NACA M6 AIRFOIL (m6-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 AIRFOIL (m6-il) Reynolds number: 500,000 Max Cl/Cd: 76.41 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m6-il-500000-n5.txt Download as CSV file: xf-m6-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9351 0.04927 0.04623 -0.0362 1.0000 0.0213
-12.000 -0.9497 0.04600 0.04279 -0.0344 1.0000 0.0214
-11.750 -0.9581 0.04361 0.04024 -0.0317 1.0000 0.0215
-11.500 -0.9615 0.04143 0.03791 -0.0290 1.0000 0.0217
-11.250 -0.9594 0.03923 0.03552 -0.0269 1.0000 0.0218
-11.000 -0.9539 0.03716 0.03325 -0.0249 1.0000 0.0220
-10.750 -0.9454 0.03523 0.03114 -0.0231 1.0000 0.0223
-10.500 -0.9347 0.03338 0.02909 -0.0215 1.0000 0.0225
-10.250 -0.9214 0.03175 0.02727 -0.0200 1.0000 0.0228
-10.000 -0.9066 0.03019 0.02552 -0.0186 1.0000 0.0232
-9.750 -0.8908 0.02863 0.02374 -0.0173 1.0000 0.0236
-9.500 -0.8739 0.02708 0.02196 -0.0160 1.0000 0.0239
-9.250 -0.8554 0.02570 0.02037 -0.0149 1.0000 0.0242
-9.000 -0.8291 0.02439 0.01883 -0.0153 0.9654 0.0245
-8.750 -0.8049 0.02335 0.01758 -0.0150 0.9400 0.0247
-8.500 -0.7840 0.02253 0.01656 -0.0138 0.9176 0.0249
-8.250 -0.7629 0.02194 0.01577 -0.0125 0.8986 0.0251
-8.000 -0.7428 0.02063 0.01427 -0.0113 0.8820 0.0255
-7.750 -0.7207 0.01969 0.01320 -0.0103 0.8664 0.0258
-7.500 -0.6975 0.01894 0.01233 -0.0095 0.8511 0.0261
-7.250 -0.6737 0.01829 0.01156 -0.0088 0.8363 0.0263
-7.000 -0.6493 0.01769 0.01085 -0.0082 0.8215 0.0266
-6.750 -0.6245 0.01712 0.01018 -0.0077 0.8070 0.0268
-6.500 -0.5995 0.01659 0.00954 -0.0071 0.7931 0.0271
-6.250 -0.5741 0.01610 0.00893 -0.0067 0.7796 0.0274
-6.000 -0.5486 0.01562 0.00836 -0.0062 0.7665 0.0277
-5.750 -0.5228 0.01517 0.00781 -0.0058 0.7542 0.0280
-5.500 -0.4968 0.01475 0.00730 -0.0055 0.7427 0.0283
-5.250 -0.4707 0.01438 0.00684 -0.0051 0.7319 0.0288
-5.000 -0.4443 0.01403 0.00642 -0.0048 0.7213 0.0293
-4.750 -0.4179 0.01368 0.00600 -0.0045 0.7118 0.0296
-4.500 -0.3914 0.01335 0.00560 -0.0042 0.7022 0.0299
-4.250 -0.3648 0.01305 0.00524 -0.0040 0.6933 0.0302
-4.000 -0.3381 0.01277 0.00490 -0.0037 0.6846 0.0304
-3.750 -0.3114 0.01245 0.00454 -0.0035 0.6764 0.0308
-3.500 -0.2851 0.01211 0.00416 -0.0031 0.6681 0.0314
-3.250 -0.2582 0.01184 0.00385 -0.0029 0.6604 0.0319
-3.000 -0.2311 0.01162 0.00360 -0.0028 0.6525 0.0326
-2.750 -0.2037 0.01142 0.00337 -0.0026 0.6451 0.0333
-2.500 -0.1762 0.01125 0.00316 -0.0025 0.6375 0.0341
-2.250 -0.1486 0.01110 0.00298 -0.0024 0.6304 0.0350
-2.000 -0.1209 0.01096 0.00281 -0.0024 0.6229 0.0362
-1.750 -0.0932 0.01083 0.00265 -0.0023 0.6161 0.0378
-1.500 -0.0655 0.01068 0.00250 -0.0022 0.6087 0.0405
-1.250 -0.0379 0.01056 0.00237 -0.0022 0.6018 0.0451
-1.000 -0.0107 0.01034 0.00227 -0.0021 0.5948 0.0719
-0.500 0.0436 0.00995 0.00211 -0.0019 0.5810 0.1421
-0.250 0.0711 0.00980 0.00205 -0.0018 0.5736 0.1728
0.250 0.1205 0.00885 0.00189 -0.0011 0.5598 0.4126
0.500 0.1283 0.00726 0.00186 0.0032 0.5537 0.8374
0.750 0.1563 0.00727 0.00199 0.0036 0.5466 0.8874
1.000 0.1851 0.00736 0.00208 0.0037 0.5390 0.9138
1.250 0.2162 0.00750 0.00222 0.0034 0.5316 0.9336
1.500 0.2485 0.00771 0.00240 0.0028 0.5234 0.9504
1.750 0.2840 0.00795 0.00260 0.0015 0.5154 0.9622
2.000 0.3212 0.00811 0.00272 -0.0005 0.5062 0.9662
2.250 0.3526 0.00821 0.00277 -0.0012 0.4973 0.9699
2.500 0.3856 0.00834 0.00284 -0.0024 0.4869 0.9729
2.750 0.4196 0.00843 0.00288 -0.0038 0.4748 0.9739
3.000 0.4518 0.00852 0.00293 -0.0048 0.4637 0.9750
3.250 0.4838 0.00861 0.00299 -0.0058 0.4543 0.9762
3.500 0.5153 0.00870 0.00305 -0.0067 0.4453 0.9776
3.750 0.5458 0.00880 0.00312 -0.0074 0.4353 0.9793
4.000 0.5752 0.00893 0.00320 -0.0079 0.4225 0.9813
4.250 0.6032 0.00907 0.00330 -0.0080 0.4101 0.9836
4.500 0.6355 0.00917 0.00340 -0.0092 0.3999 0.9844
4.750 0.6671 0.00931 0.00351 -0.0102 0.3873 0.9853
5.000 0.6979 0.00951 0.00363 -0.0111 0.3669 0.9863
5.250 0.7285 0.00975 0.00379 -0.0119 0.3444 0.9876
5.500 0.7587 0.01000 0.00396 -0.0127 0.3213 0.9890
5.750 0.7878 0.01031 0.00416 -0.0134 0.2966 0.9904
6.250 0.8435 0.01109 0.00470 -0.0142 0.2399 0.9935
6.500 0.8727 0.01152 0.00501 -0.0151 0.2118 0.9945
6.750 0.9022 0.01194 0.00533 -0.0159 0.1886 0.9956
7.000 0.9308 0.01240 0.00569 -0.0166 0.1652 0.9968
7.250 0.9585 0.01294 0.00610 -0.0172 0.1369 0.9980
7.750 1.0084 0.01430 0.00715 -0.0176 0.0802 1.0000
8.000 1.0272 0.01477 0.00758 -0.0162 0.0699 1.0000
8.250 1.0454 0.01524 0.00802 -0.0148 0.0604 1.0000
8.500 1.0634 0.01569 0.00845 -0.0132 0.0522 1.0000
8.750 1.0809 0.01615 0.00889 -0.0117 0.0465 1.0000
9.000 1.0977 0.01663 0.00936 -0.0100 0.0421 1.0000
9.250 1.1145 0.01707 0.00983 -0.0083 0.0391 1.0000
9.500 1.1299 0.01759 0.01035 -0.0064 0.0364 1.0000
9.750 1.1455 0.01806 0.01086 -0.0045 0.0346 1.0000
10.000 1.1606 0.01855 0.01138 -0.0026 0.0328 1.0000
10.250 1.1742 0.01910 0.01196 -0.0005 0.0311 1.0000
10.500 1.1855 0.01975 0.01263 0.0018 0.0295 1.0000
10.750 1.1985 0.02028 0.01323 0.0039 0.0285 1.0000
11.000 1.2091 0.02088 0.01388 0.0064 0.0273 1.0000
11.250 1.2164 0.02156 0.01461 0.0092 0.0262 1.0000
11.500 1.2239 0.02244 0.01552 0.0115 0.0251 1.0000
11.750 1.2321 0.02345 0.01658 0.0134 0.0241 1.0000
12.000 1.2432 0.02441 0.01762 0.0147 0.0232 1.0000
12.250 1.2537 0.02551 0.01880 0.0158 0.0222 1.0000
12.500 1.2634 0.02676 0.02011 0.0167 0.0213 1.0000
12.750 1.2720 0.02820 0.02159 0.0175 0.0205 1.0000
13.000 1.2789 0.02986 0.02331 0.0182 0.0197 1.0000
13.250 1.2878 0.03142 0.02496 0.0187 0.0190 1.0000
13.500 1.2959 0.03312 0.02675 0.0190 0.0183 1.0000
13.750 1.3029 0.03495 0.02865 0.0193 0.0176 1.0000
14.000 1.3087 0.03696 0.03072 0.0194 0.0170 1.0000
14.250 1.3127 0.03921 0.03303 0.0195 0.0165 1.0000
14.500 1.3137 0.04180 0.03570 0.0195 0.0160 1.0000
14.750 1.3167 0.04424 0.03823 0.0194 0.0156 1.0000
15.000 1.3184 0.04685 0.04094 0.0192 0.0153 1.0000
15.250 1.3190 0.04961 0.04380 0.0189 0.0149 1.0000
15.500 1.3188 0.05251 0.04681 0.0186 0.0146 1.0000
15.750 1.3180 0.05557 0.04996 0.0181 0.0142 1.0000
16.000 1.3166 0.05879 0.05326 0.0174 0.0139 1.0000
16.250 1.3143 0.06222 0.05678 0.0166 0.0136 1.0000
16.500 1.3108 0.06590 0.06054 0.0156 0.0133 1.0000
16.750 1.3055 0.06988 0.06461 0.0145 0.0131 1.0000
17.000 1.2984 0.07422 0.06904 0.0132 0.0128 1.0000
17.250 1.2924 0.07848 0.07340 0.0118 0.0126 1.0000
17.500 1.2874 0.08264 0.07767 0.0104 0.0124 1.0000
17.750 1.2816 0.08700 0.08214 0.0089 0.0122 1.0000
18.000 1.2751 0.09154 0.08679 0.0073 0.0120 1.0000
18.250 1.2682 0.09621 0.09157 0.0055 0.0119 1.0000
18.500 1.2604 0.10104 0.09651 0.0036 0.0117 1.0000
18.750 1.2524 0.10600 0.10157 0.0016 0.0115 1.0000
19.000 1.2441 0.11109 0.10676 -0.0006 0.0114 1.0000
19.250 1.2358 0.11626 0.11204 -0.0029 0.0112 1.0000
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