RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 50,000 Max Cl/Cd: 19.38 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf33-il-50000-n5.txt Download as CSV file: xf-raf33-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 33 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2562 0.11116 0.10486 -0.0374 0.9012 0.1280
-9.750 -0.2633 0.10971 0.10337 -0.0423 0.8854 0.1323
-9.500 -0.2774 0.10845 0.10211 -0.0473 0.8706 0.1332
-9.250 -0.2419 0.10220 0.09576 -0.0443 0.8611 0.1366
-9.000 -0.2312 0.09909 0.09259 -0.0448 0.8505 0.1395
-8.750 -0.2263 0.09635 0.08983 -0.0459 0.8403 0.1425
-8.500 -0.2286 0.09395 0.08743 -0.0479 0.8301 0.1466
-8.250 -0.2600 0.09321 0.08674 -0.0522 0.8196 0.1498
-8.000 -0.2628 0.09035 0.08389 -0.0531 0.8110 0.1506
-7.750 -0.2377 0.08575 0.07925 -0.0519 0.8045 0.1529
-7.500 -0.2266 0.08288 0.07637 -0.0515 0.7967 0.1567
-7.250 -0.2489 0.07658 0.06972 -0.0580 0.7904 0.0989
-7.000 -0.2384 0.07340 0.06654 -0.0578 0.7827 0.0968
-6.500 -0.2393 0.06580 0.05840 -0.0590 0.7703 0.0847
-6.250 -0.2282 0.06308 0.05562 -0.0584 0.7636 0.0836
-6.000 -0.2188 0.06039 0.05277 -0.0574 0.7583 0.0825
-5.750 -0.2089 0.05778 0.04998 -0.0568 0.7516 0.0814
-5.500 -0.1987 0.05519 0.04717 -0.0557 0.7457 0.0805
-5.250 -0.1873 0.05274 0.04443 -0.0543 0.7410 0.0808
-5.000 -0.1753 0.05058 0.04199 -0.0533 0.7343 0.0815
-4.750 -0.1616 0.04842 0.03950 -0.0518 0.7286 0.0822
-4.500 -0.1461 0.04627 0.03698 -0.0502 0.7243 0.0824
-4.250 -0.1304 0.04447 0.03487 -0.0490 0.7178 0.0822
-4.000 -0.1133 0.04268 0.03272 -0.0476 0.7123 0.0822
-3.750 -0.0938 0.04095 0.03060 -0.0460 0.7081 0.0824
-3.500 -0.0749 0.03961 0.02892 -0.0449 0.7018 0.0831
-3.250 -0.0540 0.03839 0.02725 -0.0436 0.6963 0.0849
-3.000 -0.0312 0.03717 0.02587 -0.0428 0.6922 0.0874
-2.750 -0.0088 0.03638 0.02494 -0.0422 0.6864 0.0896
-2.500 0.0155 0.03555 0.02389 -0.0417 0.6806 0.0914
-2.250 0.0436 0.03458 0.02265 -0.0415 0.6763 0.0936
-2.000 0.0728 0.03382 0.02164 -0.0416 0.6717 0.0968
-1.750 0.1041 0.03337 0.02103 -0.0426 0.6653 0.1018
-1.500 0.1426 0.03271 0.02029 -0.0445 0.6607 0.1091
-1.250 0.1832 0.03196 0.01928 -0.0461 0.6573 0.1168
-1.000 0.2083 0.03201 0.01943 -0.0467 0.6500 0.1271
-0.750 0.2349 0.03169 0.01910 -0.0465 0.6451 0.1409
-0.500 0.2612 0.03122 0.01864 -0.0459 0.6415 0.1637
-0.250 0.2779 0.03140 0.01905 -0.0449 0.6347 0.1956
0.000 0.2956 0.03090 0.01905 -0.0435 0.6294 0.2912
0.250 0.4782 0.02893 0.01824 -0.0708 0.6260 1.0000
0.500 0.4969 0.02958 0.01874 -0.0698 0.6202 1.0000
0.750 0.5151 0.03022 0.01926 -0.0688 0.6139 1.0000
1.000 0.5366 0.03045 0.01932 -0.0675 0.6097 1.0000
1.250 0.5536 0.03120 0.01999 -0.0664 0.6036 1.0000
1.500 0.5702 0.03194 0.02065 -0.0651 0.5972 1.0000
1.750 0.5919 0.03215 0.02073 -0.0638 0.5930 1.0000
2.000 0.6053 0.03317 0.02172 -0.0625 0.5861 1.0000
2.250 0.6215 0.03386 0.02236 -0.0611 0.5800 1.0000
2.500 0.6442 0.03397 0.02236 -0.0597 0.5761 1.0000
2.750 0.6511 0.03545 0.02385 -0.0580 0.5676 1.0000
3.000 0.6697 0.03589 0.02424 -0.0565 0.5623 1.0000
3.250 0.6945 0.03583 0.02410 -0.0553 0.5589 1.0000
3.500 0.6932 0.03782 0.02614 -0.0530 0.5487 1.0000
3.750 0.7161 0.03790 0.02616 -0.0517 0.5445 1.0000
4.250 0.7353 0.04001 0.02828 -0.0477 0.5300 1.0000
4.500 0.7633 0.03969 0.02791 -0.0467 0.5268 1.0000
4.750 0.7523 0.04216 0.03042 -0.0435 0.5152 1.0000
5.000 0.7797 0.04188 0.03012 -0.0425 0.5117 1.0000
5.250 0.7665 0.04446 0.03274 -0.0392 0.5001 1.0000
5.500 0.7937 0.04415 0.03241 -0.0381 0.4964 1.0000
6.000 0.8049 0.04664 0.03494 -0.0337 0.4809 1.0000
6.500 0.8089 0.04952 0.03783 -0.0290 0.4650 1.0000
7.000 0.8159 0.05248 0.04082 -0.0250 0.4493 1.0000
7.500 0.8250 0.05559 0.04400 -0.0216 0.4338 1.0000
8.000 0.8338 0.05906 0.04753 -0.0188 0.4184 1.0000
8.500 0.8420 0.06286 0.05140 -0.0164 0.4032 1.0000
9.000 0.8469 0.06735 0.05600 -0.0145 0.3883 1.0000
9.500 0.8501 0.07228 0.06103 -0.0130 0.3737 1.0000
9.750 0.8686 0.07291 0.06173 -0.0120 0.3702 1.0000
10.000 0.8473 0.07837 0.06723 -0.0121 0.3598 1.0000
10.250 0.8670 0.07898 0.06792 -0.0112 0.3570 1.0000
10.500 0.8453 0.08466 0.07363 -0.0116 0.3472 1.0000
10.750 0.8590 0.08601 0.07509 -0.0110 0.3432 1.0000
11.000 0.8803 0.08647 0.07566 -0.0101 0.3408 1.0000
11.250 0.8495 0.09374 0.08295 -0.0113 0.3315 1.0000
11.500 0.8599 0.09575 0.08505 -0.0110 0.3281 1.0000
11.750 0.8780 0.09673 0.08615 -0.0103 0.3257 1.0000
12.000 0.8518 0.10348 0.09294 -0.0117 0.3175 1.0000
12.250 0.8603 0.10575 0.09531 -0.0116 0.3136 1.0000
12.500 0.8800 0.10644 0.09615 -0.0108 0.3108 1.0000
12.750 0.8593 0.11266 0.10242 -0.0123 0.3039 1.0000
13.000 0.8712 0.11404 0.10392 -0.0118 0.2981 1.0000
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Polar data table (+)
Polar graphs
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