7.8x7 (78x7.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 6.0320 -0.5000 -0.5000 0.4500 0.0000 0.2531 0.0000 0.2278 0.0000 0.2000 0.0000 0.0000 0.1200 0.8593 6.1347 -0.4852 -1.0500 0.4452 0.0070 0.2546 -32.7631 0.2188 0.3781 0.2026 0.0138 -0.0560 0.2400 0.8128 6.2317 -0.3845 -1.5727 0.4424 0.0259 0.2558 -14.3031 0.2079 0.3605 0.2096 0.0352 -0.0540 0.3600 0.7679 6.3229 -0.1179 -1.9304 0.4414 0.0530 0.2565 -2.9831 0.1970 0.3327 0.2188 0.0604 -0.0487 0.4800 0.7320 6.4083 0.3867 -1.9736 0.4416 0.0851 0.2568 7.3063 0.1880 0.2973 0.2293 0.0874 -0.0407 0.6000 0.7108 6.4880 1.1845 -1.5795 0.4429 0.1190 0.2567 17.4431 0.1825 0.2589 0.2398 0.1146 -0.0312 0.7200 0.7056 6.5619 2.2931 -0.6747 0.4447 0.1514 0.2562 26.8798 0.1808 0.2217 0.2496 0.1401 -0.0215 0.8400 0.7123 6.6301 3.6572 0.7124 0.4467 0.1793 0.2553 34.7190 0.1819 0.1885 0.2573 0.1623 -0.0127 0.9600 0.7233 6.6925 5.1075 2.3820 0.4487 0.1995 0.2540 40.2566 0.1837 0.1612 0.2615 0.1793 -0.0056 1.0800 0.7296 6.7491 6.3397 3.9132 0.4501 0.2087 0.2522 43.0534 0.1840 0.1411 0.2601 0.1896 -0.0008 1.2000 0.7245 6.8000 6.9565 4.7043 0.4507 0.2038 0.2500 42.6956 0.1812 0.1289 0.2511 0.1918 0.0010 1.3180 0.7114 6.8444 7.0333 4.8538 0.4506 0.1896 0.2475 40.3409 0.1761 0.1187 0.2355 0.1896 0.0002 1.4022 0.7018 6.8727 7.0800 5.0542 0.4504 0.1797 0.2455 38.7848 0.1723 0.1082 0.2228 0.1890 -0.0007 1.4845 0.6924 6.8976 7.1220 5.2852 0.4501 0.1704 0.2433 37.3643 0.1684 0.0975 0.2103 0.1889 -0.0017 1.5667 0.6829 6.9198 7.1606 5.5118 0.4496 0.1614 0.2409 36.0326 0.1645 0.0883 0.1986 0.1889 -0.0025 1.6490 0.6734 6.9393 7.1958 5.7095 0.4491 0.1527 0.2383 34.7811 0.1604 0.0814 0.1885 0.1887 -0.0028 1.7312 0.6636 6.9560 7.2276 5.8738 0.4484 0.1443 0.2355 33.6024 0.1563 0.0771 0.1802 0.1882 -0.0024 1.8134 0.6538 6.9701 7.2560 6.0256 0.4475 0.1361 0.2325 32.4896 0.1520 0.0739 0.1732 0.1877 -0.0016 1.8957 0.6438 6.9815 7.2810 6.1834 0.4464 0.1283 0.2293 31.4368 0.1476 0.0708 0.1665 0.1873 -0.0010 1.9779 0.6337 6.9901 7.3025 6.3430 0.4452 0.1208 0.2260 30.4384 0.1432 0.0677 0.1600 0.1872 -0.0004 2.0602 0.6233 6.9961 7.3205 6.4992 0.4438 0.1136 0.2224 29.4895 0.1386 0.0646 0.1536 0.1872 -0.0001 2.1424 0.6128 6.9993 7.3350 6.6459 0.4421 0.1067 0.2186 28.5858 0.1340 0.0615 0.1473 0.1875 0.0001 2.2247 0.6020 7.0000 7.3460 6.7759 0.4403 0.1001 0.2147 27.7237 0.1292 0.0584 0.1410 0.1879 0.0000 2.3069 0.5910 7.0000 7.3554 6.8831 0.4382 0.0937 0.2105 26.9057 0.1244 0.0552 0.1346 0.1887 -0.0005 2.3891 0.5797 7.0000 7.3638 6.9598 0.4359 0.0876 0.2062 26.1301 0.1195 0.0521 0.1280 0.1897 -0.0013 2.4714 0.5681 7.0000 7.3712 6.9980 0.4333 0.0818 0.2017 25.3936 0.1146 0.0490 0.1212 0.1910 -0.0025 2.5536 0.5562 7.0000 7.3774 7.0007 0.4304 0.0763 0.1970 24.6929 0.1096 0.0458 0.1141 0.1924 -0.0041 2.6359 0.5439 7.0000 7.3824 7.0007 0.4272 0.0709 0.1923 24.0250 0.1046 0.0428 0.1072 0.1939 -0.0057 2.7181 0.5313 7.0000 7.3859 7.0006 0.4237 0.0657 0.1876 23.3871 0.0997 0.0398 0.1004 0.1952 -0.0073 2.8003 0.5183 7.0000 7.3880 7.0006 0.4200 0.0607 0.1829 22.7770 0.0948 0.0370 0.0938 0.1964 -0.0088 2.8826 0.5050 7.0000 7.3885 7.0005 0.4159 0.0559 0.1782 22.1923 0.0900 0.0342 0.0873 0.1976 -0.0104 2.9648 0.4912 7.0000 7.3872 7.0005 0.4114 0.0512 0.1735 21.6310 0.0852 0.0315 0.0810 0.1986 -0.0118 3.0471 0.4769 7.0000 7.3842 7.0004 0.4066 0.0467 0.1688 21.0912 0.0805 0.0289 0.0748 0.1995 -0.0132 3.1293 0.4622 7.0000 7.3791 7.0004 0.4015 0.0423 0.1641 20.5711 0.0758 0.0264 0.0687 0.2002 -0.0146 3.2116 0.4470 7.0000 7.3770 6.9879 0.3959 0.0382 0.1594 20.0815 0.0712 0.0241 0.0628 0.2008 -0.0160 3.2938 0.4314 7.0000 7.3975 6.9415 0.3900 0.0347 0.1547 19.6691 0.0667 0.0218 0.0572 0.2013 -0.0176 3.3760 0.4156 7.0000 7.4546 6.8770 0.3837 0.0321 0.1500 19.3629 0.0623 0.0196 0.0519 0.2016 -0.0191 3.4583 0.3994 7.0000 7.5603 6.8111 0.3769 0.0302 0.1453 19.1846 0.0580 0.0175 0.0474 0.2017 -0.0203 3.5405 0.3828 6.9892 7.7137 6.7483 0.3697 0.0293 0.1406 19.1241 0.0538 0.0155 0.0437 0.2016 -0.0213 3.6228 0.3659 6.9011 7.8544 6.6367 0.3621 0.0289 0.1359 19.0374 0.0497 0.0137 0.0408 0.2012 -0.0214 3.7017 0.3467 6.7329 7.9693 6.4842 0.3522 0.0283 0.1314 18.9133 0.0456 0.0118 0.0379 0.1993 -0.0214 3.7247 0.3369 6.6687 7.9993 6.4333 0.3453 0.0268 0.1301 18.8709 0.0438 0.0110 0.0356 0.1966 -0.0221 3.7444 0.3260 6.6081 8.0238 6.3946 0.3371 0.0247 0.1289 18.8320 0.0420 0.0102 0.0328 0.1931 -0.0231 3.7641 0.3126 6.5423 8.0469 6.3709 0.3265 0.0217 0.1278 18.7905 0.0400 0.0093 0.0292 0.1883 -0.0246 3.7838 0.2962 6.4715 8.0685 6.3560 0.3132 0.0178 0.1267 18.7462 0.0375 0.0083 0.0246 0.1819 -0.0265 3.8035 0.2761 6.3956 8.0885 6.3556 0.2963 0.0127 0.1256 18.6988 0.0347 0.0072 0.0187 0.1737 -0.0291 3.8232 0.2510 6.3146 8.1066 6.3815 0.2748 0.0060 0.1244 18.6479 0.0312 0.0059 0.0112 0.1629 -0.0325 3.8429 0.2180 6.2285 8.1228 6.4645 0.2458 -0.0034 0.1233 18.5936 0.0269 0.0044 0.0009 0.1480 -0.0372 3.8626 0.1671 6.1374 8.1374 6.7401 0.2000 -0.0187 0.1222 18.5361 0.0204 0.0026 -0.0155 0.1242 -0.0451 3.8823 0.0874 6.0411 8.1506 7.9762 0.1269 -0.0435 0.1211 18.4764 0.0106 0.0007 -0.0419 0.0856 -0.0580 3.9000 0.0148 5.9501 5.9501 5.9501 0.0608 -0.0672 0.1201 13.6482 0.0018 0.0000 -0.0672 0.0000 0.0000 RADIUS: 3.90 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) = 0.054842 TOTAL WEIGHT (Kg) = 0.024872 TOTAL VOLUME (IN**3) = 0.893452 TOTAL PROJECTED AREA (IN**2) = 4.0922 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000239 MOMENT OF INERTIA (Kg-M**2) = 0.000027 STATIC MOMENT, ONE SIDE (IN-LB) = 0.026640 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 = 90.421 INNER LIMIT (NORMALIZED BY RADIUS) = 0.115 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 46092.79 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.