9x4.5MRF-RH (9x45MRF-RH.dat) v2022-0915 Simulation Date: 09/22/2022 ----- 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 IS 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 THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.9925 0.8407 3.1045 3.1045 3.0168 0.3208 0.1106 26.4654 0.0930 0.0498 0.1513 -0.0147 0.0136 1.0423 0.8748 3.3417 3.3417 3.2696 0.3260 0.1054 27.0339 0.0922 0.0516 0.1527 -0.0221 0.0068 1.0921 0.9053 3.5550 3.5550 3.4957 0.3308 0.1009 27.3882 0.0913 0.0531 0.1539 -0.0286 0.0014 1.1419 0.9322 3.7443 3.7443 3.6952 0.3352 0.0970 27.5594 0.0905 0.0544 0.1551 -0.0344 -0.0026 1.1916 0.9557 3.9096 3.9096 3.8682 0.3392 0.0939 27.5720 0.0897 0.0554 0.1561 -0.0396 -0.0053 1.2414 0.9756 4.0510 4.0510 4.0146 0.3429 0.0912 27.4452 0.0890 0.0563 0.1569 -0.0440 -0.0069 1.2912 0.9920 4.1684 4.1684 4.1352 0.3462 0.0890 27.1942 0.0883 0.0569 0.1575 -0.0477 -0.0073 1.3462 1.0061 4.2703 4.2703 4.2388 0.3494 0.0871 26.7874 0.0876 0.0573 0.1579 -0.0509 -0.0065 1.4405 1.0203 4.3769 4.3769 4.3461 0.3540 0.0847 25.8082 0.0864 0.0574 0.1580 -0.0542 -0.0022 1.5399 1.0217 4.4040 4.4040 4.3718 0.3574 0.0829 24.4736 0.0847 0.0565 0.1573 -0.0545 0.0054 1.6393 1.0159 4.4139 4.4139 4.3793 0.3596 0.0815 23.1963 0.0828 0.0550 0.1559 -0.0529 0.0129 1.7388 1.0083 4.4239 4.4239 4.3865 0.3604 0.0801 22.0442 0.0808 0.0533 0.1538 -0.0515 0.0190 1.8382 0.9991 4.4338 4.4338 4.3935 0.3600 0.0789 21.0007 0.0788 0.0516 0.1511 -0.0502 0.0238 1.9377 0.9882 4.4438 4.4438 4.4003 0.3583 0.0778 20.0518 0.0769 0.0498 0.1476 -0.0491 0.0274 2.0371 0.9757 4.4537 4.4537 4.4068 0.3554 0.0768 19.1855 0.0749 0.0480 0.1436 -0.0483 0.0299 2.1366 0.9617 4.4637 4.4637 4.4129 0.3514 0.0759 18.3918 0.0730 0.0462 0.1390 -0.0477 0.0315 2.2360 0.9461 4.4736 4.4736 4.4188 0.3462 0.0751 17.6624 0.0710 0.0442 0.1339 -0.0475 0.0321 2.3355 0.9291 4.4836 4.4835 4.4243 0.3399 0.0744 16.9898 0.0691 0.0423 0.1283 -0.0476 0.0319 2.4349 0.9106 4.4935 4.4935 4.4295 0.3326 0.0738 16.3679 0.0672 0.0403 0.1223 -0.0479 0.0310 2.5344 0.8908 4.5034 4.5034 4.4343 0.3242 0.0733 15.7912 0.0653 0.0383 0.1158 -0.0486 0.0294 2.6339 0.8696 4.5134 4.5134 4.4384 0.3149 0.0728 15.2552 0.0633 0.0364 0.1090 -0.0499 0.0270 2.7333 0.8471 4.5233 4.5233 4.4405 0.3046 0.0725 14.7557 0.0614 0.0346 0.1018 -0.0521 0.0237 2.8328 0.8233 4.5333 4.5333 4.4409 0.2933 0.0722 14.2893 0.0594 0.0330 0.0943 -0.0554 0.0195 2.9322 0.7984 4.5432 4.5432 4.4397 0.2812 0.0720 13.8527 0.0575 0.0315 0.0865 -0.0594 0.0147 3.0317 0.7722 4.5532 4.5532 4.4371 0.2682 0.0718 13.4432 0.0555 0.0300 0.0785 -0.0641 0.0092 3.1311 0.7449 4.5631 4.5631 4.4336 0.2544 0.0717 13.0585 0.0534 0.0286 0.0703 -0.0691 0.0034 3.2306 0.7166 4.5731 4.5731 4.4296 0.2398 0.0717 12.6964 0.0514 0.0271 0.0619 -0.0744 -0.0026 3.3300 0.6871 4.5830 4.5830 4.4256 0.2245 0.0717 12.3550 0.0493 0.0256 0.0534 -0.0797 -0.0088 3.4295 0.6567 4.5929 4.5929 4.4220 0.2084 0.0717 12.0326 0.0471 0.0240 0.0448 -0.0849 -0.0150 3.5289 0.6253 4.6029 4.6029 4.4194 0.1917 0.0718 11.7276 0.0449 0.0223 0.0361 -0.0900 -0.0211 3.6284 0.5930 4.6128 4.6128 4.4181 0.1743 0.0719 11.4387 0.0427 0.0205 0.0275 -0.0948 -0.0271 3.7278 0.5598 4.6228 4.6228 4.4186 0.1563 0.0721 11.1647 0.0404 0.0186 0.0188 -0.0994 -0.0328 3.8273 0.5258 4.6327 4.6327 4.4211 0.1377 0.0723 10.9045 0.0380 0.0167 0.0102 -0.1037 -0.0383 3.9267 0.4910 4.6427 4.6427 4.4258 0.1185 0.0725 10.6570 0.0356 0.0147 0.0017 -0.1078 -0.0435 4.0262 0.4554 4.6526 4.6526 4.4317 0.0989 0.0727 10.4213 0.0331 0.0128 -0.0067 -0.1117 -0.0484 4.1256 0.4191 4.6626 4.6626 4.4271 0.0788 0.0729 10.1967 0.0306 0.0109 -0.0155 -0.1155 -0.0536 4.2250 0.3822 4.6725 4.6725 4.4046 0.0582 0.0732 9.9824 0.0280 0.0091 -0.0245 -0.1192 -0.0593 4.3191 0.3382 4.6819 4.6819 4.3625 0.0301 0.0734 9.7886 0.0248 0.0071 -0.0311 -0.1272 -0.0620 4.3720 0.2961 4.6872 4.6872 4.3079 -0.0028 0.0735 9.6831 0.0218 0.0055 -0.0321 -0.1402 -0.0592 4.4158 0.2454 4.6916 4.6916 4.2421 -0.0456 0.0736 9.5977 0.0181 0.0037 -0.0323 -0.1590 -0.0550 4.4486 0.1899 4.6949 4.6949 4.1363 -0.0950 0.0737 9.5348 0.0140 0.0022 -0.0337 -0.1823 -0.0513 4.4807 0.0900 4.6981 4.6981 3.9914 -0.1882 0.0738 9.4740 0.0066 0.0005 -0.0416 -0.2295 -0.0501 4.5000 0.0138 4.7000 4.7061 4.7061 -0.2601 0.0738 9.4499 0.0010 0.0000 -0.0488 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBTRA: 0.99 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.020882 TOTAL WEIGHT (Kg) = 0.009470 TOTAL VOLUME (IN**3) = 0.340189 TOTAL PROJECTED AREA (IN**2) = 5.9532 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000230 MOMENT OF INERTIA (Kg-M**2) = 0.000026 STATIC MOMENT, ONE SIDE (IN-LB) = 0.018462 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 = 99.580 INNER LIMIT (NORMALIZED) = 0.138 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9413.35 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.57, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.18, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412