9x7.5SF (9x75SF.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 0.0920 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0400 0.0000 0.0000 0.0800 0.4760 0.6728 0.0102 -0.3624 0.2498 0.0049 0.0964 1.1643 0.0459 0.0885 0.0438 0.0092 -0.0612 0.1600 0.4539 1.2299 0.0805 -0.7050 0.2566 0.0185 0.0922 4.5785 0.0418 0.0877 0.0545 0.0278 -0.0564 0.2400 0.4375 1.7632 0.2662 -0.9575 0.2691 0.0389 0.0881 10.0100 0.0386 0.0872 0.0696 0.0513 -0.0491 0.3200 0.4311 2.2729 0.6125 -0.9580 0.2863 0.0642 0.0842 16.9437 0.0363 0.0814 0.0858 0.0783 -0.0394 0.4000 0.4376 2.7589 1.1440 -0.5978 0.3069 0.0928 0.0805 24.4750 0.0352 0.0722 0.1059 0.1071 -0.0280 0.4800 0.4574 3.2211 1.8516 0.1568 0.3299 0.1229 0.0770 31.5475 0.0352 0.0617 0.1303 0.1359 -0.0151 0.5600 0.4882 3.6597 2.6825 1.2425 0.3541 0.1527 0.0737 37.3212 0.0360 0.0515 0.1570 0.1632 -0.0011 0.6400 0.5260 4.0745 3.5399 2.4881 0.3784 0.1805 0.0705 41.3573 0.0371 0.0428 0.1834 0.1874 0.0136 0.7200 0.5668 4.4657 4.2981 3.6204 0.4017 0.2046 0.0676 43.5336 0.0383 0.0368 0.2069 0.2067 0.0280 0.8000 0.6071 4.8331 4.8316 4.3403 0.4228 0.2233 0.0648 43.8671 0.0393 0.0353 0.2254 0.2177 0.0396 0.8819 0.6465 5.1849 5.1849 4.7473 0.4423 0.2376 0.0621 43.0965 0.0401 0.0372 0.2399 0.2216 0.0475 0.9971 0.6988 5.6371 5.6371 5.2810 0.4678 0.2547 0.0587 41.9813 0.0410 0.0393 0.2573 0.2253 0.0571 1.1141 0.7484 6.0466 6.0466 5.7746 0.4914 0.2687 0.0555 40.8193 0.0416 0.0406 0.2716 0.2274 0.0654 1.2312 0.7943 6.4054 6.4054 6.2114 0.5128 0.2794 0.0528 39.6250 0.0420 0.0413 0.2826 0.2278 0.0722 1.3483 0.8365 6.7134 6.7134 6.5863 0.5319 0.2870 0.0505 38.3957 0.0422 0.0413 0.2906 0.2265 0.0776 1.4653 0.8748 6.9706 6.9706 6.8993 0.5488 0.2918 0.0485 37.1292 0.0425 0.0408 0.2957 0.2239 0.0818 1.5824 0.9094 7.1771 7.1771 7.1480 0.5635 0.2937 0.0470 35.8236 0.0427 0.0400 0.2980 0.2199 0.0849 1.6995 0.9400 7.3327 7.3327 7.3363 0.5759 0.2930 0.0458 34.4776 0.0430 0.0390 0.2978 0.2148 0.0870 1.8166 0.9666 7.4377 7.4377 7.4672 0.5860 0.2899 0.0450 33.0900 0.0435 0.0380 0.2951 0.2089 0.0884 1.9336 0.9892 7.4918 7.4918 7.5409 0.5939 0.2845 0.0446 31.6600 0.0441 0.0371 0.2902 0.2024 0.0890 2.0507 1.0077 7.5000 7.5000 7.5578 0.5995 0.2770 0.0445 30.2028 0.0448 0.0364 0.2832 0.1956 0.0891 2.1678 1.0221 7.5000 7.5000 7.5640 0.6028 0.2676 0.0445 28.8391 0.0455 0.0359 0.2743 0.1889 0.0877 2.2848 1.0323 7.5000 7.5000 7.5679 0.6040 0.2563 0.0445 27.5839 0.0459 0.0355 0.2636 0.1822 0.0845 2.4019 1.0383 7.5000 7.5000 7.5697 0.6028 0.2435 0.0445 26.4258 0.0462 0.0353 0.2514 0.1756 0.0798 2.5190 1.0399 7.5000 7.5000 7.5692 0.5994 0.2292 0.0445 25.3549 0.0463 0.0352 0.2377 0.1690 0.0735 2.6360 1.0372 7.5000 7.5000 7.5684 0.5938 0.2137 0.0445 24.3622 0.0462 0.0350 0.2228 0.1621 0.0660 2.7531 1.0301 7.5000 7.5000 7.5682 0.5859 0.1972 0.0445 23.4401 0.0458 0.0345 0.2068 0.1551 0.0575 2.8702 1.0185 7.5000 7.5000 7.5686 0.5757 0.1798 0.0445 22.5817 0.0453 0.0337 0.1899 0.1477 0.0480 2.9872 1.0024 7.5000 7.5000 7.5696 0.5633 0.1617 0.0445 21.7810 0.0446 0.0327 0.1722 0.1402 0.0378 3.1043 0.9817 7.5000 7.5000 7.5714 0.5486 0.1431 0.0445 21.0326 0.0437 0.0314 0.1540 0.1324 0.0271 3.2214 0.9564 7.5000 7.5000 7.5740 0.5317 0.1242 0.0445 20.3319 0.0426 0.0298 0.1352 0.1244 0.0159 3.3384 0.9263 7.5000 7.5000 7.5775 0.5126 0.1051 0.0445 19.6745 0.0412 0.0280 0.1163 0.1161 0.0045 3.4555 0.8916 7.5000 7.5000 7.5824 0.4911 0.0860 0.0445 19.0568 0.0397 0.0261 0.0973 0.1077 -0.0071 3.5726 0.8520 7.5000 7.5000 7.5888 0.4675 0.0670 0.0445 18.4754 0.0379 0.0239 0.0783 0.0990 -0.0185 3.6897 0.8075 7.5000 7.5000 7.5964 0.4415 0.0485 0.0445 17.9272 0.0359 0.0216 0.0596 0.0902 -0.0297 3.8067 0.7582 7.5000 7.5000 7.6064 0.4133 0.0305 0.0445 17.4097 0.0337 0.0192 0.0413 0.0812 -0.0405 3.9238 0.7038 7.5000 7.5000 7.6198 0.3829 0.0131 0.0445 16.9204 0.0313 0.0167 0.0235 0.0722 -0.0507 4.0409 0.6444 7.5000 7.5000 7.6373 0.3502 -0.0033 0.0445 16.4570 0.0287 0.0141 0.0065 0.0630 -0.0602 4.1579 0.5800 7.5000 7.5000 7.6607 0.3153 -0.0188 0.0445 16.0178 0.0258 0.0116 -0.0096 0.0538 -0.0687 4.2701 0.5090 7.5000 7.5000 7.6917 0.2755 -0.0336 0.0445 15.6178 0.0227 0.0091 -0.0253 0.0428 -0.0767 4.2977 0.4853 7.5000 7.5000 7.7011 0.2600 -0.0385 0.0445 15.5222 0.0216 0.0083 -0.0305 0.0373 -0.0795 4.3205 0.4629 7.5000 7.5000 7.7095 0.2446 -0.0432 0.0445 15.4445 0.0206 0.0076 -0.0355 0.0315 -0.0822 4.3432 0.4374 7.5000 7.5000 7.7188 0.2264 -0.0485 0.0445 15.3675 0.0195 0.0068 -0.0413 0.0242 -0.0853 4.3659 0.4082 7.5000 7.5000 7.7289 0.2046 -0.0548 0.0445 15.2913 0.0182 0.0060 -0.0480 0.0152 -0.0890 4.3886 0.3740 7.5000 7.5000 7.7491 0.1782 -0.0621 0.0445 15.2158 0.0166 0.0051 -0.0558 0.0037 -0.0936 4.4114 0.3330 7.5000 7.5000 7.7928 0.1452 -0.0712 0.0445 15.1410 0.0148 0.0041 -0.0655 -0.0115 -0.0994 4.4341 0.2800 7.5000 7.5000 7.8689 0.1009 -0.0831 0.0445 15.0669 0.0125 0.0029 -0.0783 -0.0327 -0.1072 4.4568 0.1986 7.5000 7.5000 8.0670 0.0290 -0.1022 0.0445 14.9935 0.0088 0.0015 -0.0988 -0.0683 -0.1200 4.4795 0.1036 7.5000 7.5000 8.6912 -0.0558 -0.1245 0.0445 14.9209 0.0046 0.0005 -0.1227 -0.1102 -0.1349 4.5000 0.0181 7.5000 7.5038 7.5038 -0.1321 -0.1444 0.0445 14.8632 0.0008 0.0000 -0.1444 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.020231 TOTAL WEIGHT (Kg) = 0.009175 TOTAL VOLUME (IN**3) = 0.329591 TOTAL PROJECTED AREA (IN**2) = 6.2036 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000222 MOMENT OF INERTIA (Kg-M**2) = 0.000025 STATIC MOMENT, ONE SIDE (IN-LB) = 0.016856 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 = 129.925 INNER LIMIT (NORMALIZED BY RADIUS) = 0.056 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6185.72 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.