7.4x7.5C (74x75C.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 2.1414 0.0000 0.0000 0.4500 0.0000 0.3150 0.0000 0.2835 0.0000 0.1000 0.0000 0.0000 0.1100 0.8598 3.0424 0.0121 -0.5561 0.4408 0.0046 0.3035 0.9990 0.2609 0.3305 0.1028 0.0067 -0.1161 0.2200 0.8093 3.8256 0.0948 -1.0922 0.4254 0.0171 0.2926 3.9241 0.2368 0.3149 0.1103 0.0176 -0.1140 0.3300 0.7563 4.4990 0.3167 -1.5107 0.4058 0.0350 0.2822 8.6837 0.2135 0.2907 0.1204 0.0284 -0.1100 0.4400 0.7090 5.0706 0.7454 -1.6850 0.3838 0.0562 0.2724 15.0904 0.1931 0.2586 0.1318 0.0388 -0.1041 0.5500 0.6743 5.5484 1.4432 -1.4905 0.3612 0.0786 0.2631 22.6670 0.1774 0.2233 0.1440 0.0483 -0.0966 0.6600 0.6559 5.9403 2.4473 -0.8156 0.3398 0.1002 0.2542 30.5471 0.1667 0.1884 0.1559 0.0565 -0.0881 0.7700 0.6524 6.2543 3.7311 0.3905 0.3212 0.1188 0.2457 37.6393 0.1603 0.1568 0.1663 0.0630 -0.0789 0.8800 0.6579 6.4983 5.1477 2.0343 0.3072 0.1324 0.2376 42.9534 0.1563 0.1304 0.1735 0.0675 -0.0696 0.9900 0.6648 6.6803 6.3893 3.7878 0.2996 0.1389 0.2298 45.7678 0.1527 0.1099 0.1757 0.0696 -0.0608 1.1000 0.6669 6.8082 7.0366 5.0945 0.3000 0.1362 0.2223 45.5139 0.1482 0.0952 0.1709 0.0690 -0.0533 1.2084 0.6652 6.8891 7.1392 5.7752 0.3057 0.1273 0.2151 43.2371 0.1431 0.0847 0.1614 0.0667 -0.0481 1.2895 0.6638 6.9249 7.1862 6.1583 0.3096 0.1206 0.2099 41.5719 0.1394 0.0783 0.1542 0.0653 -0.0456 1.3690 0.6625 6.9429 7.2141 6.4415 0.3131 0.1140 0.2049 39.9866 0.1358 0.0731 0.1472 0.0642 -0.0440 1.4484 0.6611 6.9470 7.2269 6.6438 0.3163 0.1073 0.2000 38.4529 0.1322 0.0688 0.1403 0.0633 -0.0432 1.5279 0.6598 6.9402 7.2280 6.7769 0.3191 0.1007 0.1952 36.9759 0.1288 0.0653 0.1333 0.0627 -0.0431 1.6074 0.6584 6.9254 7.2203 6.8531 0.3216 0.0941 0.1904 35.5611 0.1253 0.0624 0.1264 0.0623 -0.0436 1.6869 0.6571 6.9058 7.2069 6.8855 0.3238 0.0876 0.1856 34.2140 0.1220 0.0600 0.1194 0.0621 -0.0445 1.7664 0.6558 6.8842 7.1909 6.8855 0.3257 0.0811 0.1809 32.9398 0.1186 0.0580 0.1125 0.0619 -0.0458 1.8459 0.6545 6.8638 7.1752 6.8670 0.3272 0.0747 0.1762 31.7437 0.1153 0.0562 0.1056 0.0618 -0.0475 1.9253 0.6533 6.8474 7.1630 6.8489 0.3284 0.0683 0.1715 30.6304 0.1120 0.0545 0.0987 0.0616 -0.0496 2.0048 0.6521 6.8381 7.1571 6.8385 0.3293 0.0621 0.1667 29.6042 0.1087 0.0527 0.0918 0.0614 -0.0520 2.0843 0.6510 6.8389 7.1607 6.8394 0.3298 0.0559 0.1620 28.6689 0.1054 0.0510 0.0848 0.0610 -0.0546 2.1638 0.6499 6.8528 7.1766 6.8533 0.3300 0.0499 0.1572 27.8280 0.1021 0.0494 0.0780 0.0604 -0.0575 2.2433 0.6488 6.8829 7.2078 6.8833 0.3299 0.0439 0.1523 27.0842 0.0988 0.0477 0.0711 0.0597 -0.0608 2.3228 0.6479 6.9320 7.2573 6.9323 0.3295 0.0381 0.1473 26.4399 0.0955 0.0460 0.0642 0.0589 -0.0645 2.4022 0.6468 6.9971 7.3220 6.9974 0.3287 0.0324 0.1423 25.8780 0.0921 0.0443 0.0573 0.0579 -0.0684 2.4817 0.6446 7.0488 7.3722 7.0491 0.3276 0.0267 0.1374 25.3040 0.0886 0.0425 0.0504 0.0570 -0.0721 2.5612 0.6413 7.0853 7.4062 7.0856 0.3262 0.0209 0.1325 24.7130 0.0850 0.0406 0.0436 0.0562 -0.0755 2.6407 0.6368 7.1096 7.4270 7.1099 0.3244 0.0152 0.1276 24.1147 0.0813 0.0386 0.0367 0.0556 -0.0787 2.7202 0.6311 7.1248 7.4377 7.1250 0.3223 0.0095 0.1228 23.5174 0.0775 0.0365 0.0298 0.0552 -0.0818 2.7997 0.6242 7.1338 7.4412 7.1340 0.3199 0.0039 0.1180 22.9291 0.0737 0.0343 0.0229 0.0550 -0.0847 2.8791 0.6162 7.1396 7.4404 7.1397 0.3172 -0.0018 0.1132 22.3571 0.0697 0.0321 0.0160 0.0550 -0.0875 2.9586 0.6069 7.1452 7.4383 7.1454 0.3141 -0.0074 0.1084 21.8080 0.0658 0.0298 0.0092 0.0551 -0.0904 3.0381 0.5965 7.1537 7.4380 7.1538 0.3107 -0.0130 0.1035 21.2882 0.0617 0.0275 0.0023 0.0555 -0.0932 3.1176 0.5849 7.1680 7.4422 7.1681 0.3070 -0.0186 0.0986 20.8033 0.0577 0.0253 -0.0046 0.0562 -0.0960 3.1971 0.5721 7.1911 7.4540 7.1912 0.3029 -0.0241 0.0937 20.3584 0.0536 0.0230 -0.0115 0.0570 -0.0990 3.2766 0.5578 7.2261 7.4763 7.2262 0.2983 -0.0298 0.0886 19.9586 0.0494 0.0207 -0.0185 0.0579 -0.1021 3.3560 0.5325 7.2759 7.5135 7.2777 0.2840 -0.0389 0.0835 19.6119 0.0445 0.0178 -0.0291 0.0540 -0.1074 3.4355 0.4899 7.3435 7.5683 7.3545 0.2542 -0.0532 0.0783 19.3213 0.0384 0.0142 -0.0451 0.0420 -0.1161 3.5118 0.4293 7.4281 7.6390 7.4597 0.2076 -0.0729 0.0732 19.0958 0.0314 0.0102 -0.0666 0.0208 -0.1283 3.5337 0.4074 7.4562 7.6628 7.4967 0.1900 -0.0800 0.0717 19.0409 0.0292 0.0090 -0.0742 0.0125 -0.1326 3.5524 0.3867 7.4817 7.6843 7.5314 0.1732 -0.0867 0.0705 18.9974 0.0272 0.0080 -0.0813 0.0044 -0.1367 3.5711 0.3638 7.5086 7.7071 7.5697 0.1543 -0.0940 0.0692 18.9571 0.0252 0.0070 -0.0891 -0.0048 -0.1412 3.5897 0.3383 7.5370 7.7311 7.6125 0.1330 -0.1021 0.0679 18.9199 0.0230 0.0059 -0.0978 -0.0152 -0.1462 3.6084 0.3096 7.5668 7.7563 7.6612 0.1088 -0.1112 0.0666 18.8859 0.0206 0.0049 -0.1074 -0.0273 -0.1518 3.6271 0.2768 7.5981 7.7827 7.7192 0.0807 -0.1217 0.0653 18.8549 0.0181 0.0039 -0.1184 -0.0414 -0.1582 3.6458 0.2383 7.6310 7.8102 7.7929 0.0472 -0.1340 0.0639 18.8268 0.0152 0.0028 -0.1312 -0.0585 -0.1656 3.6645 0.1905 7.6654 7.8388 7.9015 0.0051 -0.1492 0.0626 18.8013 0.0119 0.0018 -0.1471 -0.0804 -0.1748 3.6832 0.1229 7.7015 7.8684 8.1428 -0.0559 -0.1708 0.0613 18.7782 0.0075 0.0007 -0.1695 -0.1124 -0.1879 3.7000 0.0231 7.7355 7.7355 7.7354 -0.1475 -0.2027 0.0601 18.4044 0.0014 0.0000 -0.2027 0.0000 0.0000 RADIUS: 3.70 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.043770 TOTAL WEIGHT (Kg) = 0.019850 TOTAL VOLUME (IN**3) = 0.713072 TOTAL PROJECTED AREA (IN**2) = 4.1313 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000186 MOMENT OF INERTIA (Kg-M**2) = 0.000021 STATIC MOMENT, ONE SIDE (IN-LB) = 0.020676 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 = 122.204 INNER LIMIT (NORMALIZED BY RADIUS) = 0.122 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 41048.55 BASED ON MODULUS (MILLION) = 3.50 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.