NACA M2 (nacam2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 100,000 Max Cl/Cd: 27.94 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam2-il-100000-n5.txt Download as CSV file: xf-nacam2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7428 0.08759 0.08262 -0.0024 1.0000 0.0281
-10.000 -0.7570 0.07863 0.07368 -0.0098 1.0000 0.0278
-9.750 -0.7751 0.07182 0.06678 -0.0149 1.0000 0.0275
-9.500 -0.7944 0.06658 0.06141 -0.0163 1.0000 0.0274
-9.250 -0.8094 0.06133 0.05592 -0.0166 1.0000 0.0274
-9.000 -0.8194 0.05608 0.05032 -0.0163 1.0000 0.0275
-8.750 -0.8241 0.05103 0.04480 -0.0154 1.0000 0.0278
-8.500 -0.8227 0.04647 0.03967 -0.0141 1.0000 0.0283
-8.250 -0.8168 0.04224 0.03506 -0.0130 1.0000 0.0294
-8.000 -0.8022 0.04015 0.03279 -0.0123 1.0000 0.0312
-7.750 -0.7862 0.03788 0.03024 -0.0114 1.0000 0.0332
-7.500 -0.7702 0.03485 0.02672 -0.0102 1.0000 0.0349
-7.250 -0.7515 0.03223 0.02356 -0.0091 1.0000 0.0372
-7.000 -0.7311 0.02996 0.02081 -0.0081 1.0000 0.0398
-6.750 -0.7096 0.02791 0.01863 -0.0074 1.0000 0.0421
-6.500 -0.6867 0.02649 0.01702 -0.0068 1.0000 0.0450
-6.250 -0.6629 0.02519 0.01543 -0.0061 1.0000 0.0487
-6.000 -0.6384 0.02384 0.01383 -0.0054 1.0000 0.0506
-5.750 -0.6153 0.02238 0.01235 -0.0047 1.0000 0.0536
-5.500 -0.5917 0.02144 0.01138 -0.0041 1.0000 0.0574
-5.250 -0.5680 0.02044 0.01029 -0.0033 1.0000 0.0600
-5.000 -0.5446 0.01955 0.00926 -0.0025 1.0000 0.0624
-4.750 -0.5217 0.01867 0.00834 -0.0016 1.0000 0.0652
-4.500 -0.4988 0.01791 0.00756 -0.0008 1.0000 0.0693
-4.250 -0.4751 0.01731 0.00687 0.0000 1.0000 0.0762
-4.000 -0.4520 0.01661 0.00621 0.0008 1.0000 0.0881
-3.750 -0.4292 0.01583 0.00558 0.0016 1.0000 0.1113
-3.500 -0.4072 0.01491 0.00503 0.0024 1.0000 0.1798
-3.250 -0.3859 0.01398 0.00463 0.0032 1.0000 0.2923
-3.000 -0.3649 0.01318 0.00433 0.0042 1.0000 0.4072
-2.750 -0.3449 0.01243 0.00420 0.0058 1.0000 0.5439
-2.500 -0.3249 0.01189 0.00424 0.0081 1.0000 0.6781
-2.250 -0.3038 0.01168 0.00441 0.0108 1.0000 0.7887
-2.000 -0.2769 0.01172 0.00457 0.0123 1.0000 0.8632
-1.750 -0.2413 0.01184 0.00466 0.0116 1.0000 0.9092
-1.500 -0.2011 0.01192 0.00464 0.0094 1.0000 0.9386
-1.250 -0.1600 0.01196 0.00458 0.0067 1.0000 0.9587
-1.000 -0.1163 0.01198 0.00450 0.0032 1.0000 0.9755
-0.750 -0.0672 0.01196 0.00442 -0.0014 1.0000 0.9892
-0.500 -0.0245 0.01191 0.00433 -0.0050 1.0000 1.0000
-0.250 -0.0121 0.01184 0.00425 -0.0025 1.0000 1.0000
0.000 0.0000 0.01181 0.00423 0.0000 1.0000 1.0000
0.250 0.0121 0.01184 0.00425 0.0025 1.0000 1.0000
0.500 0.0245 0.01191 0.00433 0.0050 1.0000 1.0000
0.750 0.0672 0.01196 0.00442 0.0014 0.9892 1.0000
1.000 0.1162 0.01198 0.00450 -0.0032 0.9755 1.0000
1.250 0.1600 0.01196 0.00458 -0.0067 0.9587 1.0000
1.500 0.2011 0.01192 0.00464 -0.0094 0.9386 1.0000
1.750 0.2413 0.01184 0.00466 -0.0116 0.9092 1.0000
2.000 0.2769 0.01172 0.00457 -0.0123 0.8631 1.0000
2.250 0.3038 0.01168 0.00441 -0.0108 0.7889 1.0000
2.500 0.3248 0.01189 0.00424 -0.0081 0.6782 1.0000
2.750 0.3448 0.01243 0.00420 -0.0058 0.5441 1.0000
3.000 0.3648 0.01318 0.00433 -0.0042 0.4075 1.0000
3.500 0.4072 0.01490 0.00503 -0.0024 0.1800 1.0000
3.750 0.4291 0.01583 0.00558 -0.0016 0.1114 1.0000
4.000 0.4520 0.01661 0.00621 -0.0008 0.0881 1.0000
4.250 0.4751 0.01731 0.00687 0.0000 0.0762 1.0000
4.500 0.4988 0.01791 0.00756 0.0008 0.0693 1.0000
4.750 0.5217 0.01867 0.00834 0.0016 0.0652 1.0000
5.000 0.5445 0.01954 0.00926 0.0025 0.0624 1.0000
5.250 0.5680 0.02044 0.01029 0.0033 0.0600 1.0000
5.500 0.5917 0.02143 0.01138 0.0041 0.0574 1.0000
5.750 0.6153 0.02238 0.01235 0.0047 0.0536 1.0000
6.000 0.6384 0.02384 0.01382 0.0054 0.0506 1.0000
6.250 0.6629 0.02519 0.01543 0.0061 0.0487 1.0000
6.500 0.6867 0.02649 0.01702 0.0068 0.0450 1.0000
6.750 0.7096 0.02791 0.01863 0.0074 0.0421 1.0000
7.000 0.7311 0.02996 0.02081 0.0081 0.0398 1.0000
7.250 0.7515 0.03222 0.02356 0.0091 0.0372 1.0000
7.500 0.7702 0.03485 0.02672 0.0102 0.0349 1.0000
7.750 0.7863 0.03788 0.03024 0.0114 0.0332 1.0000
8.000 0.8022 0.04015 0.03279 0.0123 0.0312 1.0000
8.250 0.8169 0.04224 0.03506 0.0130 0.0294 1.0000
8.500 0.8228 0.04647 0.03967 0.0141 0.0283 1.0000
8.750 0.8241 0.05103 0.04481 0.0154 0.0278 1.0000
9.000 0.8195 0.05609 0.05034 0.0163 0.0275 1.0000
9.250 0.8095 0.06136 0.05594 0.0166 0.0274 1.0000
9.500 0.7945 0.06662 0.06144 0.0162 0.0274 1.0000
9.750 0.7754 0.07186 0.06682 0.0148 0.0275 1.0000
10.000 0.7573 0.07871 0.07377 0.0097 0.0278 1.0000
10.250 0.7432 0.08771 0.08273 0.0022 0.0281 1.0000
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Polar data table (+)
Polar graphs
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