USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 500,000 Max Cl/Cd: 93.67 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45m-il-500000.txt Download as CSV file: xf-usa45m-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 M AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3788 0.08924 0.08699 -0.0271 1.0000 0.0302
-9.000 -0.3977 0.08131 0.07911 -0.0363 1.0000 0.0311
-8.750 -0.4116 0.07522 0.07304 -0.0425 1.0000 0.0312
-8.500 -0.4300 0.07069 0.06847 -0.0433 1.0000 0.0312
-8.250 -0.4546 0.06426 0.06198 -0.0432 1.0000 0.0315
-8.000 -0.4550 0.06193 0.05969 -0.0413 1.0000 0.0318
-7.750 -0.4565 0.06007 0.05784 -0.0391 1.0000 0.0320
-7.500 -0.4515 0.05759 0.05534 -0.0386 0.9989 0.0323
-7.250 -0.4260 0.05425 0.05194 -0.0426 0.9940 0.0329
-7.000 -0.4020 0.05061 0.04819 -0.0462 0.9874 0.0338
-6.750 -0.3768 0.04609 0.04346 -0.0501 0.9805 0.0356
-6.500 -0.3595 0.03806 0.03462 -0.0534 0.9707 0.0387
-6.250 -0.3329 0.03544 0.03200 -0.0550 0.9615 0.0393
-6.000 -0.3027 0.03333 0.02982 -0.0570 0.9518 0.0401
-5.750 -0.2733 0.03134 0.02769 -0.0585 0.9390 0.0412
-5.500 -0.2473 0.02944 0.02558 -0.0589 0.9210 0.0431
-5.250 -0.2177 0.03062 0.02624 -0.0576 0.8980 0.0463
-5.000 -0.2059 0.02513 0.02044 -0.0565 0.8744 0.0480
-4.750 -0.1838 0.02372 0.01891 -0.0558 0.8479 0.0490
-4.500 -0.1620 0.02262 0.01764 -0.0547 0.8202 0.0502
-4.250 -0.1399 0.02168 0.01646 -0.0536 0.7919 0.0520
-4.000 -0.1161 0.02150 0.01597 -0.0522 0.7619 0.0552
-3.750 -0.0964 0.01999 0.01398 -0.0505 0.7320 0.0584
-3.500 -0.0738 0.01866 0.01255 -0.0497 0.7002 0.0600
-3.250 -0.0475 0.01622 0.00955 -0.0477 0.6716 0.0444
-3.000 -0.0233 0.01504 0.00812 -0.0467 0.6406 0.0430
-2.750 0.0014 0.01428 0.00712 -0.0458 0.6092 0.0425
-2.500 0.0262 0.01369 0.00633 -0.0449 0.5787 0.0424
-2.250 0.0512 0.01321 0.00569 -0.0442 0.5511 0.0426
-2.000 0.0763 0.01291 0.00526 -0.0435 0.5278 0.0435
-1.750 0.1016 0.01258 0.00482 -0.0428 0.5084 0.0442
-1.500 0.1267 0.01226 0.00440 -0.0421 0.4922 0.0447
-1.250 0.1519 0.01201 0.00406 -0.0414 0.4786 0.0453
-1.000 0.1772 0.01183 0.00380 -0.0408 0.4667 0.0460
-0.750 0.2026 0.01159 0.00351 -0.0402 0.4566 0.0467
-0.500 0.2268 0.01122 0.00308 -0.0394 0.4482 0.0483
-0.250 0.2524 0.01106 0.00289 -0.0389 0.4398 0.0507
0.000 0.2784 0.01098 0.00278 -0.0384 0.4322 0.0536
0.250 0.3046 0.01092 0.00267 -0.0380 0.4249 0.0562
0.500 0.3303 0.01081 0.00250 -0.0374 0.4187 0.0615
0.750 0.3568 0.01071 0.00240 -0.0370 0.4125 0.0722
1.000 0.3616 0.00864 0.00236 -0.0331 0.4080 0.7147
1.250 0.4233 0.00843 0.00275 -0.0391 0.4002 0.9709
1.500 0.4810 0.00866 0.00286 -0.0453 0.3928 0.9847
1.750 0.5470 0.00884 0.00293 -0.0533 0.3855 0.9959
2.000 0.5906 0.00890 0.00293 -0.0567 0.3792 1.0000
2.250 0.6130 0.00901 0.00296 -0.0557 0.3745 1.0000
2.500 0.6360 0.00908 0.00301 -0.0547 0.3698 1.0000
2.750 0.6591 0.00915 0.00306 -0.0538 0.3651 1.0000
3.000 0.6818 0.00926 0.00313 -0.0528 0.3606 1.0000
3.250 0.7046 0.00940 0.00322 -0.0518 0.3560 1.0000
3.500 0.7280 0.00947 0.00330 -0.0509 0.3514 1.0000
3.750 0.7510 0.00958 0.00338 -0.0499 0.3466 1.0000
4.000 0.7735 0.00976 0.00350 -0.0489 0.3417 1.0000
4.250 0.7972 0.00982 0.00359 -0.0480 0.3367 1.0000
4.500 0.8204 0.00993 0.00368 -0.0471 0.3315 1.0000
4.750 0.8428 0.01014 0.00384 -0.0460 0.3269 1.0000
5.000 0.8666 0.01022 0.00397 -0.0452 0.3231 1.0000
5.250 0.8901 0.01035 0.00410 -0.0444 0.3187 1.0000
5.500 0.9130 0.01052 0.00425 -0.0434 0.3140 1.0000
5.750 0.9364 0.01065 0.00440 -0.0426 0.3082 1.0000
6.000 0.9599 0.01076 0.00451 -0.0417 0.3015 1.0000
6.250 0.9828 0.01093 0.00467 -0.0408 0.2950 1.0000
6.500 1.0065 0.01104 0.00481 -0.0400 0.2878 1.0000
6.750 1.0291 0.01124 0.00498 -0.0391 0.2813 1.0000
7.000 1.0529 0.01137 0.00514 -0.0383 0.2734 1.0000
7.250 1.0755 0.01157 0.00534 -0.0374 0.2655 1.0000
7.500 1.0986 0.01176 0.00553 -0.0366 0.2564 1.0000
7.750 1.1212 0.01197 0.00574 -0.0357 0.2454 1.0000
8.000 1.1428 0.01226 0.00599 -0.0347 0.2302 1.0000
8.250 1.1632 0.01264 0.00629 -0.0335 0.2120 1.0000
8.500 1.1810 0.01322 0.00672 -0.0320 0.1834 1.0000
8.750 1.1919 0.01434 0.00750 -0.0296 0.1344 1.0000
9.000 1.1862 0.01661 0.00916 -0.0249 0.0441 1.0000
9.250 1.1951 0.01773 0.01024 -0.0221 0.0270 1.0000
9.500 1.2088 0.01847 0.01104 -0.0200 0.0240 1.0000
9.750 1.2239 0.01907 0.01173 -0.0181 0.0228 1.0000
10.000 1.2358 0.01977 0.01250 -0.0158 0.0216 1.0000
10.250 1.2423 0.02059 0.01340 -0.0126 0.0206 1.0000
10.500 1.2447 0.02164 0.01455 -0.0091 0.0198 1.0000
10.750 1.2467 0.02280 0.01582 -0.0059 0.0191 1.0000
11.000 1.2531 0.02381 0.01692 -0.0036 0.0186 1.0000
11.250 1.2578 0.02501 0.01820 -0.0014 0.0180 1.0000
11.500 1.2592 0.02655 0.01984 0.0006 0.0175 1.0000
11.750 1.2592 0.02838 0.02176 0.0022 0.0172 1.0000
12.000 1.2577 0.03057 0.02406 0.0033 0.0170 1.0000
12.250 1.2535 0.03332 0.02691 0.0039 0.0166 1.0000
12.500 1.2474 0.03661 0.03033 0.0037 0.0163 1.0000
12.750 1.2384 0.04058 0.03441 0.0030 0.0161 1.0000
13.000 1.2305 0.04465 0.03860 0.0019 0.0159 1.0000
13.250 1.2200 0.04917 0.04324 0.0007 0.0159 1.0000
13.500 1.2061 0.05413 0.04830 -0.0007 0.0157 1.0000
13.750 1.1951 0.05867 0.05292 -0.0019 0.0156 1.0000
14.000 1.1841 0.06314 0.05747 -0.0029 0.0155 1.0000
14.250 1.1727 0.06750 0.06190 -0.0038 0.0153 1.0000
14.500 1.1723 0.07095 0.06544 -0.0048 0.0151 1.0000
14.750 1.1683 0.07456 0.06911 -0.0056 0.0150 1.0000
15.000 1.1667 0.07794 0.07256 -0.0063 0.0149 1.0000
15.250 1.1661 0.08133 0.07602 -0.0072 0.0146 1.0000
15.500 1.1657 0.08484 0.07960 -0.0084 0.0143 1.0000
15.750 1.1659 0.08808 0.08291 -0.0092 0.0140 1.0000
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