NACA M10 AIRFOIL (m10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M10 AIRFOIL (m10-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.94 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m10-il-1000000.txt Download as CSV file: xf-m10-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5992 0.08650 0.08499 0.0080 1.0000 0.0119
-7.750 -0.5938 0.08138 0.07987 0.0022 1.0000 0.0125
-7.250 -0.6386 0.02449 0.02149 -0.0251 1.0000 0.0092
-7.000 -0.6266 0.01606 0.01189 -0.0241 1.0000 0.0098
-6.750 -0.6031 0.01389 0.00934 -0.0237 1.0000 0.0108
-6.500 -0.5761 0.01365 0.00907 -0.0237 1.0000 0.0115
-6.250 -0.5490 0.01332 0.00869 -0.0236 1.0000 0.0123
-6.000 -0.5222 0.01283 0.00810 -0.0234 1.0000 0.0132
-5.750 -0.4948 0.01265 0.00786 -0.0233 1.0000 0.0138
-5.500 -0.4687 0.01179 0.00691 -0.0232 1.0000 0.0155
-5.250 -0.4409 0.01202 0.00718 -0.0232 1.0000 0.0166
-5.000 -0.4136 0.01185 0.00698 -0.0231 1.0000 0.0179
-4.750 -0.3861 0.01183 0.00693 -0.0230 1.0000 0.0190
-4.500 -0.3605 0.01069 0.00565 -0.0227 1.0000 0.0208
-4.250 -0.3336 0.01062 0.00560 -0.0226 1.0000 0.0223
-4.000 -0.3069 0.01055 0.00553 -0.0224 1.0000 0.0239
-3.750 -0.2809 0.01026 0.00521 -0.0220 1.0000 0.0253
-3.500 -0.2532 0.01000 0.00492 -0.0220 0.9989 0.0265
-3.250 -0.2172 0.01010 0.00501 -0.0239 0.9931 0.0275
-3.000 -0.1845 0.00869 0.00348 -0.0251 0.9837 0.0300
-2.750 -0.1519 0.00830 0.00307 -0.0262 0.9688 0.0317
-2.500 -0.1238 0.00803 0.00276 -0.0261 0.9456 0.0328
-2.250 -0.0988 0.00781 0.00244 -0.0252 0.9196 0.0335
-2.000 -0.0736 0.00762 0.00215 -0.0244 0.8941 0.0342
-1.750 -0.0476 0.00747 0.00189 -0.0239 0.8702 0.0351
-1.500 -0.0208 0.00736 0.00169 -0.0235 0.8473 0.0366
-1.250 0.0063 0.00727 0.00150 -0.0232 0.8263 0.0380
-1.000 0.0337 0.00721 0.00135 -0.0231 0.8060 0.0390
-0.750 0.0613 0.00710 0.00114 -0.0229 0.7869 0.0428
-0.500 0.0891 0.00703 0.00104 -0.0228 0.7686 0.0480
-0.250 0.1168 0.00686 0.00097 -0.0228 0.7509 0.0907
0.000 0.1441 0.00647 0.00093 -0.0229 0.7338 0.2291
0.250 0.1664 0.00479 0.00090 -0.0226 0.7177 0.7847
0.500 0.1863 0.00436 0.00094 -0.0202 0.7020 0.9690
0.750 0.2353 0.00443 0.00095 -0.0249 0.6844 1.0000
1.000 0.2616 0.00453 0.00093 -0.0246 0.6597 1.0000
1.250 0.2880 0.00464 0.00093 -0.0242 0.6320 1.0000
1.500 0.3146 0.00474 0.00094 -0.0240 0.6084 1.0000
1.750 0.3415 0.00485 0.00097 -0.0237 0.5883 1.0000
2.000 0.3685 0.00497 0.00100 -0.0236 0.5638 1.0000
2.500 0.4223 0.00534 0.00111 -0.0233 0.4926 1.0000
2.750 0.4492 0.00557 0.00119 -0.0232 0.4498 1.0000
3.000 0.4759 0.00588 0.00130 -0.0231 0.3951 1.0000
3.250 0.5021 0.00636 0.00147 -0.0230 0.3158 1.0000
3.500 0.5270 0.00725 0.00178 -0.0230 0.1804 1.0000
3.750 0.5517 0.00828 0.00224 -0.0229 0.0490 1.0000
4.000 0.5788 0.00858 0.00250 -0.0228 0.0384 1.0000
4.250 0.6061 0.00880 0.00274 -0.0228 0.0347 1.0000
4.500 0.6330 0.00918 0.00312 -0.0226 0.0290 1.0000
4.750 0.6601 0.00944 0.00343 -0.0226 0.0266 1.0000
5.000 0.6872 0.00966 0.00365 -0.0225 0.0235 1.0000
5.250 0.7131 0.01029 0.00432 -0.0223 0.0189 1.0000
5.500 0.7403 0.01047 0.00451 -0.0222 0.0177 1.0000
5.750 0.7671 0.01076 0.00483 -0.0221 0.0159 1.0000
6.000 0.7934 0.01118 0.00526 -0.0220 0.0142 1.0000
6.250 0.8177 0.01210 0.00628 -0.0215 0.0127 1.0000
6.500 0.8442 0.01238 0.00660 -0.0214 0.0119 1.0000
6.750 0.8698 0.01287 0.00713 -0.0211 0.0110 1.0000
7.000 0.8952 0.01337 0.00769 -0.0208 0.0102 1.0000
7.250 0.9200 0.01401 0.00836 -0.0205 0.0096 1.0000
7.500 0.9383 0.01626 0.01083 -0.0192 0.0087 1.0000
7.750 0.9626 0.01701 0.01169 -0.0187 0.0085 1.0000
8.000 0.9866 0.01782 0.01260 -0.0183 0.0081 1.0000
8.250 1.0097 0.01884 0.01375 -0.0177 0.0077 1.0000
8.500 1.0331 0.01967 0.01470 -0.0172 0.0072 1.0000
8.750 1.0559 0.02055 0.01568 -0.0167 0.0068 1.0000
9.000 1.0773 0.02173 0.01701 -0.0160 0.0065 1.0000
9.250 1.0978 0.02301 0.01844 -0.0153 0.0063 1.0000
9.500 1.1160 0.02474 0.02036 -0.0144 0.0061 1.0000
9.750 1.1294 0.02739 0.02330 -0.0130 0.0060 1.0000
10.000 1.1338 0.03160 0.02796 -0.0110 0.0058 1.0000
10.250 1.1262 0.03729 0.03419 -0.0083 0.0058 1.0000
10.500 1.1106 0.04312 0.04046 -0.0057 0.0057 1.0000
10.750 1.0912 0.04776 0.04539 -0.0031 0.0057 1.0000
11.000 1.0713 0.05199 0.04981 -0.0021 0.0058 1.0000
11.250 1.0507 0.05758 0.05559 -0.0044 0.0058 1.0000
11.500 1.0345 0.06394 0.06211 -0.0089 0.0058 1.0000
11.750 1.0180 0.07188 0.07019 -0.0152 0.0059 1.0000
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Polar data table (+)
Polar graphs
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