NACA M10 AIRFOIL (m10-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M10 AIRFOIL (m10-il) Reynolds number: 500,000 Max Cl/Cd: 72.85 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m10-il-500000.txt Download as CSV file: xf-m10-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M10 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5903 0.10136 0.09916 0.0124 1.0000 0.0191
-8.500 -0.5864 0.09739 0.09521 0.0090 1.0000 0.0193
-8.250 -0.5837 0.09320 0.09105 0.0056 1.0000 0.0193
-8.000 -0.5802 0.08857 0.08642 0.0009 1.0000 0.0194
-7.750 -0.5721 0.08343 0.08127 -0.0042 1.0000 0.0194
-7.500 -0.5625 0.07815 0.07595 -0.0088 1.0000 0.0194
-7.250 -0.5514 0.07275 0.07050 -0.0129 1.0000 0.0194
-7.000 -0.5390 0.06721 0.06488 -0.0165 1.0000 0.0195
-6.750 -0.5374 0.05765 0.05519 -0.0209 1.0000 0.0200
-6.500 -0.5249 0.05385 0.05131 -0.0221 1.0000 0.0206
-6.250 -0.5083 0.05120 0.04860 -0.0228 1.0000 0.0213
-6.000 -0.4895 0.04808 0.04538 -0.0239 1.0000 0.0224
-5.750 -0.4684 0.04417 0.04130 -0.0251 1.0000 0.0243
-5.500 -0.4365 0.04115 0.03797 -0.0255 1.0000 0.0274
-5.250 -0.4298 0.02552 0.02137 -0.0258 1.0000 0.0213
-5.000 -0.4062 0.02291 0.01847 -0.0255 1.0000 0.0223
-4.750 -0.3817 0.02017 0.01535 -0.0249 1.0000 0.0236
-4.500 -0.3559 0.01843 0.01329 -0.0244 1.0000 0.0258
-4.250 -0.3295 0.01754 0.01212 -0.0239 1.0000 0.0281
-4.000 -0.3055 0.01477 0.00906 -0.0235 1.0000 0.0303
-3.750 -0.2799 0.01409 0.00830 -0.0231 1.0000 0.0324
-3.500 -0.2546 0.01359 0.00773 -0.0226 1.0000 0.0351
-3.250 -0.2298 0.01283 0.00685 -0.0219 1.0000 0.0367
-3.000 -0.2056 0.01224 0.00617 -0.0211 1.0000 0.0379
-2.750 -0.1824 0.01155 0.00541 -0.0202 1.0000 0.0395
-2.500 -0.1485 0.01039 0.00419 -0.0216 0.9964 0.0412
-2.250 -0.1113 0.00975 0.00352 -0.0237 0.9907 0.0426
-2.000 -0.0740 0.00928 0.00304 -0.0258 0.9828 0.0443
-1.750 -0.0387 0.00892 0.00268 -0.0275 0.9704 0.0468
-1.500 -0.0058 0.00859 0.00232 -0.0284 0.9534 0.0490
-1.250 0.0228 0.00839 0.00207 -0.0283 0.9313 0.0511
-1.000 0.0483 0.00815 0.00177 -0.0275 0.9074 0.0564
-0.750 0.0734 0.00803 0.00161 -0.0266 0.8841 0.0656
-0.500 0.0983 0.00746 0.00148 -0.0261 0.8616 0.2090
-0.250 0.1094 0.00526 0.00148 -0.0227 0.8415 0.8872
0.000 0.1641 0.00524 0.00148 -0.0280 0.8234 1.0000
0.250 0.1896 0.00532 0.00141 -0.0274 0.8028 1.0000
0.500 0.2154 0.00539 0.00137 -0.0269 0.7835 1.0000
0.750 0.2414 0.00547 0.00135 -0.0264 0.7644 1.0000
1.000 0.2675 0.00556 0.00134 -0.0259 0.7460 1.0000
1.250 0.2938 0.00565 0.00134 -0.0255 0.7281 1.0000
1.500 0.3200 0.00575 0.00136 -0.0251 0.7055 1.0000
1.750 0.3462 0.00588 0.00137 -0.0247 0.6782 1.0000
2.000 0.3727 0.00600 0.00140 -0.0243 0.6533 1.0000
2.250 0.3994 0.00613 0.00145 -0.0240 0.6317 1.0000
2.500 0.4262 0.00627 0.00152 -0.0238 0.6055 1.0000
2.750 0.4527 0.00646 0.00159 -0.0235 0.5707 1.0000
3.000 0.4792 0.00668 0.00167 -0.0232 0.5316 1.0000
3.250 0.5056 0.00694 0.00177 -0.0230 0.4832 1.0000
3.500 0.5317 0.00731 0.00193 -0.0228 0.4222 1.0000
3.750 0.5565 0.00804 0.00218 -0.0226 0.3076 1.0000
4.000 0.5776 0.00987 0.00289 -0.0224 0.0683 1.0000
4.250 0.6038 0.01038 0.00333 -0.0222 0.0481 1.0000
4.500 0.6300 0.01092 0.00387 -0.0219 0.0403 1.0000
4.750 0.6563 0.01135 0.00438 -0.0217 0.0357 1.0000
5.000 0.6822 0.01190 0.00496 -0.0215 0.0309 1.0000
5.250 0.7060 0.01301 0.00617 -0.0209 0.0271 1.0000
5.500 0.7321 0.01343 0.00664 -0.0206 0.0245 1.0000
5.750 0.7576 0.01395 0.00720 -0.0203 0.0218 1.0000
6.000 0.7806 0.01516 0.00845 -0.0196 0.0198 1.0000
6.250 0.8026 0.01686 0.01027 -0.0187 0.0186 1.0000
6.500 0.8276 0.01775 0.01127 -0.0181 0.0176 1.0000
6.750 0.8525 0.01852 0.01213 -0.0177 0.0161 1.0000
7.000 0.8769 0.01939 0.01308 -0.0172 0.0150 1.0000
7.250 0.9005 0.02052 0.01433 -0.0167 0.0142 1.0000
7.500 0.9224 0.02241 0.01636 -0.0160 0.0136 1.0000
7.750 0.9402 0.02641 0.02074 -0.0147 0.0131 1.0000
8.000 0.9563 0.03039 0.02514 -0.0133 0.0131 1.0000
8.250 0.9751 0.03274 0.02777 -0.0122 0.0133 1.0000
19.000 0.9785 0.25475 0.25242 -0.1043 0.0086 1.0000
19.250 0.9858 0.25863 0.25630 -0.1076 0.0085 1.0000
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Polar data table (+)
Polar graphs
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