NACA M2 (nacam2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 500,000 Max Cl/Cd: 44.55 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam2-il-500000.txt Download as CSV file: xf-nacam2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.8947 0.05520 0.05251 -0.0194 1.0000 0.0150
-10.250 -0.9149 0.05083 0.04790 -0.0180 1.0000 0.0150
-10.000 -0.9318 0.04536 0.04207 -0.0165 1.0000 0.0150
-9.750 -0.9472 0.03894 0.03516 -0.0143 1.0000 0.0151
-9.500 -0.9467 0.03455 0.03040 -0.0126 1.0000 0.0154
-9.250 -0.9305 0.03314 0.02888 -0.0118 1.0000 0.0159
-9.000 -0.9120 0.03204 0.02767 -0.0112 1.0000 0.0164
-8.750 -0.8945 0.03037 0.02580 -0.0103 1.0000 0.0170
-8.500 -0.8770 0.02836 0.02353 -0.0092 1.0000 0.0179
-8.250 -0.8577 0.02659 0.02143 -0.0082 1.0000 0.0190
-8.000 -0.8350 0.02588 0.02045 -0.0073 1.0000 0.0198
-7.750 -0.8198 0.02194 0.01616 -0.0061 1.0000 0.0209
-7.500 -0.7966 0.02107 0.01523 -0.0056 1.0000 0.0218
-7.250 -0.7727 0.02027 0.01434 -0.0051 1.0000 0.0230
-7.000 -0.7483 0.01952 0.01348 -0.0046 1.0000 0.0244
-6.750 -0.7230 0.01908 0.01291 -0.0042 1.0000 0.0259
-6.500 -0.7001 0.01734 0.01095 -0.0034 1.0000 0.0273
-6.250 -0.6770 0.01597 0.00956 -0.0028 1.0000 0.0290
-6.000 -0.6523 0.01535 0.00890 -0.0023 1.0000 0.0307
-5.750 -0.6273 0.01481 0.00831 -0.0018 1.0000 0.0326
-5.500 -0.6024 0.01425 0.00769 -0.0012 1.0000 0.0341
-5.250 -0.5773 0.01382 0.00720 -0.0007 1.0000 0.0350
-5.000 -0.5554 0.01258 0.00590 0.0004 1.0000 0.0371
-4.750 -0.5320 0.01194 0.00523 0.0011 1.0000 0.0392
-4.500 -0.5081 0.01147 0.00474 0.0019 1.0000 0.0408
-4.250 -0.4840 0.01107 0.00432 0.0026 1.0000 0.0426
-4.000 -0.4599 0.01074 0.00396 0.0034 1.0000 0.0445
-3.750 -0.4357 0.01044 0.00362 0.0041 1.0000 0.0456
-3.500 -0.4120 0.01001 0.00316 0.0049 1.0000 0.0487
-3.250 -0.3881 0.00970 0.00288 0.0057 1.0000 0.0532
-3.000 -0.3641 0.00942 0.00264 0.0065 1.0000 0.0631
-2.750 -0.3414 0.00867 0.00234 0.0071 1.0000 0.1598
-2.500 -0.3185 0.00787 0.00215 0.0075 1.0000 0.3035
-2.250 -0.2948 0.00726 0.00204 0.0079 1.0000 0.4288
-2.000 -0.2705 0.00678 0.00200 0.0083 1.0000 0.5395
-1.750 -0.2456 0.00639 0.00200 0.0087 1.0000 0.6398
-1.500 -0.2162 0.00612 0.00202 0.0083 0.9987 0.7138
-1.250 -0.1797 0.00586 0.00203 0.0066 0.9950 0.7846
-1.000 -0.1437 0.00565 0.00205 0.0052 0.9895 0.8473
-0.750 -0.1055 0.00554 0.00207 0.0033 0.9844 0.8905
-0.500 -0.0717 0.00551 0.00212 0.0026 0.9780 0.9260
-0.250 -0.0361 0.00554 0.00219 0.0015 0.9718 0.9513
0.000 0.0000 0.00555 0.00220 0.0000 0.9630 0.9630
0.250 0.0361 0.00554 0.00219 -0.0015 0.9516 0.9718
0.500 0.0717 0.00551 0.00212 -0.0026 0.9261 0.9780
0.750 0.1055 0.00554 0.00207 -0.0033 0.8906 0.9844
1.000 0.1437 0.00565 0.00205 -0.0052 0.8475 0.9895
1.250 0.1797 0.00585 0.00203 -0.0066 0.7853 0.9950
1.500 0.2161 0.00612 0.00202 -0.0083 0.7139 0.9987
1.750 0.2456 0.00639 0.00200 -0.0087 0.6398 1.0000
2.000 0.2705 0.00678 0.00200 -0.0083 0.5396 1.0000
2.250 0.2947 0.00726 0.00204 -0.0079 0.4288 1.0000
2.500 0.3184 0.00787 0.00215 -0.0075 0.3039 1.0000
2.750 0.3413 0.00867 0.00234 -0.0071 0.1590 1.0000
3.000 0.3640 0.00942 0.00264 -0.0064 0.0632 1.0000
3.250 0.3880 0.00970 0.00288 -0.0057 0.0532 1.0000
3.500 0.4120 0.01001 0.00316 -0.0049 0.0487 1.0000
3.750 0.4356 0.01044 0.00362 -0.0041 0.0457 1.0000
4.000 0.4598 0.01074 0.00396 -0.0033 0.0445 1.0000
4.250 0.4840 0.01107 0.00432 -0.0026 0.0427 1.0000
4.500 0.5080 0.01147 0.00474 -0.0019 0.0408 1.0000
4.750 0.5319 0.01194 0.00523 -0.0011 0.0392 1.0000
5.000 0.5554 0.01258 0.00590 -0.0003 0.0371 1.0000
5.250 0.5773 0.01382 0.00720 0.0007 0.0350 1.0000
5.500 0.6024 0.01425 0.00769 0.0012 0.0341 1.0000
5.750 0.6273 0.01481 0.00831 0.0018 0.0326 1.0000
6.000 0.6523 0.01534 0.00889 0.0023 0.0306 1.0000
6.250 0.6770 0.01597 0.00956 0.0028 0.0290 1.0000
6.500 0.7001 0.01733 0.01095 0.0034 0.0273 1.0000
6.750 0.7230 0.01909 0.01291 0.0042 0.0259 1.0000
7.000 0.7483 0.01951 0.01347 0.0046 0.0244 1.0000
7.250 0.7727 0.02026 0.01433 0.0051 0.0230 1.0000
7.500 0.7966 0.02107 0.01522 0.0056 0.0218 1.0000
7.750 0.8199 0.02193 0.01615 0.0061 0.0209 1.0000
8.000 0.8351 0.02588 0.02046 0.0073 0.0198 1.0000
8.250 0.8577 0.02660 0.02144 0.0081 0.0190 1.0000
8.500 0.8771 0.02836 0.02352 0.0092 0.0179 1.0000
8.750 0.8946 0.03038 0.02582 0.0102 0.0170 1.0000
9.000 0.9120 0.03207 0.02769 0.0111 0.0164 1.0000
9.250 0.9305 0.03317 0.02890 0.0118 0.0159 1.0000
9.500 0.9470 0.03453 0.03037 0.0126 0.0154 1.0000
9.750 0.9471 0.03900 0.03521 0.0143 0.0151 1.0000
10.000 0.9319 0.04540 0.04212 0.0164 0.0150 1.0000
10.250 0.9147 0.05091 0.04798 0.0179 0.0150 1.0000
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Polar data table (+)
Polar graphs
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