RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: RAF 6 AIRFOIL (raf6-il) Reynolds number: 100,000 Max Cl/Cd: 52.48 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf6-il-100000-n5.txt Download as CSV file: xf-raf6-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3544 0.11033 0.10587 -0.0274 1.0000 0.0365
-8.000 -0.3671 0.10897 0.10461 -0.0256 1.0000 0.0366
-7.750 -0.3767 0.10724 0.10295 -0.0253 0.9989 0.0367
-7.500 -0.3586 0.10275 0.09845 -0.0339 0.9930 0.0369
-7.250 -0.3380 0.09801 0.09367 -0.0419 0.9873 0.0370
-7.000 -0.3196 0.09356 0.08915 -0.0481 0.9814 0.0371
-6.750 -0.3007 0.08844 0.08400 -0.0533 0.9770 0.0374
-6.500 -0.2983 0.08360 0.07928 -0.0486 0.9745 0.0387
-6.250 -0.2838 0.08001 0.07569 -0.0496 0.9706 0.0402
-6.000 -0.2665 0.07625 0.07189 -0.0530 0.9653 0.0420
-5.750 -0.2451 0.07216 0.06773 -0.0577 0.9601 0.0441
-5.500 -0.2239 0.06818 0.06364 -0.0621 0.9540 0.0462
-5.000 -0.1596 0.06134 0.05596 -0.0738 0.9416 0.0497
-4.750 -0.1432 0.05574 0.05052 -0.0750 0.9383 0.0508
-4.500 -0.1180 0.05200 0.04673 -0.0771 0.9357 0.0521
-4.000 -0.0631 0.04459 0.03870 -0.0794 0.9256 0.0351
-3.750 -0.0303 0.04117 0.03499 -0.0818 0.9231 0.0342
-3.500 -0.0077 0.03857 0.03211 -0.0816 0.9170 0.0333
-3.250 0.0235 0.03569 0.02887 -0.0827 0.9132 0.0316
-3.000 0.0592 0.03293 0.02565 -0.0841 0.9106 0.0304
-2.750 0.0953 0.03058 0.02284 -0.0855 0.9078 0.0301
-2.500 0.1215 0.02906 0.02098 -0.0849 0.9003 0.0319
-2.250 0.1612 0.02712 0.01860 -0.0865 0.8961 0.0332
-2.000 0.1957 0.02547 0.01659 -0.0870 0.8894 0.0340
-1.750 0.2316 0.02425 0.01502 -0.0877 0.8824 0.0368
-1.500 0.2722 0.02250 0.01317 -0.0896 0.8789 0.0395
-1.250 0.2987 0.02172 0.01236 -0.0891 0.8705 0.0436
-1.000 0.3362 0.02064 0.01117 -0.0903 0.8649 0.0489
-0.750 0.3695 0.01958 0.01012 -0.0908 0.8553 0.0573
-0.500 0.4140 0.01842 0.00883 -0.0932 0.8466 0.0712
-0.250 0.4454 0.01771 0.00811 -0.0933 0.8343 0.0968
0.000 0.4887 0.01501 0.00772 -0.0956 0.8277 1.0000
0.250 0.5205 0.01489 0.00734 -0.0960 0.8168 1.0000
0.500 0.5508 0.01482 0.00707 -0.0961 0.8047 1.0000
0.750 0.5831 0.01471 0.00679 -0.0967 0.7920 1.0000
1.000 0.6136 0.01465 0.00657 -0.0968 0.7772 1.0000
1.250 0.6409 0.01465 0.00645 -0.0964 0.7599 1.0000
1.500 0.6667 0.01466 0.00635 -0.0957 0.7400 1.0000
1.750 0.6932 0.01466 0.00623 -0.0951 0.7161 1.0000
2.000 0.7190 0.01468 0.00612 -0.0943 0.6849 1.0000
2.250 0.7471 0.01471 0.00594 -0.0940 0.6437 1.0000
2.500 0.7757 0.01486 0.00575 -0.0937 0.5915 1.0000
2.750 0.7993 0.01523 0.00573 -0.0926 0.5359 1.0000
3.000 0.8195 0.01575 0.00588 -0.0910 0.4888 1.0000
3.250 0.8392 0.01629 0.00614 -0.0895 0.4521 1.0000
3.500 0.8594 0.01682 0.00644 -0.0881 0.4231 1.0000
3.750 0.8801 0.01732 0.00677 -0.0868 0.3988 1.0000
4.000 0.9009 0.01782 0.00713 -0.0856 0.3775 1.0000
4.250 0.9222 0.01829 0.00749 -0.0845 0.3581 1.0000
4.500 0.9436 0.01876 0.00786 -0.0835 0.3413 1.0000
4.750 0.9649 0.01925 0.00827 -0.0824 0.3273 1.0000
5.000 0.9867 0.01972 0.00868 -0.0815 0.3152 1.0000
5.250 1.0087 0.02019 0.00912 -0.0806 0.3042 1.0000
5.500 1.0301 0.02071 0.00958 -0.0796 0.2948 1.0000
5.750 1.0521 0.02119 0.01006 -0.0788 0.2858 1.0000
6.000 1.0739 0.02173 0.01058 -0.0779 0.2785 1.0000
6.250 1.0962 0.02223 0.01112 -0.0772 0.2712 1.0000
6.500 1.1176 0.02282 0.01166 -0.0763 0.2649 1.0000
6.750 1.1399 0.02333 0.01228 -0.0755 0.2579 1.0000
7.000 1.1613 0.02392 0.01287 -0.0747 0.2521 1.0000
7.250 1.1835 0.02450 0.01352 -0.0740 0.2463 1.0000
7.500 1.2050 0.02508 0.01420 -0.0731 0.2405 1.0000
8.000 1.2479 0.02635 0.01563 -0.0715 0.2301 1.0000
8.250 1.2688 0.02699 0.01638 -0.0707 0.2250 1.0000
8.500 1.2905 0.02773 0.01713 -0.0700 0.2207 1.0000
8.750 1.3104 0.02839 0.01803 -0.0690 0.2156 1.0000
9.000 1.3304 0.02910 0.01889 -0.0680 0.2109 1.0000
9.250 1.3512 0.02985 0.01973 -0.0672 0.2071 1.0000
9.500 1.3713 0.03067 0.02074 -0.0663 0.2031 1.0000
9.750 1.3862 0.03136 0.02169 -0.0644 0.1976 1.0000
10.000 1.3947 0.03186 0.02223 -0.0616 0.1905 1.0000
10.250 1.3984 0.03236 0.02298 -0.0581 0.1808 1.0000
10.500 1.4029 0.03294 0.02366 -0.0550 0.1718 1.0000
10.750 1.4096 0.03361 0.02455 -0.0523 0.1620 1.0000
11.000 1.4162 0.03439 0.02548 -0.0499 0.1491 1.0000
11.250 1.4229 0.03534 0.02653 -0.0477 0.1340 1.0000
11.500 1.4295 0.03657 0.02781 -0.0456 0.1112 1.0000
11.750 1.4275 0.03865 0.02970 -0.0430 0.0772 1.0000
12.000 1.4064 0.04267 0.03328 -0.0395 0.0337 1.0000
12.250 1.3962 0.04593 0.03662 -0.0370 0.0287 1.0000
12.500 1.3864 0.04930 0.04017 -0.0350 0.0255 1.0000
12.750 1.3772 0.05276 0.04384 -0.0334 0.0235 1.0000
13.000 1.3679 0.05639 0.04774 -0.0324 0.0223 1.0000
13.250 1.3557 0.06060 0.05220 -0.0320 0.0215 1.0000
13.500 1.3406 0.06550 0.05736 -0.0322 0.0210 1.0000
13.750 1.3230 0.07120 0.06331 -0.0333 0.0207 1.0000
14.000 1.3031 0.07787 0.07023 -0.0355 0.0206 1.0000
14.250 1.2807 0.08556 0.07815 -0.0386 0.0208 1.0000
14.500 1.2570 0.09402 0.08684 -0.0424 0.0210 1.0000
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