 0.2484 0.3159 0.1110 0.0336 0.8400 0.7878 5.4130 3.3627 0.7773 0.4467 0.2465 0.2457 32.5027 0.1935 0.2185 0.3339 0.1274 0.0498 0.9600 0.8077 5.6807 4.6198 2.2127 0.4487 0.2762 0.2477 37.4486 0.2001 0.1934 0.3469 0.1400 0.0629 1.0800 0.8208 5.9237 5.7043 3.5133 0.4501 0.2919 0.2492 40.0509 0.2045 0.1746 0.3519 0.1475 0.0715 1.2000 0.8202 6.1420 6.3361 4.2394 0.4507 0.2894 0.2500 40.0420 0.2051 0.1636 0.3459 0.1490 0.0738 1.3188 0.8092 6.3338 6.5601 4.4709 0.4506 0.2747 0.2503 38.3672 0.2025 0.1546 0.3310 0.1472 0.0714 1.4178 0.7993 6.4750 6.7248 4.7535 0.4503 0.2627 0.2500 37.0486 0.1998 0.1425 0.3166 0.1468 0.0691 1.5156 0.7888 6.5981 6.8706 5.0736 0.4499 0.2512 0.2493 35.8100 0.1967 0.1294 0.3019 0.1470 0.0671 1.6134 0.7777 6.7048 6.9996 5.3908 0.4493 0.2401 0.2483 34.6241 0.1931 0.1177 0.2883 0.1474 0.0655 1.7112 0.7660 6.7950 7.1116 5.6771 0.4485 0.2294 0.2468 33.4817 0.1890 0.1089 0.2765 0.1476 0.0648 1.8090 0.7536 6.8688 7.2065 5.9267 0.4475 0.2191 0.2449 32.3754 0.1846 0.1030 0.2670 0.1475 0.0651 1.9068 0.7406 6.9262 7.2842 6.1536 0.4463 0.2091 0.2426 31.2989 0.1797 0.0986 0.2589 0.1474 0.0660 2.0046 0.7270 6.9672 7.3445 6.3717 0.4448 0.1995 0.2399 30.2470 0.1744 0.0941 0.2512 0.1476 0.0669 2.1024 0.7127 6.9918 7.3874 6.5715 0.4430 0.1903 0.2368 29.2154 0.1688 0.0894 0.2435 0.1482 0.0676 2.2002 0.6978 7.0000 7.4127 6.7408 0.4409 0.1814 0.2333 28.2003 0.1628 0.0846 0.2356 0.1493 0.0681 2.2980 0.6823 7.0000 7.4284 6.8739 0.4384 0.1729 0.2294 27.2246 0.1565 0.0796 0.2275 0.1509 0.0680 2.3958 0.6661 7.0000 7.4427 6.9650 0.4357 0.1648 0.2251 26.3086 0.1499 0.0745 0.2189 0.1530 0.0673 2.4936 0.6493 7.0000 7.4553 7.0009 0.4325 0.1571 0.2203 25.4467 0.1431 0.0693 0.2097 0.1558 0.0657 2.5914 0.6318 7.0000 7.4663 7.0009 0.4290 0.1497 0.2154 24.6337 0.1361 0.0641 0.2002 0.1588 0.0637 2.6892 0.6137 7.0000 7.4755 7.0009 0.4250 0.1424 0.2104 23.8655 0.1291 0.0591 0.1907 0.1618 0.0616 2.7870 0.5949 7.0000 7.4830 7.0008 0.4206 0.1353 0.2055 23.1380 0.1223 0.0542 0.1814 0.1647 0.0594 2.8848 0.5755 7.0000 7.4885 7.0007 0.4157 0.1284 0.2005 22.4473 0.1154 0.0495 0.1722 0.1676 0.0571 2.9826 0.5555 7.0000 7.4919 7.0007 0.4104 0.1217 0.1956 21.7901 0.1086 0.0450 0.1630 0.1703 0.0547 3.0804 0.5348 7.0000 7.4930 7.0006 0.4046 0.1150 0.1906 21.1632 0.1019 0.0407 0.1539 0.1728 0.0523 3.1782 0.5135 7.0000 7.4915 7.0006 0.3982 0.1085 0.1857 20.5636 0.0953 0.0366 0.1450 0.1752 0.0498 3.2760 0.4915 7.0000 7.4873 7.0005 0.3913 0.1021 0.1807 19.9886 0.0888 0.0327 0.1361 0.1773 0.0472 3.3738 0.4689 7.0000 7.4798 7.0004 0.3838 0.0957 0.1757 19.4353 0.0824 0.0289 0.1273 0.1791 0.0446 3.4716 0.4457 7.0000 7.4688 7.0004 0.3758 0.0895 0.1708 18.9012 0.0761 0.0255 0.1187 0.1806 0.0419 3.5694 0.4217 7.0000 7.4535 7.0003 0.3671 0.0833 0.1658 18.3837 0.0699 0.0222 0.1101 0.1818 0.0391 3.6672 0.3972 7.0000 7.4334 7.0003 0.3578 0.0772 0.1609 17.8799 0.0639 0.0192 0.1016 0.1827 0.0363 3.7650 0.3720 7.0000 7.4075 7.0002 0.3479 0.0711 0.1559 17.3868 0.0580 0.0163 0.0932 0.1832 0.0335 3.8628 0.3461 7.0000 7.3745 7.0002 0.3372 0.0651 0.1510 16.9008 0.0523 0.0138 0.0849 0.1833 0.0306 3.9606 0.3196 7.0000 7.3326 7.0001 0.3259 0.0591 0.1460 16.4179 0.0467 0.0114 0.0767 0.1829 0.0277 4.0584 0.2925 6.9738 7.2535 6.9739 0.3139 0.0531 0.1411 15.8784 0.0413 0.0093 0.0686 0.1821 0.0248 4.1523 0.2658 6.8223 7.0377 6.8224 0.3016 0.0472 0.1363 15.0962 0.0362 0.0075 0.0609 0.1807 0.0223 4.1783 0.2583 6.7564 6.9510 6.7564 0.2981 0.0456 0.1350 14.8298 0.0349 0.0070 0.0587 0.1802 0.0217 4.2004 0.2518 6.6923 6.8683 6.6923 0.2951 0.0442 0.1339 14.5870 0.0337 0.0067 0.0569 0.1798 0.0211 4.2225 0.2454 6.6207 6.7769 6.6207 0.2919 0.0428 0.1327 14.3288 0.0326 0.0063 0.0551 0.1793 0.0206 4.2446 0.2367 6.5416 6.6770 6.5418 0.2867 0.0408 0.1316 14.0555 0.0312 0.0058 0.0527 0.1777 0.0197 4.2667 0.2244 6.4551 6.5684 6.4555 0.2779 0.0379 0.1305 13.7668 0.0293 0.0052 0.0491 0.1743 0.0183 4.2888 0.2076 6.3611 6.4508 6.3964 0.2648 0.0340 0.1294 13.4624 0.0269 0.0044 0.0444 0.1684 0.0161 4.3109 0.1849 6.2596 6.3241 6.3632 0.2459 0.0287 0.1283 13.1420 0.0237 0.0035 0.0379 0.1595 0.0130 4.3330 0.1522 6.1506 6.1880 6.4060 0.2173 0.0213 0.1271 12.8053 0.0194 0.0024 0.0289 0.1453 0.0084 4.3551 0.0890 6.0342 6.0424 6.9587 0.1588 0.0070 0.1260 12.4519 0.0112 0.0008 0.0115 0.1153 -0.0007 4.3750 0.0100 5.9230 5.9230 5.9230 0.0846 -0.0102 0.1250 12.1594 0.0013 0.0000 -0.0102 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) = 0.064885 TOTAL WEIGHT (Kg) = 0.029426 TOTAL VOLUME (IN**3) = 1.057057 TOTAL PROJECTED AREA (IN**2) = 4.8376 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000357 MOMENT OF INERTIA (Kg-M**2) = 0.000040 STATIC MOMENT, ONE SIDE (IN-LB) = 0.036162 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) = 43896.31 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.