NACA M3 (nacam3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M3 (nacam3-il) Reynolds number: 50,000 Max Cl/Cd: 26.62 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam3-il-50000-n5.txt Download as CSV file: xf-nacam3-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7467 0.09622 0.08831 -0.0209 1.0000 0.0723
-11.750 -0.7795 0.08618 0.07821 -0.0276 1.0000 0.0716
-11.500 -0.8133 0.07808 0.06998 -0.0323 1.0000 0.0710
-11.250 -0.8437 0.07199 0.06371 -0.0342 1.0000 0.0707
-11.000 -0.8695 0.06731 0.05882 -0.0336 1.0000 0.0707
-10.750 -0.8910 0.06351 0.05477 -0.0315 1.0000 0.0710
-10.500 -0.9052 0.05980 0.05074 -0.0293 1.0000 0.0716
-10.250 -0.9135 0.05627 0.04682 -0.0271 1.0000 0.0724
-10.000 -0.9158 0.05294 0.04305 -0.0249 1.0000 0.0732
-9.750 -0.9126 0.04984 0.03949 -0.0228 1.0000 0.0739
-9.500 -0.8996 0.04724 0.03675 -0.0216 1.0000 0.0751
-9.250 -0.8848 0.04520 0.03457 -0.0205 1.0000 0.0771
-9.000 -0.8702 0.04329 0.03248 -0.0192 1.0000 0.0797
-8.750 -0.8546 0.04129 0.03020 -0.0179 1.0000 0.0825
-8.500 -0.8368 0.03926 0.02782 -0.0167 1.0000 0.0851
-8.250 -0.8158 0.03735 0.02569 -0.0158 1.0000 0.0873
-8.000 -0.7944 0.03576 0.02409 -0.0150 1.0000 0.0901
-7.750 -0.7737 0.03437 0.02261 -0.0140 1.0000 0.0943
-7.500 -0.7522 0.03304 0.02104 -0.0129 1.0000 0.1000
-7.250 -0.7326 0.03176 0.01987 -0.0118 1.0000 0.1056
-7.000 -0.7117 0.03055 0.01850 -0.0106 1.0000 0.1129
-6.750 -0.6933 0.02933 0.01736 -0.0092 1.0000 0.1209
-6.500 -0.6757 0.02819 0.01625 -0.0076 1.0000 0.1335
-6.250 -0.6590 0.02706 0.01521 -0.0060 1.0000 0.1515
-6.000 -0.6429 0.02593 0.01422 -0.0043 1.0000 0.1763
-5.750 -0.6278 0.02484 0.01335 -0.0025 1.0000 0.2105
-5.500 -0.6136 0.02381 0.01262 -0.0006 1.0000 0.2581
-5.250 -0.6001 0.02287 0.01205 0.0016 1.0000 0.3182
-5.000 -0.5863 0.02207 0.01161 0.0040 1.0000 0.3813
-4.750 -0.5709 0.02145 0.01124 0.0063 1.0000 0.4394
-4.500 -0.5542 0.02098 0.01097 0.0087 1.0000 0.4935
-4.250 -0.5369 0.02063 0.01082 0.0111 1.0000 0.5451
-4.000 -0.5190 0.02041 0.01074 0.0136 1.0000 0.5946
-3.750 -0.5002 0.02028 0.01072 0.0161 1.0000 0.6403
-3.500 -0.4802 0.02024 0.01074 0.0184 1.0000 0.6814
-3.250 -0.4596 0.02025 0.01077 0.0206 1.0000 0.7188
-3.000 -0.4371 0.02034 0.01085 0.0225 1.0000 0.7526
-2.750 -0.4136 0.02047 0.01094 0.0241 1.0000 0.7845
-2.500 -0.3882 0.02064 0.01106 0.0254 1.0000 0.8139
-2.250 -0.3583 0.02086 0.01120 0.0257 1.0000 0.8400
-2.000 -0.3286 0.02103 0.01129 0.0257 1.0000 0.8656
-1.750 -0.2919 0.02125 0.01140 0.0242 1.0000 0.8876
-1.500 -0.2553 0.02142 0.01147 0.0225 1.0000 0.9095
-1.250 -0.2137 0.02157 0.01153 0.0196 1.0000 0.9289
-1.000 -0.1656 0.02170 0.01158 0.0152 1.0000 0.9456
-0.750 -0.1176 0.02177 0.01158 0.0106 1.0000 0.9615
-0.500 -0.0706 0.02179 0.01157 0.0059 1.0000 0.9770
-0.250 -0.0237 0.02179 0.01155 0.0010 1.0000 0.9922
0.000 0.0000 0.02178 0.01154 0.0000 1.0000 1.0000
0.250 0.0237 0.02179 0.01155 -0.0010 0.9922 1.0000
0.500 0.0706 0.02179 0.01157 -0.0059 0.9770 1.0000
0.750 0.1176 0.02177 0.01158 -0.0106 0.9615 1.0000
1.000 0.1655 0.02170 0.01157 -0.0152 0.9456 1.0000
1.250 0.2136 0.02157 0.01153 -0.0196 0.9289 1.0000
1.500 0.2553 0.02141 0.01147 -0.0225 0.9095 1.0000
1.750 0.2918 0.02125 0.01140 -0.0242 0.8876 1.0000
2.000 0.3286 0.02103 0.01128 -0.0257 0.8656 1.0000
2.250 0.3583 0.02085 0.01119 -0.0256 0.8400 1.0000
2.500 0.3882 0.02063 0.01105 -0.0253 0.8139 1.0000
2.750 0.4136 0.02047 0.01094 -0.0241 0.7845 1.0000
3.000 0.4370 0.02034 0.01084 -0.0225 0.7527 1.0000
3.250 0.4595 0.02025 0.01077 -0.0206 0.7188 1.0000
3.500 0.4801 0.02024 0.01074 -0.0184 0.6814 1.0000
3.750 0.5001 0.02028 0.01072 -0.0161 0.6403 1.0000
4.000 0.5189 0.02040 0.01074 -0.0136 0.5946 1.0000
4.250 0.5368 0.02063 0.01082 -0.0111 0.5452 1.0000
4.500 0.5541 0.02098 0.01097 -0.0086 0.4936 1.0000
4.750 0.5709 0.02145 0.01124 -0.0063 0.4395 1.0000
5.000 0.5863 0.02207 0.01160 -0.0040 0.3814 1.0000
5.250 0.6001 0.02287 0.01205 -0.0016 0.3182 1.0000
5.500 0.6135 0.02381 0.01262 0.0006 0.2581 1.0000
5.750 0.6278 0.02483 0.01334 0.0025 0.2106 1.0000
6.000 0.6429 0.02593 0.01422 0.0043 0.1763 1.0000
6.250 0.6590 0.02706 0.01520 0.0060 0.1515 1.0000
6.500 0.6757 0.02819 0.01625 0.0076 0.1335 1.0000
6.750 0.6934 0.02933 0.01736 0.0092 0.1209 1.0000
7.000 0.7117 0.03055 0.01850 0.0106 0.1129 1.0000
7.250 0.7327 0.03176 0.01987 0.0118 0.1056 1.0000
7.500 0.7522 0.03304 0.02104 0.0129 0.1000 1.0000
7.750 0.7738 0.03437 0.02261 0.0140 0.0943 1.0000
8.000 0.7945 0.03576 0.02409 0.0150 0.0901 1.0000
8.250 0.8159 0.03735 0.02569 0.0157 0.0873 1.0000
8.500 0.8369 0.03926 0.02781 0.0167 0.0851 1.0000
8.750 0.8548 0.04129 0.03020 0.0179 0.0825 1.0000
9.000 0.8703 0.04329 0.03248 0.0192 0.0797 1.0000
9.250 0.8850 0.04520 0.03457 0.0205 0.0770 1.0000
9.500 0.8998 0.04725 0.03675 0.0216 0.0751 1.0000
9.750 0.9128 0.04985 0.03950 0.0228 0.0739 1.0000
10.000 0.9160 0.05295 0.04306 0.0248 0.0732 1.0000
10.250 0.9137 0.05629 0.04683 0.0270 0.0724 1.0000
10.500 0.9055 0.05982 0.05076 0.0292 0.0716 1.0000
10.750 0.8912 0.06353 0.05480 0.0314 0.0710 1.0000
11.000 0.8699 0.06734 0.05886 0.0335 0.0707 1.0000
11.250 0.8441 0.07203 0.06376 0.0340 0.0706 1.0000
11.500 0.8137 0.07815 0.07006 0.0321 0.0710 1.0000
11.750 0.7800 0.08628 0.07831 0.0274 0.0716 1.0000
12.000 0.7472 0.09639 0.08848 0.0206 0.0723 1.0000
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Polar data table (+)
Polar graphs
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