NACA M18 (nacam18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 200,000 Max Cl/Cd: 71.65 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam18-il-200000.txt Download as CSV file: xf-nacam18-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3940 0.10683 0.10353 -0.0178 1.0000 0.0547
-9.000 -0.4063 0.10270 0.09948 -0.0275 1.0000 0.0552
-8.750 -0.4153 0.09824 0.09504 -0.0350 1.0000 0.0554
-8.500 -0.3884 0.09385 0.09070 -0.0275 1.0000 0.0563
-8.250 -0.3747 0.09083 0.08772 -0.0273 1.0000 0.0572
-8.000 -0.3645 0.08757 0.08450 -0.0295 0.9921 0.0582
-7.750 -0.3514 0.08344 0.08032 -0.0347 0.9459 0.0597
-7.500 -0.3524 0.08021 0.07701 -0.0365 0.9139 0.0610
-7.250 -0.3552 0.07703 0.07371 -0.0382 0.8916 0.0630
-6.750 -0.3565 0.06795 0.06421 -0.0447 0.8590 0.0666
-6.500 -0.3454 0.06538 0.06162 -0.0433 0.8458 0.0675
-6.250 -0.3335 0.06291 0.05908 -0.0426 0.8334 0.0686
-6.000 -0.3212 0.06034 0.05640 -0.0424 0.8225 0.0703
-5.750 -0.3077 0.05754 0.05343 -0.0427 0.8125 0.0729
-5.500 -0.2951 0.05319 0.04848 -0.0447 0.8028 0.0784
-5.250 -0.2801 0.05020 0.04548 -0.0439 0.7946 0.0794
-5.000 -0.2625 0.04797 0.04323 -0.0434 0.7848 0.0809
-4.750 -0.2448 0.04602 0.04115 -0.0427 0.7774 0.0834
-4.500 -0.2252 0.04361 0.03814 -0.0424 0.7686 0.0923
-4.250 -0.2069 0.04081 0.03535 -0.0419 0.7618 0.0938
-4.000 -0.1862 0.03889 0.03341 -0.0415 0.7533 0.0959
-3.750 -0.1594 0.04031 0.03413 -0.0399 0.7463 0.1060
-3.500 -0.1433 0.03502 0.02895 -0.0400 0.7393 0.1085
-3.250 -0.1211 0.03324 0.02712 -0.0396 0.7322 0.1111
-3.000 -0.0971 0.03202 0.02570 -0.0389 0.7257 0.1176
-2.750 -0.0693 0.02536 0.01792 -0.0364 0.7198 0.0740
-2.500 -0.0418 0.02291 0.01471 -0.0349 0.7140 0.0652
-2.250 -0.0150 0.02115 0.01275 -0.0346 0.7074 0.0643
-2.000 0.0125 0.01994 0.01132 -0.0342 0.7004 0.0640
-1.750 0.0403 0.01902 0.01017 -0.0338 0.6948 0.0642
-1.500 0.0687 0.01827 0.00932 -0.0337 0.6874 0.0648
-1.250 0.0964 0.01746 0.00838 -0.0335 0.6813 0.0666
-1.000 0.1237 0.01683 0.00779 -0.0334 0.6746 0.0693
-0.750 0.1511 0.01634 0.00729 -0.0331 0.6678 0.0715
-0.500 0.1779 0.01595 0.00681 -0.0327 0.6626 0.0745
-0.250 0.2047 0.01557 0.00646 -0.0324 0.6550 0.0781
0.000 0.2302 0.01511 0.00604 -0.0318 0.6490 0.0855
0.250 0.2559 0.01480 0.00578 -0.0314 0.6427 0.1023
0.500 0.2785 0.01405 0.00550 -0.0304 0.6361 0.2054
0.750 0.4347 0.01291 0.00633 -0.0554 0.6268 1.0000
1.000 0.4609 0.01294 0.00627 -0.0553 0.6197 1.0000
1.250 0.4868 0.01300 0.00616 -0.0550 0.6141 1.0000
1.500 0.5130 0.01305 0.00619 -0.0549 0.6066 1.0000
1.750 0.5389 0.01310 0.00614 -0.0546 0.6003 1.0000
2.000 0.5649 0.01319 0.00615 -0.0545 0.5941 1.0000
2.250 0.5907 0.01324 0.00617 -0.0543 0.5869 1.0000
2.500 0.6165 0.01332 0.00612 -0.0540 0.5815 1.0000
2.750 0.6420 0.01341 0.00624 -0.0538 0.5740 1.0000
3.000 0.6674 0.01348 0.00623 -0.0534 0.5677 1.0000
3.250 0.6927 0.01359 0.00631 -0.0532 0.5616 1.0000
3.500 0.7178 0.01368 0.00639 -0.0529 0.5544 1.0000
3.750 0.7432 0.01377 0.00638 -0.0525 0.5490 1.0000
4.000 0.7680 0.01389 0.00657 -0.0522 0.5415 1.0000
4.250 0.7931 0.01398 0.00661 -0.0519 0.5354 1.0000
4.500 0.8180 0.01413 0.00676 -0.0515 0.5293 1.0000
4.750 0.8426 0.01426 0.00691 -0.0512 0.5224 1.0000
5.000 0.8678 0.01438 0.00696 -0.0508 0.5171 1.0000
5.250 0.8918 0.01456 0.00723 -0.0504 0.5097 1.0000
5.500 0.9165 0.01469 0.00733 -0.0500 0.5038 1.0000
5.750 0.9408 0.01489 0.00757 -0.0497 0.4978 1.0000
6.000 0.9648 0.01507 0.00780 -0.0492 0.4909 1.0000
6.250 0.9898 0.01524 0.00789 -0.0489 0.4855 1.0000
6.500 1.0126 0.01544 0.00823 -0.0483 0.4773 1.0000
6.750 1.0370 0.01559 0.00833 -0.0479 0.4709 1.0000
7.000 1.0598 0.01584 0.00868 -0.0473 0.4633 1.0000
7.250 1.0837 0.01601 0.00885 -0.0468 0.4565 1.0000
7.500 1.1064 0.01626 0.00918 -0.0462 0.4488 1.0000
7.750 1.1296 0.01644 0.00937 -0.0456 0.4411 1.0000
8.000 1.1519 0.01672 0.00973 -0.0450 0.4336 1.0000
8.250 1.1746 0.01692 0.00996 -0.0443 0.4255 1.0000
8.500 1.1950 0.01706 0.01017 -0.0433 0.4138 1.0000
8.750 1.2145 0.01713 0.01026 -0.0421 0.3996 1.0000
9.000 1.2334 0.01726 0.01041 -0.0408 0.3852 1.0000
9.250 1.2525 0.01748 0.01067 -0.0396 0.3727 1.0000
9.500 1.2706 0.01774 0.01096 -0.0383 0.3593 1.0000
9.750 1.2875 0.01806 0.01131 -0.0368 0.3451 1.0000
10.000 1.3032 0.01842 0.01173 -0.0352 0.3291 1.0000
10.250 1.3172 0.01885 0.01224 -0.0334 0.3113 1.0000
10.500 1.3284 0.01940 0.01280 -0.0311 0.2903 1.0000
10.750 1.3345 0.02018 0.01352 -0.0282 0.2638 1.0000
11.000 1.3314 0.02135 0.01454 -0.0242 0.2288 1.0000
11.250 1.3158 0.02302 0.01598 -0.0187 0.1877 1.0000
11.500 1.2934 0.02582 0.01844 -0.0141 0.1383 1.0000
11.750 1.2715 0.02936 0.02171 -0.0111 0.1036 1.0000
12.000 1.2541 0.03303 0.02520 -0.0091 0.0744 1.0000
12.250 1.2416 0.03656 0.02864 -0.0079 0.0620 1.0000
12.500 1.2315 0.04006 0.03215 -0.0071 0.0562 1.0000
12.750 1.2249 0.04331 0.03549 -0.0065 0.0522 1.0000
13.000 1.2147 0.04701 0.03923 -0.0061 0.0496 1.0000
13.250 1.2080 0.05039 0.04269 -0.0057 0.0475 1.0000
13.500 1.2044 0.05348 0.04588 -0.0055 0.0453 1.0000
13.750 1.2004 0.05669 0.04915 -0.0054 0.0435 1.0000
14.000 1.1948 0.06011 0.05259 -0.0053 0.0419 1.0000
14.250 1.1908 0.06325 0.05574 -0.0049 0.0405 1.0000
14.500 1.1935 0.06579 0.05838 -0.0048 0.0392 1.0000
14.750 1.1964 0.06824 0.06090 -0.0045 0.0379 1.0000
15.000 1.2003 0.07056 0.06326 -0.0042 0.0368 1.0000
15.250 1.2054 0.07263 0.06534 -0.0038 0.0357 1.0000
15.500 1.2150 0.07374 0.06636 -0.0024 0.0344 1.0000
15.750 1.2239 0.07535 0.06805 -0.0016 0.0334 1.0000
16.000 1.2302 0.07754 0.07037 -0.0015 0.0325 1.0000
16.250 1.2376 0.07956 0.07248 -0.0012 0.0315 1.0000
16.500 1.2458 0.08142 0.07444 -0.0008 0.0308 1.0000
16.750 1.2540 0.08332 0.07641 -0.0004 0.0301 1.0000
17.000 1.2625 0.08519 0.07834 0.0000 0.0295 1.0000
17.250 1.2738 0.08670 0.07989 0.0008 0.0290 1.0000
17.500 1.2932 0.08755 0.08078 0.0030 0.0282 1.0000
17.750 1.2868 0.09160 0.08505 0.0020 0.0280 1.0000
18.000 1.2792 0.09593 0.08961 0.0007 0.0278 1.0000
18.250 1.2706 0.10054 0.09445 -0.0008 0.0276 1.0000
18.500 1.2608 0.10546 0.09960 -0.0025 0.0274 1.0000
18.750 1.2497 0.11075 0.10511 -0.0046 0.0273 1.0000
19.000 1.2371 0.11644 0.11102 -0.0070 0.0271 1.0000
19.250 1.2231 0.12255 0.11734 -0.0098 0.0271 1.0000
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Polar data table (+)
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