7x5SF (7x5SF.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 0.5000 5.0000 0.0000 0.0000 0.2500 0.0000 0.0817 0.0000 0.0408 0.0000 0.0500 0.0000 0.0000 0.0580 0.4767 5.0000 0.0073 -0.2704 0.2455 0.0070 0.0799 1.1415 0.0381 0.0944 0.0556 0.0047 -0.0569 0.1160 0.4452 5.0000 0.0582 -0.5381 0.2383 0.0259 0.0782 4.5643 0.0348 0.0907 0.0707 0.0140 -0.0467 0.1740 0.4118 5.0000 0.1996 -0.7799 0.2294 0.0536 0.0765 10.3457 0.0315 0.0867 0.0929 0.0246 -0.0321 0.2320 0.3839 5.0000 0.4855 -0.9404 0.2198 0.0869 0.0749 18.4215 0.0288 0.0807 0.1183 0.0355 -0.0147 0.2900 0.3685 5.0000 0.9755 -0.8180 0.2105 0.1225 0.0734 28.1632 0.0270 0.0688 0.1421 0.0463 0.0039 0.3480 0.3695 5.0000 1.7144 -0.2556 0.2025 0.1575 0.0719 38.0993 0.0266 0.0550 0.1673 0.0560 0.0218 0.4060 0.3854 5.0000 2.6871 0.8167 0.1966 0.1890 0.0704 46.4889 0.0271 0.0423 0.1932 0.0637 0.0376 0.4640 0.4111 5.0000 3.7522 2.2566 0.1936 0.2140 0.0691 52.1533 0.0284 0.0327 0.2160 0.0685 0.0497 0.5220 0.4407 5.0000 4.6235 3.6146 0.1945 0.2298 0.0678 54.6486 0.0299 0.0269 0.2309 0.0697 0.0564 0.5800 0.4704 5.0000 4.9968 4.2722 0.2000 0.2334 0.0665 53.8963 0.0313 0.0258 0.2344 0.0662 0.0551 0.6398 0.4996 5.0000 5.0000 4.3063 0.2089 0.2284 0.0653 51.2005 0.0326 0.0280 0.2296 0.0591 0.0486 0.7307 0.5398 5.0000 5.0000 4.3683 0.2217 0.2206 0.0635 47.4428 0.0343 0.0306 0.2222 0.0490 0.0412 0.8233 0.5755 5.0000 5.0000 4.4487 0.2339 0.2126 0.0619 44.0257 0.0356 0.0325 0.2146 0.0396 0.0360 0.9160 0.6063 5.0000 5.0000 4.5317 0.2452 0.2047 0.0604 40.9835 0.0366 0.0336 0.2071 0.0314 0.0326 1.0086 0.6322 5.0000 5.0000 4.6123 0.2556 0.1969 0.0591 38.2725 0.0373 0.0340 0.1997 0.0246 0.0306 1.1013 0.6536 5.0000 5.0000 4.6871 0.2651 0.1891 0.0579 35.8516 0.0378 0.0337 0.1923 0.0191 0.0295 1.1939 0.6707 5.0000 5.0000 4.7542 0.2737 0.1813 0.0568 33.6841 0.0381 0.0330 0.1850 0.0150 0.0291 1.2866 0.6836 5.0000 5.0000 4.8130 0.2815 0.1736 0.0560 31.7375 0.0383 0.0320 0.1777 0.0121 0.0292 1.3792 0.6927 5.0000 5.0000 4.8632 0.2883 0.1659 0.0552 29.9835 0.0383 0.0307 0.1705 0.0105 0.0294 1.4719 0.6981 5.0000 5.0000 4.9054 0.2942 0.1583 0.0546 28.3977 0.0381 0.0292 0.1633 0.0101 0.0298 1.5646 0.7001 5.0000 5.0000 4.9410 0.2993 0.1507 0.0542 26.9592 0.0379 0.0276 0.1562 0.0106 0.0300 1.6572 0.6988 5.0000 5.0000 4.9706 0.3034 0.1431 0.0537 25.6499 0.0375 0.0260 0.1492 0.0120 0.0302 1.7499 0.6946 5.0000 5.0000 4.9947 0.3066 0.1356 0.0533 24.4543 0.0370 0.0243 0.1422 0.0141 0.0302 1.8425 0.6876 5.0000 5.0000 5.0154 0.3090 0.1283 0.0528 23.3593 0.0363 0.0227 0.1352 0.0168 0.0300 1.9352 0.6781 5.0000 5.0000 5.0336 0.3105 0.1210 0.0523 22.3533 0.0355 0.0210 0.1283 0.0200 0.0296 2.0278 0.6663 5.0000 5.0000 5.0496 0.3110 0.1138 0.0519 21.4264 0.0346 0.0195 0.1215 0.0235 0.0290 2.1205 0.6524 5.0000 5.0000 5.0639 0.3107 0.1068 0.0514 20.5701 0.0335 0.0180 0.1147 0.0272 0.0281 2.2131 0.6366 5.0000 5.0000 5.0748 0.3095 0.0998 0.0509 19.7770 0.0324 0.0166 0.1080 0.0310 0.0270 2.3058 0.6192 5.0000 5.0000 5.0843 0.3074 0.0930 0.0505 19.0406 0.0313 0.0153 0.1013 0.0349 0.0257 2.3984 0.6005 5.0000 5.0000 5.0929 0.3043 0.0862 0.0500 18.3552 0.0300 0.0140 0.0947 0.0385 0.0241 2.4911 0.5805 5.0000 5.0000 5.1011 0.3004 0.0796 0.0495 17.7159 0.0288 0.0129 0.0881 0.0420 0.0223 2.5838 0.5596 5.0000 5.0000 5.1091 0.2956 0.0730 0.0491 17.1184 0.0275 0.0118 0.0816 0.0450 0.0202 2.6764 0.5380 5.0000 5.0000 5.1170 0.2899 0.0666 0.0486 16.5587 0.0262 0.0108 0.0751 0.0477 0.0179 2.7691 0.5158 5.0000 5.0000 5.1241 0.2834 0.0602 0.0482 16.0336 0.0248 0.0099 0.0687 0.0497 0.0155 2.8617 0.4934 5.0000 5.0000 5.1316 0.2759 0.0540 0.0477 15.5399 0.0235 0.0090 0.0624 0.0511 0.0128 2.9544 0.4710 5.0000 5.0000 5.1399 0.2675 0.0478 0.0472 15.0751 0.0222 0.0082 0.0561 0.0517 0.0099 3.0470 0.4487 5.0000 5.0000 5.1492 0.2582 0.0417 0.0468 14.6366 0.0210 0.0074 0.0498 0.0514 0.0069 3.1397 0.4269 5.0000 5.0000 5.1589 0.2481 0.0357 0.0463 14.2225 0.0198 0.0067 0.0436 0.0501 0.0038 3.2323 0.4056 5.0000 5.0000 5.1691 0.2370 0.0297 0.0458 13.8307 0.0186 0.0061 0.0375 0.0477 0.0004 3.3211 0.3694 5.0000 5.0000 5.1797 0.2093 0.0202 0.0454 13.4747 0.0168 0.0050 0.0274 0.0360 -0.0057 3.3427 0.3556 5.0000 5.0000 5.1824 0.1974 0.0167 0.0453 13.3909 0.0161 0.0047 0.0237 0.0303 -0.0080 3.3604 0.3424 5.0000 5.0000 5.1846 0.1858 0.0134 0.0452 13.3229 0.0155 0.0043 0.0202 0.0247 -0.0102 3.3780 0.3272 5.0000 5.0000 5.1932 0.1721 0.0097 0.0451 13.2557 0.0148 0.0040 0.0162 0.0179 -0.0127 3.3957 0.3097 5.0000 5.0000 5.2089 0.1561 0.0055 0.0450 13.1891 0.0139 0.0035 0.0117 0.0096 -0.0157 3.4134 0.2891 5.0000 5.0000 5.2297 0.1371 0.0006 0.0449 13.1232 0.0130 0.0031 0.0064 -0.0003 -0.0192 3.4311 0.2646 5.0000 5.0000 5.2590 0.1140 -0.0052 0.0448 13.0579 0.0119 0.0026 0.0002 -0.0125 -0.0234 3.4487 0.2339 5.0000 5.0000 5.3041 0.0850 -0.0123 0.0448 12.9932 0.0105 0.0021 -0.0075 -0.0278 -0.0285 3.4664 0.1916 5.0000 5.0000 5.3904 0.0445 -0.0219 0.0447 12.9292 0.0086 0.0014 -0.0180 -0.0493 -0.0355 3.4841 0.1105 5.0000 5.0000 5.7423 -0.0339 -0.0401 0.0446 12.8658 0.0049 0.0005 -0.0379 -0.0910 -0.0487 3.5000 0.0175 5.0000 5.0025 5.0025 -0.1242 -0.0608 0.0445 12.8155 0.0008 0.0000 -0.0609 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.58 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.011529 TOTAL WEIGHT (Kg) = 0.005229 TOTAL VOLUME (IN**3) = 0.187828 TOTAL PROJECTED AREA (IN**2) = 3.3696 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000057 MOMENT OF INERTIA (Kg-M**2) = 0.000006 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006144 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 = 110.574 INNER LIMIT (NORMALIZED BY RADIUS) = 0.071 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11836.56 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.00, E63 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.