NACA M3 (nacam3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M3 (nacam3-il) Reynolds number: 200,000 Max Cl/Cd: 45.8 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam3-il-200000.txt Download as CSV file: xf-nacam3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M3
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6450 0.09044 0.08670 -0.0275 1.0000 0.0592
-12.250 -0.9128 0.06896 0.06448 -0.0375 1.0000 0.0504
-12.000 -0.9334 0.06401 0.05939 -0.0377 1.0000 0.0500
-11.750 -0.9548 0.05973 0.05493 -0.0365 1.0000 0.0497
-11.500 -0.9752 0.05600 0.05099 -0.0337 1.0000 0.0493
-11.250 -0.9915 0.05233 0.04706 -0.0305 1.0000 0.0490
-11.000 -1.0018 0.04859 0.04300 -0.0276 1.0000 0.0488
-10.750 -1.0065 0.04513 0.03919 -0.0248 1.0000 0.0489
-10.500 -1.0058 0.04220 0.03589 -0.0221 1.0000 0.0494
-10.250 -1.0005 0.03971 0.03301 -0.0196 1.0000 0.0500
-10.000 -0.9918 0.03758 0.03051 -0.0173 1.0000 0.0506
-9.750 -0.9801 0.03576 0.02834 -0.0151 1.0000 0.0510
-9.500 -0.9652 0.03246 0.02480 -0.0139 1.0000 0.0517
-9.250 -0.9459 0.03049 0.02278 -0.0130 1.0000 0.0530
-9.000 -0.9266 0.02922 0.02142 -0.0119 1.0000 0.0543
-8.750 -0.9067 0.02796 0.02004 -0.0108 1.0000 0.0556
-8.500 -0.8863 0.02663 0.01857 -0.0096 1.0000 0.0567
-8.250 -0.8656 0.02541 0.01720 -0.0084 1.0000 0.0579
-8.000 -0.8450 0.02445 0.01608 -0.0071 1.0000 0.0593
-7.750 -0.8243 0.02337 0.01488 -0.0058 1.0000 0.0606
-7.500 -0.8036 0.02196 0.01351 -0.0048 1.0000 0.0624
-7.250 -0.7836 0.02106 0.01264 -0.0034 1.0000 0.0641
-7.000 -0.7640 0.02028 0.01183 -0.0020 1.0000 0.0661
-6.750 -0.7446 0.01958 0.01109 -0.0004 1.0000 0.0685
-6.500 -0.7255 0.01895 0.01040 0.0012 1.0000 0.0710
-6.250 -0.7094 0.01799 0.00953 0.0032 1.0000 0.0745
-6.000 -0.6915 0.01737 0.00891 0.0050 1.0000 0.0786
-5.750 -0.6741 0.01671 0.00824 0.0069 1.0000 0.0838
-5.500 -0.6572 0.01603 0.00762 0.0087 1.0000 0.0930
-5.250 -0.6411 0.01518 0.00696 0.0107 1.0000 0.1142
-5.000 -0.6254 0.01422 0.00636 0.0126 1.0000 0.1688
-4.750 -0.6082 0.01346 0.00597 0.0141 1.0000 0.2341
-4.500 -0.5896 0.01291 0.00571 0.0154 1.0000 0.2953
-4.250 -0.5700 0.01244 0.00551 0.0166 1.0000 0.3544
-4.000 -0.5498 0.01203 0.00536 0.0178 1.0000 0.4138
-3.750 -0.5290 0.01171 0.00528 0.0188 1.0000 0.4705
-3.500 -0.5079 0.01143 0.00524 0.0199 1.0000 0.5257
-3.250 -0.4866 0.01122 0.00526 0.0210 1.0000 0.5821
-3.000 -0.4652 0.01108 0.00536 0.0222 1.0000 0.6354
-2.750 -0.4437 0.01102 0.00548 0.0234 1.0000 0.6820
-2.500 -0.4075 0.01101 0.00561 0.0218 0.9959 0.7253
-2.250 -0.3683 0.01104 0.00573 0.0196 0.9903 0.7621
-2.000 -0.3289 0.01112 0.00590 0.0175 0.9844 0.7960
-1.750 -0.2918 0.01119 0.00603 0.0160 0.9775 0.8239
-1.500 -0.2516 0.01129 0.00616 0.0139 0.9714 0.8466
-1.250 -0.2154 0.01139 0.00628 0.0127 0.9637 0.8670
-1.000 -0.1737 0.01150 0.00639 0.0104 0.9578 0.8848
-0.750 -0.1329 0.01160 0.00649 0.0083 0.9510 0.8994
-0.500 -0.0891 0.01166 0.00654 0.0056 0.9444 0.9117
-0.250 -0.0411 0.01167 0.00654 0.0021 0.9398 0.9217
0.000 0.0000 0.01172 0.00659 0.0000 0.9298 0.9298
0.250 0.0411 0.01167 0.00654 -0.0021 0.9217 0.9398
0.500 0.0891 0.01166 0.00654 -0.0056 0.9117 0.9444
0.750 0.1329 0.01160 0.00649 -0.0083 0.8994 0.9510
1.000 0.1737 0.01150 0.00639 -0.0104 0.8848 0.9578
1.250 0.2154 0.01139 0.00628 -0.0127 0.8670 0.9637
1.500 0.2516 0.01129 0.00616 -0.0139 0.8466 0.9715
1.750 0.2919 0.01119 0.00603 -0.0160 0.8240 0.9775
2.000 0.3289 0.01111 0.00590 -0.0175 0.7960 0.9845
2.250 0.3683 0.01104 0.00573 -0.0196 0.7621 0.9903
2.500 0.4075 0.01101 0.00560 -0.0218 0.7252 0.9959
2.750 0.4435 0.01102 0.00548 -0.0234 0.6820 1.0000
3.000 0.4651 0.01107 0.00535 -0.0222 0.6354 1.0000
3.250 0.4865 0.01122 0.00526 -0.0210 0.5821 1.0000
3.500 0.5078 0.01143 0.00524 -0.0199 0.5259 1.0000
3.750 0.5288 0.01171 0.00527 -0.0188 0.4706 1.0000
4.000 0.5497 0.01203 0.00536 -0.0177 0.4137 1.0000
4.250 0.5698 0.01244 0.00550 -0.0166 0.3546 1.0000
4.500 0.5895 0.01290 0.00570 -0.0154 0.2954 1.0000
4.750 0.6081 0.01346 0.00597 -0.0141 0.2343 1.0000
5.000 0.6253 0.01421 0.00635 -0.0125 0.1690 1.0000
5.250 0.6410 0.01517 0.00695 -0.0107 0.1143 1.0000
5.500 0.6571 0.01602 0.00762 -0.0087 0.0931 1.0000
5.750 0.6740 0.01671 0.00824 -0.0069 0.0839 1.0000
6.000 0.6914 0.01737 0.00891 -0.0049 0.0786 1.0000
6.250 0.7093 0.01798 0.00952 -0.0032 0.0745 1.0000
6.500 0.7254 0.01895 0.01040 -0.0012 0.0710 1.0000
6.750 0.7446 0.01958 0.01109 0.0004 0.0685 1.0000
7.000 0.7639 0.02027 0.01183 0.0020 0.0661 1.0000
7.250 0.7836 0.02106 0.01263 0.0034 0.0641 1.0000
7.500 0.8035 0.02195 0.01351 0.0048 0.0624 1.0000
7.750 0.8242 0.02336 0.01487 0.0058 0.0606 1.0000
8.000 0.8450 0.02444 0.01607 0.0071 0.0593 1.0000
8.250 0.8656 0.02541 0.01720 0.0084 0.0579 1.0000
8.500 0.8863 0.02663 0.01857 0.0096 0.0567 1.0000
8.750 0.9067 0.02795 0.02004 0.0108 0.0556 1.0000
9.000 0.9267 0.02923 0.02143 0.0119 0.0543 1.0000
9.250 0.9460 0.03049 0.02278 0.0130 0.0529 1.0000
9.500 0.9653 0.03247 0.02481 0.0138 0.0517 1.0000
9.750 0.9802 0.03577 0.02834 0.0151 0.0510 1.0000
10.000 0.9920 0.03759 0.03051 0.0172 0.0506 1.0000
10.250 1.0007 0.03970 0.03301 0.0196 0.0500 1.0000
10.500 1.0059 0.04220 0.03589 0.0221 0.0493 1.0000
10.750 1.0067 0.04514 0.03920 0.0248 0.0488 1.0000
11.000 1.0020 0.04861 0.04302 0.0276 0.0488 1.0000
11.250 0.9918 0.05235 0.04709 0.0305 0.0490 1.0000
11.500 0.9755 0.05603 0.05103 0.0336 0.0493 1.0000
11.750 0.9550 0.05978 0.05498 0.0364 0.0497 1.0000
12.000 0.9337 0.06407 0.05945 0.0376 0.0500 1.0000
12.250 0.9131 0.06903 0.06456 0.0373 0.0504 1.0000
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